Month: September 2024
How to calculate the mean integrated curvature of an ellipsoid?
I am using the following code to compute the surface area, mean integrated curvature, and Euler characteristic of the ellipsoid parameterized by r(x,y). Here ‘x’ and ‘y’ represent the angles $theta$ and $phi$ in spherical coordinates. The code is
clc; clear;
%ellipsoid radii
a=value1; b=value2; c=value2;
syms x y
%parametric vector equation of the ellipsoid
r=[a*cos(y)*sin(x), b*sin(x)*sin(y), c*cos(x)];
%partial derivatives
r_x=diff(r,x);
r_xx=diff(r_x,x);
r_y=diff(r,y);
r_yy=diff(r_y,y);
r_xy=diff(r_x,y);
%normal vector to the surface at each point
n=cross(r_x,r_y)/norm(cross(r_x,r_y));
%coefficients of the second fundamental form
E=dot(r_x,r_x);
F=dot(r_x,r_y);
G=dot(r_y,r_y);
L=dot(r_xx,n);
M=dot(r_xy,n);
N=dot(r_yy,n);
A=E*G-F^2;
K=((E*N)+(G*L)-(2*F*M))/A;
H=(L*N-M^2)/A;
dA=sqrt(A);
dC=K*dA;
dX=H*dA;
%converting syms functions to matlab functions
dA_=matlabFunction(dA); dC_=matlabFunction(dC); dX_=matlabFunction(dX);
% numerical integration
S = integral2(dA_, 0, 2*pi, 0, pi); %total surface area
C = (1/2)*integral2(dC_, 0, 2*pi, 0, pi); % medium integrated curvature
X = (1/(2*pi))*integral2(dX_, 0, 2*pi, 0, pi); % Euler characteristics
S and X give me very well, but the problem is with C, which always gives me very small, of the order of 1e-16 to 1e-14, which is absurd since C must be of the order of 4*pi*r (for the case of a sphere a=b=c=r). Could someone tell me what is wrong?I am using the following code to compute the surface area, mean integrated curvature, and Euler characteristic of the ellipsoid parameterized by r(x,y). Here ‘x’ and ‘y’ represent the angles $theta$ and $phi$ in spherical coordinates. The code is
clc; clear;
%ellipsoid radii
a=value1; b=value2; c=value2;
syms x y
%parametric vector equation of the ellipsoid
r=[a*cos(y)*sin(x), b*sin(x)*sin(y), c*cos(x)];
%partial derivatives
r_x=diff(r,x);
r_xx=diff(r_x,x);
r_y=diff(r,y);
r_yy=diff(r_y,y);
r_xy=diff(r_x,y);
%normal vector to the surface at each point
n=cross(r_x,r_y)/norm(cross(r_x,r_y));
%coefficients of the second fundamental form
E=dot(r_x,r_x);
F=dot(r_x,r_y);
G=dot(r_y,r_y);
L=dot(r_xx,n);
M=dot(r_xy,n);
N=dot(r_yy,n);
A=E*G-F^2;
K=((E*N)+(G*L)-(2*F*M))/A;
H=(L*N-M^2)/A;
dA=sqrt(A);
dC=K*dA;
dX=H*dA;
%converting syms functions to matlab functions
dA_=matlabFunction(dA); dC_=matlabFunction(dC); dX_=matlabFunction(dX);
% numerical integration
S = integral2(dA_, 0, 2*pi, 0, pi); %total surface area
C = (1/2)*integral2(dC_, 0, 2*pi, 0, pi); % medium integrated curvature
X = (1/(2*pi))*integral2(dX_, 0, 2*pi, 0, pi); % Euler characteristics
S and X give me very well, but the problem is with C, which always gives me very small, of the order of 1e-16 to 1e-14, which is absurd since C must be of the order of 4*pi*r (for the case of a sphere a=b=c=r). Could someone tell me what is wrong? I am using the following code to compute the surface area, mean integrated curvature, and Euler characteristic of the ellipsoid parameterized by r(x,y). Here ‘x’ and ‘y’ represent the angles $theta$ and $phi$ in spherical coordinates. The code is
clc; clear;
%ellipsoid radii
a=value1; b=value2; c=value2;
syms x y
%parametric vector equation of the ellipsoid
r=[a*cos(y)*sin(x), b*sin(x)*sin(y), c*cos(x)];
%partial derivatives
r_x=diff(r,x);
r_xx=diff(r_x,x);
r_y=diff(r,y);
r_yy=diff(r_y,y);
r_xy=diff(r_x,y);
%normal vector to the surface at each point
n=cross(r_x,r_y)/norm(cross(r_x,r_y));
%coefficients of the second fundamental form
E=dot(r_x,r_x);
F=dot(r_x,r_y);
G=dot(r_y,r_y);
L=dot(r_xx,n);
M=dot(r_xy,n);
N=dot(r_yy,n);
A=E*G-F^2;
K=((E*N)+(G*L)-(2*F*M))/A;
H=(L*N-M^2)/A;
dA=sqrt(A);
dC=K*dA;
dX=H*dA;
%converting syms functions to matlab functions
dA_=matlabFunction(dA); dC_=matlabFunction(dC); dX_=matlabFunction(dX);
% numerical integration
S = integral2(dA_, 0, 2*pi, 0, pi); %total surface area
C = (1/2)*integral2(dC_, 0, 2*pi, 0, pi); % medium integrated curvature
X = (1/(2*pi))*integral2(dX_, 0, 2*pi, 0, pi); % Euler characteristics
S and X give me very well, but the problem is with C, which always gives me very small, of the order of 1e-16 to 1e-14, which is absurd since C must be of the order of 4*pi*r (for the case of a sphere a=b=c=r). Could someone tell me what is wrong? ellipsoid, curvature, surface, ellipsoidal fit MATLAB Answers — New Questions
Display the exact selected area by zooming in on a surface/image
Hi,
I have an uiaxes on a GUI (appdesigner) on which I draw a 2D surface with axis equal. When I zoom in by selecting an area, I’d like the area displayed to correspond exactly to the one selected (no more, no less). I had this behavior with MATLAB 2019/2020. However, since upgrading to version 2024, I’ve been able to zoom in, but the initial width/length aspect ratio of the displayed surface remains unchanged. As the background isn’t clickable, elongated surfaces are very difficult to manage.
Here’s an illustration and an attached .fig. I’ve tried changing the daspect and DataAspectRatioMode, but couldn’t get it right.
If anyone has a solution, I’d love to hear from you!
Thanks in advance.Hi,
I have an uiaxes on a GUI (appdesigner) on which I draw a 2D surface with axis equal. When I zoom in by selecting an area, I’d like the area displayed to correspond exactly to the one selected (no more, no less). I had this behavior with MATLAB 2019/2020. However, since upgrading to version 2024, I’ve been able to zoom in, but the initial width/length aspect ratio of the displayed surface remains unchanged. As the background isn’t clickable, elongated surfaces are very difficult to manage.
