Month: September 2024
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
Why do I get a blank SSO screen when attempting to sign in to MATLAB at start up?
I was able to install MATLAB, however I am not able to sign into my MathWorks Account with my university credentials when trying to launch MATLAB for the first time.
When I input my email address it says I must log in through my school’s portal, but nothing pops up except a blank white page in my shortcut.
I was able to install MATLAB, however I am not able to sign into my MathWorks Account with my university credentials when trying to launch MATLAB for the first time.
When I input my email address it says I must log in through my school’s portal, but nothing pops up except a blank white page in my shortcut.
I was able to install MATLAB, however I am not able to sign into my MathWorks Account with my university credentials when trying to launch MATLAB for the first time.
When I input my email address it says I must log in through my school’s portal, but nothing pops up except a blank white page in my shortcut.
MATLAB Answers — New Questions
Determine the direction of travelling waves in Fourier Analysis
% I am conducting a FFT analysis and i I observed that there is travelling
% wave. Please, how do I determine the direction of the travelling waves?
% Compute the phase of the FFT: theta_phase = angle(Ytheta);
% Compute the mean phase difference: p = polyfit(f, theta_phase, 1);
% slope = p(1); % The slope of the phase vs. frequency plot
% Store the mean phase difference: mean_phase_diff(i) = slope;
% Then I test the mean_phase_diff(i) > 0 implies rightward direction or if
% mean_phase_diff(i) < 0 leftward direction. I am wondering if there is a
% better way or function to do this.
clear
%close all
pars.W = 20e-6;
pars.D = 2e-6;
% time discretisation – start, step and end
t = 0:0.025:5;
% Extract theta data
loaded_data = load(‘thetam.mat’);
thetam = loaded_data.thetam;
% Sample frequency
Fs = 1/(t(2) – t(1));
% Number of samples
L = length(t);
% Number of ramp slopes
num_ramp_slopes = size(thetam, 1);
% Frequency vector for FFT
f = (-L/2 : L/2-1) * (Fs / L);
% Loop through each ramp_slope
for i = 1:num_ramp_slopes
% Extract the theta data for the current ramp_slope
theta_data = thetam(i, :);
% Compute the FFT of the theta data
Ytheta = fft(theta_data);
% Shift zero frequency component to center
Ytheta = fftshift(Ytheta);
end
% Plot the magnitude of the FFT for the first ramp_slope
fig1 = figure;
plot(f, abs(fftshift(fft(thetam(1, :)))), ‘LineWidth’, 0.8);
xlabel(‘Frequency (Hz)’);
ylabel(‘Magnitude’);
title(‘FFT Magnitude for Ramp Slope 1’);
xlim([-Fs/2 Fs/2]);
grid on;% I am conducting a FFT analysis and i I observed that there is travelling
% wave. Please, how do I determine the direction of the travelling waves?
% Compute the phase of the FFT: theta_phase = angle(Ytheta);
% Compute the mean phase difference: p = polyfit(f, theta_phase, 1);
% slope = p(1); % The slope of the phase vs. frequency plot
% Store the mean phase difference: mean_phase_diff(i) = slope;
% Then I test the mean_phase_diff(i) > 0 implies rightward direction or if
% mean_phase_diff(i) < 0 leftward direction. I am wondering if there is a
% better way or function to do this.
clear
%close all
pars.W = 20e-6;
pars.D = 2e-6;
% time discretisation – start, step and end
t = 0:0.025:5;
% Extract theta data
loaded_data = load(‘thetam.mat’);
thetam = loaded_data.thetam;
% Sample frequency
Fs = 1/(t(2) – t(1));
% Number of samples
L = length(t);
% Number of ramp slopes
num_ramp_slopes = size(thetam, 1);
% Frequency vector for FFT
f = (-L/2 : L/2-1) * (Fs / L);
% Loop through each ramp_slope
for i = 1:num_ramp_slopes
% Extract the theta data for the current ramp_slope
theta_data = thetam(i, :);
% Compute the FFT of the theta data
Ytheta = fft(theta_data);
% Shift zero frequency component to center
Ytheta = fftshift(Ytheta);
end
% Plot the magnitude of the FFT for the first ramp_slope
fig1 = figure;
plot(f, abs(fftshift(fft(thetam(1, :)))), ‘LineWidth’, 0.8);
xlabel(‘Frequency (Hz)’);
ylabel(‘Magnitude’);
title(‘FFT Magnitude for Ramp Slope 1’);
xlim([-Fs/2 Fs/2]);
grid on; % I am conducting a FFT analysis and i I observed that there is travelling
% wave. Please, how do I determine the direction of the travelling waves?