Here’s an illustration and an attached .fig. I’ve tried changing the daspect and DataAspectRatioMode, but couldn’t get it right.
If anyone has a solution, I’d love to hear from you!
Thanks in advance. Hi,
I have an uiaxes on a GUI (appdesigner) on which I draw a 2D surface with axis equal. When I zoom in by selecting an area, I’d like the area displayed to correspond exactly to the one selected (no more, no less). I had this behavior with MATLAB 2019/2020. However, since upgrading to version 2024, I’ve been able to zoom in, but the initial width/length aspect ratio of the displayed surface remains unchanged. As the background isn’t clickable, elongated surfaces are very difficult to manage.
Here’s an illustration and an attached .fig. I’ve tried changing the daspect and DataAspectRatioMode, but couldn’t get it right.
If anyone has a solution, I’d love to hear from you!
Thanks in advance. aspect ratio, zoom, uiaxes, axes, surface, daspect, aspect, image MATLAB Answers — New Questions
Difficulty Finding Hydrogen (H2) Properties for Gas Properties (G) Block
Hi everyone,
I’m having some trouble finding the different properties of Hydrogen (H2) that I need to set in the Gas Properties (G) block in Simscape. I’m hoping someone here can provide me with some guidance on how to approach this.
Can anyone recommend a resource or provide some tips on how to determine these properties for Hydrogen (H2)?
Any help would be greatly appreciated!
Thanks in advance,Hi everyone,
I’m having some trouble finding the different properties of Hydrogen (H2) that I need to set in the Gas Properties (G) block in Simscape. I’m hoping someone here can provide me with some guidance on how to approach this.
Can anyone recommend a resource or provide some tips on how to determine these properties for Hydrogen (H2)?
Any help would be greatly appreciated!
Thanks in advance, Hi everyone,
I’m having some trouble finding the different properties of Hydrogen (H2) that I need to set in the Gas Properties (G) block in Simscape. I’m hoping someone here can provide me with some guidance on how to approach this.
Can anyone recommend a resource or provide some tips on how to determine these properties for Hydrogen (H2)?
Any help would be greatly appreciated!
Thanks in advance, gasproperties, hydrogen, h2 MATLAB Answers — New Questions
How to change the altitude in UAV Package Delivery Example?
I am using the UAV Package Delivery Example to fly a drone on top of the buildings in the US City Block. Are the heights of the buildings have a finite value or they are assumed to be inifinity? How do i change the altitude of the UAV such that I can fly above the buildings?I am using the UAV Package Delivery Example to fly a drone on top of the buildings in the US City Block. Are the heights of the buildings have a finite value or they are assumed to be inifinity? How do i change the altitude of the UAV such that I can fly above the buildings? I am using the UAV Package Delivery Example to fly a drone on top of the buildings in the US City Block. Are the heights of the buildings have a finite value or they are assumed to be inifinity? How do i change the altitude of the UAV such that I can fly above the buildings? uav, package, delivery, simulink MATLAB Answers — New Questions
visboundaries/linewidth not rendering sharply when exporting figures
Hi everyone,
I am working with MATLAB to generate images that include segmentation lines (using visboundaries and viscircles) drawn over images. However, when I export these images (using saveas or print), the lines are not rendered sharply. Instead, they are much thicker. If I change the LineWidth to something like 0.5 a “halo”/outline effect appears around them. Interestingly, when I zoom into the figure manually within MATLAB and then export, the lines are much sharper.
I already tried a different export format, different dpi (max 1000) and changing the figure position to a higher zoom level.
Any idea on how to improve the export quality?
figure;
imshow(dicomData, [], ‘InitialMagnification’, ‘fit’);
title(sprintf(‘segmentation %s’, fileTitle), ‘Interpreter’, ‘none’);
hold on;
visboundaries(signalRoiMask, ‘Color’, ‘g’, ‘LineWidth’, 1);
visboundaries(lesionMask, ‘Color’, ‘m’, ‘LineWidth’, 1);
visboundaries(surroundingTissueMask, ‘Color’, ‘r’, ‘LineWidth’, 1);
visboundaries(phantomRoiMask, ‘Color’, ‘b’, ‘LineWidth’, 1);
viscircles(phantomCenter, phantomRadius, ‘EdgeColor’, ‘c’);
segmentationFile = fullfile(imageFolder, sprintf(‘segmentation_%s.png’, fileTitle));
print(‘-dpng’, segmentationFile, ‘-r600’);Hi everyone,
I am working with MATLAB to generate images that include segmentation lines (using visboundaries and viscircles) drawn over images. However, when I export these images (using saveas or print), the lines are not rendered sharply. Instead, they are much thicker. If I change the LineWidth to something like 0.5 a “halo”/outline effect appears around them. Interestingly, when I zoom into the figure manually within MATLAB and then export, the lines are much sharper.
I already tried a different export format, different dpi (max 1000) and changing the figure position to a higher zoom level.
Any idea on how to improve the export quality?
figure;
imshow(dicomData, [], ‘InitialMagnification’, ‘fit’);
title(sprintf(‘segmentation %s’, fileTitle), ‘Interpreter’, ‘none’);
hold on;
visboundaries(signalRoiMask, ‘Color’, ‘g’, ‘LineWidth’, 1);
visboundaries(lesionMask, ‘Color’, ‘m’, ‘LineWidth’, 1);
visboundaries(surroundingTissueMask, ‘Color’, ‘r’, ‘LineWidth’, 1);
visboundaries(phantomRoiMask, ‘Color’, ‘b’, ‘LineWidth’, 1);
viscircles(phantomCenter, phantomRadius, ‘EdgeColor’, ‘c’);
segmentationFile = fullfile(imageFolder, sprintf(‘segmentation_%s.png’, fileTitle));
print(‘-dpng’, segmentationFile, ‘-r600’); Hi everyone,
I am working with MATLAB to generate images that include segmentation lines (using visboundaries and viscircles) drawn over images. However, when I export these images (using saveas or print), the lines are not rendered sharply. Instead, they are much thicker. If I change the LineWidth to something like 0.5 a “halo”/outline effect appears around them. Interestingly, when I zoom into the figure manually within MATLAB and then export, the lines are much sharper.
I already tried a different export format, different dpi (max 1000) and changing the figure position to a higher zoom level.
Any idea on how to improve the export quality?
figure;
imshow(dicomData, [], ‘InitialMagnification’, ‘fit’);
title(sprintf(‘segmentation %s’, fileTitle), ‘Interpreter’, ‘none’);
hold on;
visboundaries(signalRoiMask, ‘Color’, ‘g’, ‘LineWidth’, 1);
visboundaries(lesionMask, ‘Color’, ‘m’, ‘LineWidth’, 1);
visboundaries(surroundingTissueMask, ‘Color’, ‘r’, ‘LineWidth’, 1);
visboundaries(phantomRoiMask, ‘Color’, ‘b’, ‘LineWidth’, 1);
viscircles(phantomCenter, phantomRadius, ‘EdgeColor’, ‘c’);
segmentationFile = fullfile(imageFolder, sprintf(‘segmentation_%s.png’, fileTitle));
print(‘-dpng’, segmentationFile, ‘-r600’); visboundaries, export quality, matlab MATLAB Answers — New Questions
Cell Style Keeps Reappearing after being Deleted
I’m using Excel under a M365 Home subscription (Version 2408 Build 16.0.17928.20114 64-bit)
The Problem:
Even in brand new, blank workbooks, whenever I delete the default cell styles for “Hyperlink” and “Followed Hyperlink,” these cell styles will reappear and apply themselves on their own the next time a hyperlink is created or followed in the workbook. This occurs whether the hyperlink is created via VBA, cell formula, or the “insert hyperlink” wizard/dialogue.
What I’ve Tried:
1. I have turned off the “AutoFormat As You Type” option to automatically replace “Internet and Network paths with hyperlinks;” the problem persists
2. I have deleted all cell styles (other than the “normal” cell style, which cannot be deleted) in the active workbook and my PERSONAL.xlsb workbook; the problem persists
3. I have used VBA to delete the cell styles (as compared to just right clicking the cell style and selecting “delete”); the problem persists
The Question:
Any idea how to prevent Excel from automatically re-adding the “Hyperlink” and “Followed Hyperlink” cell styles after they’ve been deleted? I want hyperlinks to exhibit NO automatic formatting whatsoever.
I’m using Excel under a M365 Home subscription (Version 2408 Build 16.0.17928.20114 64-bit) The Problem:Even in brand new, blank workbooks, whenever I delete the default cell styles for “Hyperlink” and “Followed Hyperlink,” these cell styles will reappear and apply themselves on their own the next time a hyperlink is created or followed in the workbook. This occurs whether the hyperlink is created via VBA, cell formula, or the “insert hyperlink” wizard/dialogue. What I’ve Tried:1. I have turned off the “AutoFormat As You Type” option to automatically replace “Internet and Network paths with hyperlinks;” the problem persists2. I have deleted all cell styles (other than the “normal” cell style, which cannot be deleted) in the active workbook and my PERSONAL.xlsb workbook; the problem persists3. I have used VBA to delete the cell styles (as compared to just right clicking the cell style and selecting “delete”); the problem persists The Question:Any idea how to prevent Excel from automatically re-adding the “Hyperlink” and “Followed Hyperlink” cell styles after they’ve been deleted? I want hyperlinks to exhibit NO automatic formatting whatsoever. Read More
Basic Matlab App deisnger question regarding the Component Library
Hi,
This is a very basic question but I coudln’t find information regarind my inquery.
I have multiple slider switches on the app designer and each of them has label/name. What I wanted to do is to count the number of slider switches that are on the app, then create the for loop to obtain the slider’s name then store them. Once it is stored then will display on the UITable.
I believe Matlab should have the ability to count them but I couldn’t find a document for it.Hi,
This is a very basic question but I coudln’t find information regarind my inquery.
I have multiple slider switches on the app designer and each of them has label/name. What I wanted to do is to count the number of slider switches that are on the app, then create the for loop to obtain the slider’s name then store them. Once it is stored then will display on the UITable.
I believe Matlab should have the ability to count them but I couldn’t find a document for it. Hi,
This is a very basic question but I coudln’t find information regarind my inquery.
I have multiple slider switches on the app designer and each of them has label/name. What I wanted to do is to count the number of slider switches that are on the app, then create the for loop to obtain the slider’s name then store them. Once it is stored then will display on the UITable.
I believe Matlab should have the ability to count them but I couldn’t find a document for it. appdesigner, matlab MATLAB Answers — New Questions
Microsoft Defender It seriously affected my app launch
My application was written using WPF and published as a standalone project. When my application was launched, Microsoft Defender scanned over 170 files, which caused a delay of up to 9s in my application launch time. I don’t know how to optimize it. Is there anyone who can help me?My process name is op.exe
The fast startup case can only respond quickly in less time if the cache is still available, but this cache is often released and I can’t seem to control it
Here are the logs captured using the Defender Performance Analyzer
My application was written using WPF and published as a standalone project. When my application was launched, Microsoft Defender scanned over 170 files, which caused a delay of up to 9s in my application launch time. I don’t know how to optimize it. Is there anyone who can help me?My process name is op.exe The fast startup case can only respond quickly in less time if the cache is still available, but this cache is often released and I can’t seem to control it Here are the logs captured using the Defender Performance Analyzerhttps://internal-api-drive-stream.feishu.cn/space/api/box/stream/download/all/TtZOb49AEoHJXuxrRqTc9k6Jn0c/?mount_node_token=FI9yddhrTokZthxKYg3cnkgjnaf&mount_point=docx_file Read More
Problem related to GUI deployment
Hello everyone, I am developing a GUI using MATLAB App Designer 2022b for my project, in that i have included two simulink models and a MATLAB code for the result and that is working perfectly fine when i run it in the MATLAB environment. But when i tried to deploy the same as a standalone application, it is throwing error as "File Analysis is Stopped since my model has SoC blockset".
But i didn’t use any SoC blockset for the model, it only has normal To workspace, From Workspace, bit Concat, Data conversion and UDP send block(HDL coder) alone. I didn’t know why it shows such errors because of this i can’t deploy the app now. Somebody please help where did I go wrongHello everyone, I am developing a GUI using MATLAB App Designer 2022b for my project, in that i have included two simulink models and a MATLAB code for the result and that is working perfectly fine when i run it in the MATLAB environment. But when i tried to deploy the same as a standalone application, it is throwing error as "File Analysis is Stopped since my model has SoC blockset".
But i didn’t use any SoC blockset for the model, it only has normal To workspace, From Workspace, bit Concat, Data conversion and UDP send block(HDL coder) alone. I didn’t know why it shows such errors because of this i can’t deploy the app now. Somebody please help where did I go wrong Hello everyone, I am developing a GUI using MATLAB App Designer 2022b for my project, in that i have included two simulink models and a MATLAB code for the result and that is working perfectly fine when i run it in the MATLAB environment. But when i tried to deploy the same as a standalone application, it is throwing error as "File Analysis is Stopped since my model has SoC blockset".
But i didn’t use any SoC blockset for the model, it only has normal To workspace, From Workspace, bit Concat, Data conversion and UDP send block(HDL coder) alone. I didn’t know why it shows such errors because of this i can’t deploy the app now. Somebody please help where did I go wrong app designer, simulink, soc, matlab gui MATLAB Answers — New Questions
Why do I get an “Incorrect data type” error or “Parameter precision loss” warning when I try to tune a parameter with SLRT & Speedgoat?