% Compute the phase of the FFT: theta_phase = angle(Ytheta);
% Compute the mean phase difference: p = polyfit(f, theta_phase, 1);
% slope = p(1); % The slope of the phase vs. frequency plot
% Store the mean phase difference: mean_phase_diff(i) = slope;
% Then I test the mean_phase_diff(i) > 0 implies rightward direction or if
% mean_phase_diff(i) < 0 leftward direction. I am wondering if there is a
% better way or function to do this.
clear
%close all
pars.W = 20e-6;
pars.D = 2e-6;
% time discretisation – start, step and end
t = 0:0.025:5;
% Extract theta data
loaded_data = load(‘thetam.mat’);
thetam = loaded_data.thetam;
% Sample frequency
Fs = 1/(t(2) – t(1));
% Number of samples
L = length(t);
% Number of ramp slopes
num_ramp_slopes = size(thetam, 1);
% Frequency vector for FFT
f = (-L/2 : L/2-1) * (Fs / L);
% Loop through each ramp_slope
for i = 1:num_ramp_slopes
% Extract the theta data for the current ramp_slope
theta_data = thetam(i, :);
% Compute the FFT of the theta data
Ytheta = fft(theta_data);
% Shift zero frequency component to center
Ytheta = fftshift(Ytheta);
end
% Plot the magnitude of the FFT for the first ramp_slope
fig1 = figure;
plot(f, abs(fftshift(fft(thetam(1, :)))), ‘LineWidth’, 0.8);
xlabel(‘Frequency (Hz)’);
ylabel(‘Magnitude’);
title(‘FFT Magnitude for Ramp Slope 1’);
xlim([-Fs/2 Fs/2]);
grid on; wave direction, fourier series, fft MATLAB Answers — New Questions
how can I take Dynamic Voltage Restorer Block from library browser in matlab simulink ?
I am searching the Dynamic Voltage Restorer (DVR) block in library browser but I am not getting the block.please provide me the steps to find out the DVR block from library browser in matlab simulink.I am searching the Dynamic Voltage Restorer (DVR) block in library browser but I am not getting the block.please provide me the steps to find out the DVR block from library browser in matlab simulink. I am searching the Dynamic Voltage Restorer (DVR) block in library browser but I am not getting the block.please provide me the steps to find out the DVR block from library browser in matlab simulink. dvr MATLAB Answers — New Questions
How do I find my windows 11 product key?
I recently needed to find my Windows 11 product key because I wanted to reinstall the system, but I didn’t know where to find Windows 11 product key. I’ve seen some tutorials before, but the operation was a bit complicated and I didn’t know the specific steps. Does anyone have any simple methods or tools that can help me quickly find the Windows 11 product key? If anyone has encountered a similar problem, please share your experience, thank you!
I recently needed to find my Windows 11 product key because I wanted to reinstall the system, but I didn’t know where to find Windows 11 product key. I’ve seen some tutorials before, but the operation was a bit complicated and I didn’t know the specific steps. Does anyone have any simple methods or tools that can help me quickly find the Windows 11 product key? If anyone has encountered a similar problem, please share your experience, thank you! Read More
Is a complete wipe really necessary?
Insider build expiring very soon, but updates constantly fail to install, is a complete wipe really necessary?
Insider build expiring very soon, but updates constantly fail to install, is a complete wipe really necessary? Read More
I can’t exit Windows Insider Program
What should i do if I can’t exit Windows Insider Program?
What should i do if I can’t exit Windows Insider Program? Read More
how to fuse two png images with equal tranparency and with proper positioning in the final image?
Hello there,
I need to mix two pictures in a way so that one is placed over the other. But both should have equal transparency. Also the location of the first picture over the second should be determinable. is there any way we can do this using imfuse or any other function in MATLAB? whenevr I use this script one gets faded and is located in one of the corners which are not desirable. Can we fix this?Hello there,
I need to mix two pictures in a way so that one is placed over the other. But both should have equal transparency. Also the location of the first picture over the second should be determinable. is there any way we can do this using imfuse or any other function in MATLAB? whenevr I use this script one gets faded and is located in one of the corners which are not desirable. Can we fix this? Hello there,
I need to mix two pictures in a way so that one is placed over the other. But both should have equal transparency. Also the location of the first picture over the second should be determinable. is there any way we can do this using imfuse or any other function in MATLAB? whenevr I use this script one gets faded and is located in one of the corners which are not desirable. Can we fix this? imfuse, transparency, blend MATLAB Answers — New Questions
How to obtain the State Transition Matrix from Simscape Multibody model?