I am trying to change a Gain parameter during my Simulink Real-Time (SLRT) simulation, but I get the following error when I use "setparam":
>> tg = slrealtime;
>> tg.setparam(‘MyModel/Gain’,’Gain’,-2)
Error using slrealtime.Target/throwErrorWithCause
Unable to set ‘Gain’ parameter value on target computer ‘TargetPC1’: Incorrect data type.
Error in slrealtime.Target/setparam (line 99)
this.throwErrorWithCause(‘slrealtime:target:setparamError’, …
Caused by:
Error using slrealtime.internal.ParameterTuning/setParamWork
Incorrect data type.
When I try changing the parameter in the block mask while using the external mode ("Run on Target"), I see warnings such as the following in the MATLAB prompt:
Warning: Parameter precision loss occurred for ‘Gain’ of ‘MyModel/Gain’. The
original value of the parameter, 1, cannot be represented exactly using the run-time data type
sfix32_En31. The value is quantized to 0.9999999995343387. Quantization error occurred with an absolute
difference of 4.656612873077393e-10 and a relative difference of 4.65661287307739e-08%.
Suggested Actions:
• To disable this warning or error for all parameters in the model, set the ‘Detect precision loss’
option to ‘none’. – Apply
• Inspect details in the Parameter Quantization Advisor. – Open
• – Suppress
> In slrealtime/Instrument/dataAvailableFromObserverViaTarget (line 1413)
In slrealtime.Target/dataAvailableFromObserver (line 66)
In slrealtime.Instrument>@(varargin)tg.dataAvailableFromObserver(varargin{:}) (line 1332)
In slrealtime.internal.instrument.StreamingCallBack.NewData (line 25)I am trying to change a Gain parameter during my Simulink Real-Time (SLRT) simulation, but I get the following error when I use "setparam":
>> tg = slrealtime;
>> tg.setparam(‘MyModel/Gain’,’Gain’,-2)
Error using slrealtime.Target/throwErrorWithCause
Unable to set ‘Gain’ parameter value on target computer ‘TargetPC1’: Incorrect data type.
Error in slrealtime.Target/setparam (line 99)
this.throwErrorWithCause(‘slrealtime:target:setparamError’, …
Caused by:
Error using slrealtime.internal.ParameterTuning/setParamWork
Incorrect data type.
When I try changing the parameter in the block mask while using the external mode ("Run on Target"), I see warnings such as the following in the MATLAB prompt:
Warning: Parameter precision loss occurred for ‘Gain’ of ‘MyModel/Gain’. The
original value of the parameter, 1, cannot be represented exactly using the run-time data type
sfix32_En31. The value is quantized to 0.9999999995343387. Quantization error occurred with an absolute
difference of 4.656612873077393e-10 and a relative difference of 4.65661287307739e-08%.
Suggested Actions:
• To disable this warning or error for all parameters in the model, set the ‘Detect precision loss’
option to ‘none’. – Apply
• Inspect details in the Parameter Quantization Advisor. – Open
• – Suppress
> In slrealtime/Instrument/dataAvailableFromObserverViaTarget (line 1413)
In slrealtime.Target/dataAvailableFromObserver (line 66)
In slrealtime.Instrument>@(varargin)tg.dataAvailableFromObserver(varargin{:}) (line 1332)
In slrealtime.internal.instrument.StreamingCallBack.NewData (line 25) I am trying to change a Gain parameter during my Simulink Real-Time (SLRT) simulation, but I get the following error when I use "setparam":
>> tg = slrealtime;
>> tg.setparam(‘MyModel/Gain’,’Gain’,-2)
Error using slrealtime.Target/throwErrorWithCause
Unable to set ‘Gain’ parameter value on target computer ‘TargetPC1’: Incorrect data type.
Error in slrealtime.Target/setparam (line 99)
this.throwErrorWithCause(‘slrealtime:target:setparamError’, …
Caused by:
Error using slrealtime.internal.ParameterTuning/setParamWork
Incorrect data type.
When I try changing the parameter in the block mask while using the external mode ("Run on Target"), I see warnings such as the following in the MATLAB prompt:
Warning: Parameter precision loss occurred for ‘Gain’ of ‘MyModel/Gain’. The
original value of the parameter, 1, cannot be represented exactly using the run-time data type
sfix32_En31. The value is quantized to 0.9999999995343387. Quantization error occurred with an absolute
difference of 4.656612873077393e-10 and a relative difference of 4.65661287307739e-08%.
Suggested Actions:
• To disable this warning or error for all parameters in the model, set the ‘Detect precision loss’
option to ‘none’. – Apply
• Inspect details in the Parameter Quantization Advisor. – Open
• – Suppress
> In slrealtime/Instrument/dataAvailableFromObserverViaTarget (line 1413)
In slrealtime.Target/dataAvailableFromObserver (line 66)
In slrealtime.Instrument>@(varargin)tg.dataAvailableFromObserver(varargin{:}) (line 1332)
In slrealtime.internal.instrument.StreamingCallBack.NewData (line 25) slrt, setparam, getparam MATLAB Answers — New Questions
Trying to use a spill range as a reference for FILTER that uses INDEX
Hi all! 👋😊
I am trying to find a solution that will let me use the values in a spill range to query a table and return related values from another column. I attempted to do this using this formula: FILTER(INDEX(Table1,,7),INDEX(Table1,,9)=$F3#,””) – where $F3# is the spill range, its values are in column 9 of Table1 and the required value is in column 7 of the same table. The formula results in an error and I was unable to resolve it to a working state.
Instead, I went for a clunky but simple query that references a bunch of rows where the spill will occur. It fetches the values that I need but is not dynamic… ideally the solution would expand and contract with the spill range. I’m sure it’s possible, but just beyond the reach of my current skill set or knowledge so created a sample workbook with dummy data, hoping it might help someone suggest a more elegant solution 🤞
Thanks in advance, Andy!
Hi all! 👋😊 I am trying to find a solution that will let me use the values in a spill range to query a table and return related values from another column. I attempted to do this using this formula: FILTER(INDEX(Table1,,7),INDEX(Table1,,9)=$F3#,””) – where $F3# is the spill range, its values are in column 9 of Table1 and the required value is in column 7 of the same table. The formula results in an error and I was unable to resolve it to a working state. Instead, I went for a clunky but simple query that references a bunch of rows where the spill will occur. It fetches the values that I need but is not dynamic… ideally the solution would expand and contract with the spill range. I’m sure it’s possible, but just beyond the reach of my current skill set or knowledge so created a sample workbook with dummy data, hoping it might help someone suggest a more elegant solution 🤞 Thanks in advance, Andy! Read More
How to rotate video view by 90 or 180 degrees before joining a Teams Meeting
Dear all,
We are currently working on an Electron application that integrates Microsoft Teams using Azure Communication Services. We are facing an issue with webcams that are physically installed rotated by 90 or 180 degrees. so we need to rotate the video view before joining a Teams call.
Does anyone know if there’s a video settings API in ACS or another method to rotate the video before we call callAgent.join method in ACS to join a Teams meeting? any code snippets or resources would be greatly appreciated.
Thank you in advance for your help!
Sincerely,
James from Shared Studios
Dear all,We are currently working on an Electron application that integrates Microsoft Teams using Azure Communication Services. We are facing an issue with webcams that are physically installed rotated by 90 or 180 degrees. so we need to rotate the video view before joining a Teams call.Does anyone know if there’s a video settings API in ACS or another method to rotate the video before we call callAgent.join method in ACS to join a Teams meeting? any code snippets or resources would be greatly appreciated.Thank you in advance for your help!Sincerely,James from Shared Studios Read More
Difficulties with inserting a table int oWord
insert a table, click Insert > Table and move the cursor over the grid until you highlight the number of columns and rows you want. This does not work on my computer anymore. Any suggestions? I’m working on a Mac with MS 365 OS Sonoma
insert a table, click Insert > Table and move the cursor over the grid until you highlight the number of columns and rows you want. This does not work on my computer anymore. Any suggestions? I’m working on a Mac with MS 365 OS Sonoma Read More
Problem with Power system onramp course in simulink
you can see the error what can I do. all connection are ok.you can see the error what can I do. all connection are ok. you can see the error what can I do. all connection are ok. matlab simulation power system onramp course MATLAB Answers — New Questions
What is the ratio of area of the flame between the last frame and the first? What is wrong with my approach? I am getting an incorrect answer upon submission.
Question 3 Create a mask for each frame of this video that isolates the nearly-white flame exiting the rocket. Do this by converting each frame to grayscale. Then label all pixels with intensities less than or equal to 245 as false, and all pixels with intensities greater than 245 as true.
What is the ratio of area of the flame between the last frame and the first? (Use the number of true pixels for area.)
% Load the video file ‘shuttle.avi’
videoFile = ‘shuttle.avi’;
v = VideoReader(videoFile);
% Read the first frame
firstFrame = readFrame(v);
% Move to the last frame
while hasFrame(v)
lastFrame = readFrame(v);
end
% Convert both frames to grayscale
firstGray = rgb2gray(firstFrame);
lastGray = rgb2gray(lastFrame);
% Create masks where pixel intensities > 245 are true, the rest are false
firstMask = firstGray > 245;
lastMask = lastGray > 245;
% Calculate the flame area (number of ‘true’ pixels) for both frames
areaFirst = sum(firstMask(:));
areaLast = sum(lastMask(:));
% Calculate the ratio of the flame area between the last and the first frame
if areaFirst == 0
error(‘No flame detected in the first frame.’);
else
ratio = areaLast / areaFirst;
end
% Display the results
fprintf(‘Area of the flame in the first frame: %d pixelsn’, areaFirst);
fprintf(‘Area of the flame in the last frame: %d pixelsn’, areaLast);
fprintf(‘Ratio of flame area (last frame / first frame): %.2fn’, ratio);
% Optional: Display the original frames and the masks for visual verification
figure;
subplot(2,2,1), imshow(firstFrame), title(‘First Frame’);
subplot(2,2,2), imshow(lastFrame), title(‘Last Frame’);
subplot(2,2,3), imshow(firstMask), title(‘First Frame Mask’);
subplot(2,2,4), imshow(lastMask), title(‘Last Frame Mask’);Question 3 Create a mask for each frame of this video that isolates the nearly-white flame exiting the rocket. Do this by converting each frame to grayscale. Then label all pixels with intensities less than or equal to 245 as false, and all pixels with intensities greater than 245 as true.
What is the ratio of area of the flame between the last frame and the first? (Use the number of true pixels for area.)
% Load the video file ‘shuttle.avi’
videoFile = ‘shuttle.avi’;
v = VideoReader(videoFile);
% Read the first frame
firstFrame = readFrame(v);
% Move to the last frame
while hasFrame(v)
lastFrame = readFrame(v);
end
% Convert both frames to grayscale
firstGray = rgb2gray(firstFrame);
lastGray = rgb2gray(lastFrame);
% Create masks where pixel intensities > 245 are true, the rest are false
firstMask = firstGray > 245;
lastMask = lastGray > 245;
% Calculate the flame area (number of ‘true’ pixels) for both frames
areaFirst = sum(firstMask(:));
areaLast = sum(lastMask(:));
% Calculate the ratio of the flame area between the last and the first frame
if areaFirst == 0
error(‘No flame detected in the first frame.’);
else
ratio = areaLast / areaFirst;
end
% Display the results
fprintf(‘Area of the flame in the first frame: %d pixelsn’, areaFirst);
fprintf(‘Area of the flame in the last frame: %d pixelsn’, areaLast);
fprintf(‘Ratio of flame area (last frame / first frame): %.2fn’, ratio);
% Optional: Display the original frames and the masks for visual verification
figure;
subplot(2,2,1), imshow(firstFrame), title(‘First Frame’);
subplot(2,2,2), imshow(lastFrame), title(‘Last Frame’);
subplot(2,2,3), imshow(firstMask), title(‘First Frame Mask’);
subplot(2,2,4), imshow(lastMask), title(‘Last Frame Mask’); Question 3 Create a mask for each frame of this video that isolates the nearly-white flame exiting the rocket. Do this by converting each frame to grayscale. Then label all pixels with intensities less than or equal to 245 as false, and all pixels with intensities greater than 245 as true.
What is the ratio of area of the flame between the last frame and the first? (Use the number of true pixels for area.)
% Load the video file ‘shuttle.avi’
videoFile = ‘shuttle.avi’;
v = VideoReader(videoFile);
% Read the first frame
firstFrame = readFrame(v);
% Move to the last frame
while hasFrame(v)
lastFrame = readFrame(v);
end
% Convert both frames to grayscale
firstGray = rgb2gray(firstFrame);
lastGray = rgb2gray(lastFrame);
% Create masks where pixel intensities > 245 are true, the rest are false
firstMask = firstGray > 245;
lastMask = lastGray > 245;
% Calculate the flame area (number of ‘true’ pixels) for both frames
areaFirst = sum(firstMask(:));
areaLast = sum(lastMask(:));
% Calculate the ratio of the flame area between the last and the first frame
if areaFirst == 0
error(‘No flame detected in the first frame.’);
else
ratio = areaLast / areaFirst;
end
% Display the results
fprintf(‘Area of the flame in the first frame: %d pixelsn’, areaFirst);
fprintf(‘Area of the flame in the last frame: %d pixelsn’, areaLast);
fprintf(‘Ratio of flame area (last frame / first frame): %.2fn’, ratio);
% Optional: Display the original frames and the masks for visual verification
figure;
subplot(2,2,1), imshow(firstFrame), title(‘First Frame’);
subplot(2,2,2), imshow(lastFrame), title(‘Last Frame’);
subplot(2,2,3), imshow(firstMask), title(‘First Frame Mask’);
subplot(2,2,4), imshow(lastMask), title(‘Last Frame Mask’); image processing MATLAB Answers — New Questions
Excel formula for adding correct exchange rate to correct cell
Hello,
May I ask for help with this please.