I need to include the Dynamic of the robot I’m using, imported from an URDF file, to a Extended Kalman Filter as the State Transition Function in order to estimate the states of the system. I tried to put all the simscape model inside a Simulink Function, but it brings Error1 saying I can’t put the solver configuration block (from the robot’s body tree) inside a subsystem. I came back and also tried taking the solver configuration block out of the Simulink Function and brin it in using a Connection Port, but it sends now Error2 saying all the elements of the body tree must be in the same level.
Error1: "’brazo_2dof/Simulink Function/Solver Configuration’ has been placed in the function call subsystem ‘brazo_2dof/Simulink Function’ but does not support this configuration. Move the block out of the function call subsystem."
Error2: "Connections of the Physical Network cross nonvirtual boundaries. If any blocks in a Physical Network are within a nonvirtual subsystem, then all blocks of that network must be in the same nonvirtual subsystem. Either move affected blocks out of the nonvirtual subsystem, move network blocks into exactly one nonvirtual subsystem, or reconfigure affected nonvirtual subsystems to be virtual subsystems."
How else could I include the dynamics of my system, imported from the URDF, as the StateTransitionFunction?I need to include the Dynamic of the robot I’m using, imported from an URDF file, to a Extended Kalman Filter as the State Transition Function in order to estimate the states of the system. I tried to put all the simscape model inside a Simulink Function, but it brings Error1 saying I can’t put the solver configuration block (from the robot’s body tree) inside a subsystem. I came back and also tried taking the solver configuration block out of the Simulink Function and brin it in using a Connection Port, but it sends now Error2 saying all the elements of the body tree must be in the same level.
Error1: "’brazo_2dof/Simulink Function/Solver Configuration’ has been placed in the function call subsystem ‘brazo_2dof/Simulink Function’ but does not support this configuration. Move the block out of the function call subsystem."
Error2: "Connections of the Physical Network cross nonvirtual boundaries. If any blocks in a Physical Network are within a nonvirtual subsystem, then all blocks of that network must be in the same nonvirtual subsystem. Either move affected blocks out of the nonvirtual subsystem, move network blocks into exactly one nonvirtual subsystem, or reconfigure affected nonvirtual subsystems to be virtual subsystems."
How else could I include the dynamics of my system, imported from the URDF, as the StateTransitionFunction? I need to include the Dynamic of the robot I’m using, imported from an URDF file, to a Extended Kalman Filter as the State Transition Function in order to estimate the states of the system. I tried to put all the simscape model inside a Simulink Function, but it brings Error1 saying I can’t put the solver configuration block (from the robot’s body tree) inside a subsystem. I came back and also tried taking the solver configuration block out of the Simulink Function and brin it in using a Connection Port, but it sends now Error2 saying all the elements of the body tree must be in the same level.
Error1: "’brazo_2dof/Simulink Function/Solver Configuration’ has been placed in the function call subsystem ‘brazo_2dof/Simulink Function’ but does not support this configuration. Move the block out of the function call subsystem."
Error2: "Connections of the Physical Network cross nonvirtual boundaries. If any blocks in a Physical Network are within a nonvirtual subsystem, then all blocks of that network must be in the same nonvirtual subsystem. Either move affected blocks out of the nonvirtual subsystem, move network blocks into exactly one nonvirtual subsystem, or reconfigure affected nonvirtual subsystems to be virtual subsystems."
How else could I include the dynamics of my system, imported from the URDF, as the StateTransitionFunction? simscape, extended kalman filter, state transition function, multibody, estimate states MATLAB Answers — New Questions
Edge browser takes 400MB RAM with only one tab opening!
Is this a normal? I can’t believe the fact but the task manager will not lie as you can see from the screenshot. Why this happens?
Is this a normal? I can’t believe the fact but the task manager will not lie as you can see from the screenshot. Why this happens? Read More
Can anyone recommend a safe Spotif.y music Downloader for my PC Windows 11?
I’m looking for a safe Spotif.y music downloader recently. I want to download my favorite songs to MP3 format and put them on my Windows 11 computer. I’ve tried some online tools, but they don’t seem very reliable, and some are full of ads. So I want to ask everyone, have you used a safe and simple Spotif.y music downloader? Can you recommend one? I hope the operation is not too complicated and can download songs on S.potify stably.
I’m looking for a safe Spotif.y music downloader recently. I want to download my favorite songs to MP3 format and put them on my Windows 11 computer. I’ve tried some online tools, but they don’t seem very reliable, and some are full of ads. So I want to ask everyone, have you used a safe and simple Spotif.y music downloader? Can you recommend one? I hope the operation is not too complicated and can download songs on S.potify stably. Read More
Switched of electricity, now PC won’t start.