I am running a web store, and in columns A-C (marked as 1) you can see parts of the sales report (see screenshot).
In column D, I wish to automatically insert the correct currency exchange rate for the Purchase Date (column B) and for the currency that was used to pay the order (column C).
Columns F-H and J-L (marked as 2 and 3) contains the exchange rates that should be used for Euro and USD.
So to get the correct currency exchange rates into the different rows of column D, the formula needs to:
-check that the order date (column B) is the same as the date in column F or J.
-check that the order currency (column C) is the same as the currency in column G or K.
For example:
-In cell D2, the correct currency exchange rate to be inserted is 10,35498 (from cell L10), because the order date (column B) is 2024-09-11 and the currency (column C) is USD.
Thank you!
Hello, May I ask for help with this please. I am running a web store, and in columns A-C (marked as 1) you can see parts of the sales report (see screenshot). In column D, I wish to automatically insert the correct currency exchange rate for the Purchase Date (column B) and for the currency that was used to pay the order (column C). Columns F-H and J-L (marked as 2 and 3) contains the exchange rates that should be used for Euro and USD. So to get the correct currency exchange rates into the different rows of column D, the formula needs to:-check that the order date (column B) is the same as the date in column F or J.-check that the order currency (column C) is the same as the currency in column G or K. For example:-In cell D2, the correct currency exchange rate to be inserted is 10,35498 (from cell L10), because the order date (column B) is 2024-09-11 and the currency (column C) is USD. Thank you! Read More
How to know what version of MKL is MATLAB using
Hi:
I am using MATLAB R2010b. I would like to know the version (I think there is a command but I don’t remember it) to know what version of MKL (Math Kernel Library) is MATLAB using.
Thank you very muchHi:
I am using MATLAB R2010b. I would like to know the version (I think there is a command but I don’t remember it) to know what version of MKL (Math Kernel Library) is MATLAB using.
Thank you very much Hi:
I am using MATLAB R2010b. I would like to know the version (I think there is a command but I don’t remember it) to know what version of MKL (Math Kernel Library) is MATLAB using.
Thank you very much mkl matlab MATLAB Answers — New Questions
Creating a Code to determine Lift Curve Slope
For an Aerodynamics couse, we need to create a code that computes lifting surfaces (wing) aerodynamics. I cannot get the graph to display a nice CL vs AoA curve, but only a single value. I don’t know how I can accomplish this. As I am a novice to MAtlab, I would appreciate some pointers or hints. Thank you.
clc;
% Default airfoil or not…
Default_AF = 0;
% A/F Characteristics:
% Lift coefficient [1/rad]:
Cl_alpha = 5.79;
Cl_alphaInRadians = deg2rad(Cl_alpha);
% Sectional lift curve slope [deg]:
alpha_0 = -2.0;
% Pitching moment [1/rad]:
Cm_alpha = 0;
Cm_alphaInRadians = deg2rad(Cm_alpha);
% 2D Pitching moment:
Cm_0 = -0.025;
% Coefficient in series expansion of circulation distribution [deg]:
alpha_nl = 8;
% Wing planform Geometry [inches]:
% [root-LE,root-TE,tip-LE,tip-TE]
x1 = 0;
y1 = 0;
x2 = 200;
y2 = 0;
x3 = 0;
y3 = 1000;
x4 = 200;
y4 = 1000;
% Wing twist angle [deg]:
theta_t = 0;
% Number of spanwise coefficients:
N = 100;
% Flight Conditions:
% Free-stream Velocity [ft/sec]
V = 100;
% Density [slugs/ft^3]:
rho = 0.002344;
% Viscous Force [lb.s/ft^2]
mu = 0.0000003737;
% Angle of Attack [deg]
alpha = 5;
% Wing span:
b = sqrt((x2-x1)^2 + (y2-y1)^2);
% Wing chord:
c = sqrt((x3-x1)^2 + (y3-y1)^2);
% Wing area:
S = b*c;
% Wing semi-span:
s = b/2;
% Aspect Ratio:
AR = b^2./S;
% Applying segment length of the wings:
alpha_segment = zeros(1,N);
theta_segment = zeros(1,N);
% Taper Ratio and its range within the wing (which is 0 to 1):
for lambda_r = 0:0.25:1
% Root Chord:
c_root = (2*S) / ((1+lambda_r)*b);
% Tip Chord:
c_tip = ((2*S)/((1+lambda_r)*b)) * (1-((2*(1-lambda_r))/b)*(b/2));
% Mean Aerodynamic Chord:
MAC = (2/3)*(c_root+c_tip-(c_root*c_tip)/(c_root+c_tip));
% Taper ratio:
lambda = c_tip / c_root;
% Providing segment limitation within range:
alpha_segment(1) = alpha;
theta_segment(1) = pi/2;
% Completing the Lifting Line Theory to determine the
% matrix value of the segments:
for N = 2:N
c(N) = c_root+(c_tip-c_root)/N.*N;
alpha_segment(N) = alpha+(theta_t)/N.*N;
theta_segment = pi/(2*N):pi/(2*N):pi/2;
end
% Lifting line theory construction:
xb = 4*b./(pi*c);
% Completing the [B] matrix:
for i = 1:N
for j = 1:N
B(i,j) = (sin(j.*theta_segment(i))).*(xb(i)+j/(sin(theta_segment(i))));
end
slope(i) = (alpha_segment(i)-alpha_0)*(pi/180);
end
A = Btranspose(slope);
end
% Leading edge sweep angle
for fai = 1:N
delta_LE(fai) = fai*(A(fai)/A(1))^2; %#ok<*SAGROW>
end
% Section Lift Coefficient of Airfoil
cl = 0.5*cos(pi/b);
% Wing Lift Coefficient:
CL = pi*AR*A(1);
% Span Efficiency:
delta = sum(delta_LE);
CD_0 = 1/(1+delta);
% Induced drag coefficient:
CD_i = CL.^2 / (pi*CD_0*AR);
% Speed of sound (assuming 20 degree dry air) [ft/sec]:
C = 1125.33;
% Mach Number:
M = V / C;
% Dynamic Pressure:
q = (0.5*rho*V^2);
% Pitching Moment Coefficient:
CM = M / q*S*c;
% Subsonic Lift:
alpha_inf = 2*pi*cos(delta_LE);
% 3D Lift Curve Slope of airfoil:
CL_alpha = 2*pi*A;
% Geometric Angle of Attack of Wing:
alpha = (alpha_inf)/(1+(alpha_inf)/(pi*AR));
%———————————————————-
% Wing lift coefficient (CL) vs Angle of Attack (alpha):
figure(1);
plot(alpha,CL,’-o’)
grid on
title(‘Wing lift coefficient (CL) vs Angle of Attack (alpha)’)
ylabel(‘Wing Lift Coefficient, CL’)
xlabel(‘Angle of Attack, alpha [deg]’)
% Pitching moment coefficient(CM) vs Angle of Attack (alpha):
figure(2);
plot(alpha,CM,’-o’)
grid on
title(‘Pitching moment coefficient(CM) vs Angle of Attack (alpha)’)
ylabel(‘Pitching Moment Coefficient, CM’)
xlabel(‘Angle of Attack, alpha [deg]’)
% Wing lift coefficient (CL) vs Induced drag coefficient (CD_i):
figure(3);
plot(CD_i,CL,’-o’)
grid on
title(‘Wing lift coefficient (CL) vs Induced drag coefficient (CD_i)’)
ylabel(‘Wing Lift Coefficient, CL’)
xlabel(‘Induced Drag Coefficient, CD_i’)For an Aerodynamics couse, we need to create a code that computes lifting surfaces (wing) aerodynamics. I cannot get the graph to display a nice CL vs AoA curve, but only a single value. I don’t know how I can accomplish this. As I am a novice to MAtlab, I would appreciate some pointers or hints. Thank you.
clc;
% Default airfoil or not…
Default_AF = 0;
% A/F Characteristics:
% Lift coefficient [1/rad]:
Cl_alpha = 5.79;
Cl_alphaInRadians = deg2rad(Cl_alpha);
% Sectional lift curve slope [deg]:
alpha_0 = -2.0;
% Pitching moment [1/rad]:
Cm_alpha = 0;
Cm_alphaInRadians = deg2rad(Cm_alpha);
% 2D Pitching moment:
Cm_0 = -0.025;
% Coefficient in series expansion of circulation distribution [deg]:
alpha_nl = 8;
% Wing planform Geometry [inches]:
% [root-LE,root-TE,tip-LE,tip-TE]
x1 = 0;
y1 = 0;
x2 = 200;
y2 = 0;
x3 = 0;
y3 = 1000;
x4 = 200;
y4 = 1000;
% Wing twist angle [deg]:
theta_t = 0;
% Number of spanwise coefficients:
N = 100;
% Flight Conditions:
% Free-stream Velocity [ft/sec]
V = 100;
% Density [slugs/ft^3]:
rho = 0.002344;
% Viscous Force [lb.s/ft^2]
mu = 0.0000003737;
% Angle of Attack [deg]
alpha = 5;
% Wing span:
b = sqrt((x2-x1)^2 + (y2-y1)^2);
% Wing chord:
c = sqrt((x3-x1)^2 + (y3-y1)^2);
% Wing area:
S = b*c;
% Wing semi-span:
s = b/2;
% Aspect Ratio:
AR = b^2./S;
% Applying segment length of the wings:
alpha_segment = zeros(1,N);
theta_segment = zeros(1,N);
% Taper Ratio and its range within the wing (which is 0 to 1):
for lambda_r = 0:0.25:1
% Root Chord:
c_root = (2*S) / ((1+lambda_r)*b);
% Tip Chord:
c_tip = ((2*S)/((1+lambda_r)*b)) * (1-((2*(1-lambda_r))/b)*(b/2));
% Mean Aerodynamic Chord:
MAC = (2/3)*(c_root+c_tip-(c_root*c_tip)/(c_root+c_tip));
% Taper ratio:
lambda = c_tip / c_root;
% Providing segment limitation within range:
alpha_segment(1) = alpha;
theta_segment(1) = pi/2;
% Completing the Lifting Line Theory to determine the
% matrix value of the segments:
for N = 2:N
c(N) = c_root+(c_tip-c_root)/N.*N;
alpha_segment(N) = alpha+(theta_t)/N.*N;
theta_segment = pi/(2*N):pi/(2*N):pi/2;
end
% Lifting line theory construction:
xb = 4*b./(pi*c);
% Completing the [B] matrix:
for i = 1:N
for j = 1:N
B(i,j) = (sin(j.*theta_segment(i))).*(xb(i)+j/(sin(theta_segment(i))));
end
slope(i) = (alpha_segment(i)-alpha_0)*(pi/180);
end
A = Btranspose(slope);
end
% Leading edge sweep angle
for fai = 1:N
delta_LE(fai) = fai*(A(fai)/A(1))^2; %#ok<*SAGROW>
end
% Section Lift Coefficient of Airfoil
cl = 0.5*cos(pi/b);
% Wing Lift Coefficient:
CL = pi*AR*A(1);
% Span Efficiency:
delta = sum(delta_LE);
CD_0 = 1/(1+delta);
% Induced drag coefficient:
CD_i = CL.^2 / (pi*CD_0*AR);
% Speed of sound (assuming 20 degree dry air) [ft/sec]:
C = 1125.33;
% Mach Number:
M = V / C;
% Dynamic Pressure:
q = (0.5*rho*V^2);
% Pitching Moment Coefficient:
CM = M / q*S*c;
% Subsonic Lift:
alpha_inf = 2*pi*cos(delta_LE);
% 3D Lift Curve Slope of airfoil:
CL_alpha = 2*pi*A;
% Geometric Angle of Attack of Wing:
alpha = (alpha_inf)/(1+(alpha_inf)/(pi*AR));
%———————————————————-
% Wing lift coefficient (CL) vs Angle of Attack (alpha):
figure(1);
plot(alpha,CL,’-o’)
grid on
title(‘Wing lift coefficient (CL) vs Angle of Attack (alpha)’)
ylabel(‘Wing Lift Coefficient, CL’)
xlabel(‘Angle of Attack, alpha [deg]’)
% Pitching moment coefficient(CM) vs Angle of Attack (alpha):
figure(2);
plot(alpha,CM,’-o’)
grid on
title(‘Pitching moment coefficient(CM) vs Angle of Attack (alpha)’)
ylabel(‘Pitching Moment Coefficient, CM’)
xlabel(‘Angle of Attack, alpha [deg]’)
% Wing lift coefficient (CL) vs Induced drag coefficient (CD_i):
figure(3);
plot(CD_i,CL,’-o’)
grid on
title(‘Wing lift coefficient (CL) vs Induced drag coefficient (CD_i)’)
ylabel(‘Wing Lift Coefficient, CL’)
xlabel(‘Induced Drag Coefficient, CD_i’) For an Aerodynamics couse, we need to create a code that computes lifting surfaces (wing) aerodynamics. I cannot get the graph to display a nice CL vs AoA curve, but only a single value. I don’t know how I can accomplish this. As I am a novice to MAtlab, I would appreciate some pointers or hints. Thank you.