Had to turn of the electricity to disconnect some plug sockets for painting. Turned electricity back on but now the pc shows this:
Had to turn of the electricity to disconnect some plug sockets for painting. Turned electricity back on but now the pc shows this: Read More
Microsoft office outlook cannot connect to onprem exchange server
Hi,
In my company, we are using on-prem Exchange 2019 for the mail server and we published our main website on the same domain as the primary email address. For instance, email address removed for privacy reasons is our email address format and our website address is example.com. Everything was working fine until we developed our website, after that from the internet whenever I tried to add an account to Microsoft Office Outlook I kept receiving “Something went wrong and Outlook couldn’t set up your account”. After so much effort and searching I’ve found out the reason is that Outlook sends a query to example.com which is my primary domain and the new website sends some response that causes the error and when I removed the DNS record from the internet everything went back to normal.
Now I do not know how to resolve this issue so I can have my website while outlook works correctly.
Please help me
Hi,In my company, we are using on-prem Exchange 2019 for the mail server and we published our main website on the same domain as the primary email address. For instance, email address removed for privacy reasons is our email address format and our website address is example.com. Everything was working fine until we developed our website, after that from the internet whenever I tried to add an account to Microsoft Office Outlook I kept receiving “Something went wrong and Outlook couldn’t set up your account”. After so much effort and searching I’ve found out the reason is that Outlook sends a query to example.com which is my primary domain and the new website sends some response that causes the error and when I removed the DNS record from the internet everything went back to normal.Now I do not know how to resolve this issue so I can have my website while outlook works correctly.Please help me Read More
Onedrive – why multiple folders in Explorer
OK I know many folks don’t like OneDrive, but I have 2 PC’s and a laptop, and I want files and emails to be available on either device.
Now that I found out how to stop my desktop being copied between the units that all have different display size and resolution, OneDrive basically lets me do that.
However, it presents an annoying feature whereby there are 2 different branches with folders on my primary PC.
There is a one drive folder – in John -Personal and John Chapman, the problem is I then see multiple downloads, document, picture folders etc, which confuses me.
How do I simplify this – I create Word, Excel and PowerPoint files and use outlook for 2 email addresses – those are the files I want available on either of the 3 devices I use.
Is this duplication or just a view selection that I don’t know how to control?
Did I describe my problem clearly? It’s hard to show full detail without showing more folder content.
Thanks.
OK I know many folks don’t like OneDrive, but I have 2 PC’s and a laptop, and I want files and emails to be available on either device. Now that I found out how to stop my desktop being copied between the units that all have different display size and resolution, OneDrive basically lets me do that.However, it presents an annoying feature whereby there are 2 different branches with folders on my primary PC. There is a one drive folder – in John -Personal and John Chapman, the problem is I then see multiple downloads, document, picture folders etc, which confuses me.How do I simplify this – I create Word, Excel and PowerPoint files and use outlook for 2 email addresses – those are the files I want available on either of the 3 devices I use.Is this duplication or just a view selection that I don’t know how to control? Did I describe my problem clearly? It’s hard to show full detail without showing more folder content.Thanks. Read More
I want to create a following matrix using nested loops
Matrix[1,2,3,4,5;2,4,7,11,16;3,7,14,25,41] Here every row has different logic.How do I use for loop?Matrix[1,2,3,4,5;2,4,7,11,16;3,7,14,25,41] Here every row has different logic.How do I use for loop? Matrix[1,2,3,4,5;2,4,7,11,16;3,7,14,25,41] Here every row has different logic.How do I use for loop? #nestedloop #matrix MATLAB Answers — New Questions
Organization Sign-in portal not popping up
When I try to open Matlab Desktop 2024a it asks me to sign in and when i type my email it says "Sign into your organization’s portal to proceed." but there is not Organization portal popping up for me to sign inWhen I try to open Matlab Desktop 2024a it asks me to sign in and when i type my email it says "Sign into your organization’s portal to proceed." but there is not Organization portal popping up for me to sign in When I try to open Matlab Desktop 2024a it asks me to sign in and when i type my email it says "Sign into your organization’s portal to proceed." but there is not Organization portal popping up for me to sign in login, sign-in MATLAB Answers — New Questions
Snipping tool is absolutely under rated
It’s really good, I use it all the time!!! Do you agree with me?
It’s really good, I use it all the time!!! Do you agree with me? Read More