clc;
% Default airfoil or not…
Default_AF = 0;
% A/F Characteristics:
% Lift coefficient [1/rad]:
Cl_alpha = 5.79;
Cl_alphaInRadians = deg2rad(Cl_alpha);
% Sectional lift curve slope [deg]:
alpha_0 = -2.0;
% Pitching moment [1/rad]:
Cm_alpha = 0;
Cm_alphaInRadians = deg2rad(Cm_alpha);
% 2D Pitching moment:
Cm_0 = -0.025;
% Coefficient in series expansion of circulation distribution [deg]:
alpha_nl = 8;
% Wing planform Geometry [inches]:
% [root-LE,root-TE,tip-LE,tip-TE]
x1 = 0;
y1 = 0;
x2 = 200;
y2 = 0;
x3 = 0;
y3 = 1000;
x4 = 200;
y4 = 1000;
% Wing twist angle [deg]:
theta_t = 0;
% Number of spanwise coefficients:
N = 100;
% Flight Conditions:
% Free-stream Velocity [ft/sec]
V = 100;
% Density [slugs/ft^3]:
rho = 0.002344;
% Viscous Force [lb.s/ft^2]
mu = 0.0000003737;
% Angle of Attack [deg]
alpha = 5;
% Wing span:
b = sqrt((x2-x1)^2 + (y2-y1)^2);
% Wing chord:
c = sqrt((x3-x1)^2 + (y3-y1)^2);
% Wing area:
S = b*c;
% Wing semi-span:
s = b/2;
% Aspect Ratio:
AR = b^2./S;
% Applying segment length of the wings:
alpha_segment = zeros(1,N);
theta_segment = zeros(1,N);
% Taper Ratio and its range within the wing (which is 0 to 1):
for lambda_r = 0:0.25:1
% Root Chord:
c_root = (2*S) / ((1+lambda_r)*b);
% Tip Chord:
c_tip = ((2*S)/((1+lambda_r)*b)) * (1-((2*(1-lambda_r))/b)*(b/2));
% Mean Aerodynamic Chord:
MAC = (2/3)*(c_root+c_tip-(c_root*c_tip)/(c_root+c_tip));
% Taper ratio:
lambda = c_tip / c_root;
% Providing segment limitation within range:
alpha_segment(1) = alpha;
theta_segment(1) = pi/2;
% Completing the Lifting Line Theory to determine the
% matrix value of the segments:
for N = 2:N
c(N) = c_root+(c_tip-c_root)/N.*N;
alpha_segment(N) = alpha+(theta_t)/N.*N;
theta_segment = pi/(2*N):pi/(2*N):pi/2;
end
% Lifting line theory construction:
xb = 4*b./(pi*c);
% Completing the [B] matrix:
for i = 1:N
for j = 1:N
B(i,j) = (sin(j.*theta_segment(i))).*(xb(i)+j/(sin(theta_segment(i))));
end
slope(i) = (alpha_segment(i)-alpha_0)*(pi/180);
end
A = Btranspose(slope);
end
% Leading edge sweep angle
for fai = 1:N
delta_LE(fai) = fai*(A(fai)/A(1))^2; %#ok<*SAGROW>
end
% Section Lift Coefficient of Airfoil
cl = 0.5*cos(pi/b);
% Wing Lift Coefficient:
CL = pi*AR*A(1);
% Span Efficiency:
delta = sum(delta_LE);
CD_0 = 1/(1+delta);
% Induced drag coefficient:
CD_i = CL.^2 / (pi*CD_0*AR);
% Speed of sound (assuming 20 degree dry air) [ft/sec]:
C = 1125.33;
% Mach Number:
M = V / C;
% Dynamic Pressure:
q = (0.5*rho*V^2);
% Pitching Moment Coefficient:
CM = M / q*S*c;
% Subsonic Lift:
alpha_inf = 2*pi*cos(delta_LE);
% 3D Lift Curve Slope of airfoil:
CL_alpha = 2*pi*A;
% Geometric Angle of Attack of Wing:
alpha = (alpha_inf)/(1+(alpha_inf)/(pi*AR));
%———————————————————-
% Wing lift coefficient (CL) vs Angle of Attack (alpha):
figure(1);
plot(alpha,CL,’-o’)
grid on
title(‘Wing lift coefficient (CL) vs Angle of Attack (alpha)’)
ylabel(‘Wing Lift Coefficient, CL’)
xlabel(‘Angle of Attack, alpha [deg]’)
% Pitching moment coefficient(CM) vs Angle of Attack (alpha):
figure(2);
plot(alpha,CM,’-o’)
grid on
title(‘Pitching moment coefficient(CM) vs Angle of Attack (alpha)’)
ylabel(‘Pitching Moment Coefficient, CM’)
xlabel(‘Angle of Attack, alpha [deg]’)
% Wing lift coefficient (CL) vs Induced drag coefficient (CD_i):
figure(3);
plot(CD_i,CL,’-o’)
grid on
title(‘Wing lift coefficient (CL) vs Induced drag coefficient (CD_i)’)
ylabel(‘Wing Lift Coefficient, CL’)
xlabel(‘Induced Drag Coefficient, CD_i’) aerodynamics, lifting surfaces MATLAB Answers — New Questions
4. f(x)=x^2/3(3-x^2)(x-4). how do i enter this function in matlab.
When I input the above function as x^(2/3)*(3-x^2)*(x-4) in a code where i have to find extrema , maxima and critical points for a given function , i am getting error which says
Warning: Solutions are parameterized by the symbols: z2. To include parameters and conditions in the solution, specify the ‘ReturnConditions’
value as ‘true’.
Error using mupadengine/feval2char
Unable to convert expression containing symbolic variables into double array. Apply ‘subs’ function first to substitute values for variables.
Error in sym/double (line 755)
Xstr = feval2char(symengine, "symobj::double", S);
however the same cose is working if I input some other functionWhen I input the above function as x^(2/3)*(3-x^2)*(x-4) in a code where i have to find extrema , maxima and critical points for a given function , i am getting error which says
Warning: Solutions are parameterized by the symbols: z2. To include parameters and conditions in the solution, specify the ‘ReturnConditions’
value as ‘true’.
Error using mupadengine/feval2char
Unable to convert expression containing symbolic variables into double array. Apply ‘subs’ function first to substitute values for variables.
Error in sym/double (line 755)
Xstr = feval2char(symengine, "symobj::double", S);
however the same cose is working if I input some other function When I input the above function as x^(2/3)*(3-x^2)*(x-4) in a code where i have to find extrema , maxima and critical points for a given function , i am getting error which says
Warning: Solutions are parameterized by the symbols: z2. To include parameters and conditions in the solution, specify the ‘ReturnConditions’
value as ‘true’.
Error using mupadengine/feval2char
Unable to convert expression containing symbolic variables into double array. Apply ‘subs’ function first to substitute values for variables.
Error in sym/double (line 755)
Xstr = feval2char(symengine, "symobj::double", S);
however the same cose is working if I input some other function please do clear this problem MATLAB Answers — New Questions
