Hi community, I am ploting a figure and i want to center the figure in the plot

Question

Jacob 2014-4-5

0
链接

此问题的直接链接

https://ww2.mathworks.cn/matlabcentral/answers/124611-hi-community-i-am-ploting-a-figure-and-i-want-to-center-the-figure-in-the-plot

评论： Jacob 2014-4-5

When i plot my figure it apears like a little dot with gigantic scales, I want that when the plot opens up, it opens exactly where the figure is. Here is the example:

plot(d(:,1),d(:,2),'.')

d = 1.0e+03 *

0010         0
0010   -0.0000
0010   -0.0000
0010   -0.0000
0010   -0.0000
0010   -0.0000
0010   -0.0000
0010   -0.0000
0010   -0.0000
0010   -0.0000
0010   -0.0000
0010   -0.0000
0010   -0.0000
0010   -0.0000
0010   -0.0000
0010   -0.0000
0010   -0.0000
0010   -0.0000
0009   -0.0000
0009   -0.0000
0009   -0.0000
0009   -0.0000
0009   -0.0000
0009    0.0000
0009    0.0000
0009    0.0000
0009    0.0000
0009    0.0000
0009    0.0000
0009    0.0000
0009    0.0000
0009    0.0000
0008    0.0000
0008    0.0000
0008    0.0000
0008    0.0000
0008    0.0000
0008    0.0000
0008    0.0000
0008    0.0000
0008    0.0000
0008    0.0000
0007    0.0000
0007   -0.0000
0007   -0.0000
0007   -0.0000
0007   -0.0000
0007   -0.0000
0007   -0.0000
0007   -0.0000
0007   -0.0000
0006   -0.0000
0006   -0.0000
0006   -0.0000
0006   -0.0000
0006   -0.0000
0006   -0.0000
0006   -0.0000
0006   -0.0000
0005   -0.0000
0005   -0.0000
0005   -0.0000
0005   -0.0000
0005   -0.0000
0005   -0.0000
0005   -0.0000
0005   -0.0000
0004   -0.0000
0004   -0.0000
0004   -0.0000
0004   -0.0000
0004   -0.0000
0004   -0.0000
0004   -0.0000
0004   -0.0000
0003   -0.0000
0003   -0.0000
0003   -0.0000
0003   -0.0000
0003   -0.0000
0003   -0.0000
0003   -0.0000
0003   -0.0000
0003   -0.0000
0002   -0.0000
0002   -0.0000
0002   -0.0000
0002   -0.0000
0002   -0.0000
0002   -0.0000
0002   -0.0000
0002   -0.0000
0002   -0.0000
0002   -0.0000
0001   -0.0000
0001   -0.0000
0001   -0.0000
0001   -0.0000
0001   -0.0000
0001   -0.0000
0001   -0.0000
0001   -0.0000
0001   -0.0000
0001   -0.0000
0001   -0.0000
0001   -0.0000
0001   -0.0000
0001   -0.0000
0000   -0.0000
0000   -0.0000
0000   -0.0000
0000   -0.0000
0000   -0.0000
0000   -0.0000
0000   -0.0000
0000   -0.0000
0000   -0.0000
0000   -0.0000
0000   -0.0000
0000   -0.0000
0000   -0.0000
0000   -0.0000
0000   -0.0000
0000   -0.0000
0000   -0.0000
         0         0
0000    0.0000
0000    0.0000
0000    0.0000
0000    0.0000
0000    0.0000
0000    0.0000
0000    0.0000
0000    0.0000
0000    0.0000
0000    0.0000
0000    0.0000
0000    0.0000
0000    0.0000
0000    0.0000
0000    0.0000
0000    0.0000
0000    0.0000
0000    0.0000
0001    0.0000
0001    0.0000
0001    0.0000
0001    0.0000
0001    0.0000
0001    0.0000
0001    0.0000
0001    0.0000
0001    0.0000
0001    0.0000
0001    0.0000
0001    0.0000
0001    0.0000
0002    0.0000
0002    0.0000
0002    0.0000
0002    0.0000
0002    0.0000
0002    0.0000
0002    0.0000
0002    0.0000
0002    0.0000
0002    0.0000
0003    0.0000
0003    0.0000
0003    0.0000
0003    0.0000
0003    0.0000
0003    0.0000
0003    0.0000
0003    0.0000
0003    0.0000
0004    0.0000
0004    0.0000
0004    0.0000
0004    0.0000
0004    0.0000
0004    0.0000
0004    0.0000
0004    0.0000
0005    0.0000
0005    0.0000
0005    0.0000
0005    0.0000
0005    0.0000
0005    0.0000
0005    0.0000
0005    0.0000
0006    0.0000
0006    0.0000
0006    0.0000
0006    0.0000
0006    0.0000
0006    0.0000
0006    0.0000
0006    0.0000
0007    0.0000
0007    0.0000
0007    0.0000
0007    0.0000
0007    0.0000
0007    0.0000
0007    0.0000
0007    0.0000
0007    0.0000
0008    0.0000
0008    0.0000
0008    0.0000
0008    0.0000
0008    0.0000
0008    0.0000
0008    0.0000
0008    0.0000
0008    0.0000
0008    0.0000
0009    0.0000
0009    0.0000
0009    0.0000
0009    0.0000
0009    0.0000
0009    0.0000
0009    0.0000
0009    0.0000
0009    0.0000
0009    0.0000
0009    0.0000
0009    0.0000
0009    0.0000
0009    0.0000
0010    0.0000
0010    0.0000
0010    0.0000
0010    0.0000
0010    0.0000
0010    0.0000
0010    0.0000
0010    0.0000
0010    0.0000
0010    0.0000
0010    0.0000
0010    0.0000
0010    0.0000
0010    0.0000
0010    0.0000
0010    0.0000
0010    0.0000
0010         0
9619    0.8716

0 个评论
显示 -2更早的评论隐藏 -2更早的评论

请先登录，再进行评论。

请先登录，再回答此问题。

Answer 1

Image Analyst 2014-4-5

0
链接

此回答的直接链接

https://ww2.mathworks.cn/matlabcentral/answers/124611-hi-community-i-am-ploting-a-figure-and-i-want-to-center-the-figure-in-the-plot#answer_132302

What's up with the last value? It's like 10,000 times as big as any of the other values. So all your values are crammed into a microscopic area near the origin because it has to expand the axes to be able to show your last value of d. Are you sure that's how you want to do it? If that value is not there, it does plot stuff you can see.

0 个评论
显示 -2更早的评论隐藏 -2更早的评论

请先登录，再进行评论。

Answer 2

Azzi Abdelmalek 2014-4-5

0
链接

此回答的直接链接

https://ww2.mathworks.cn/matlabcentral/answers/124611-hi-community-i-am-ploting-a-figure-and-i-want-to-center-the-figure-in-the-plot#answer_132301

编辑：Azzi Abdelmalek 2014-4-5

在 MATLAB Online 中打开

Just use

plot(d(:,1),d(:,2))

4 个评论
显示 2更早的评论隐藏 2更早的评论

Jacob 2014-4-5

Its a function that outputs x & z, i put them together in d=[x,z]

To get this data copy the function and plug in:

airf='2415' (its a character ''); N=250; AoA=alphadeg*pi/180;

function [x,z]=panelgen(airf,N,AoA)

global x global z

if length(airf)==4 c=str2num(airf(1))/100; %read max camber p=str2num(airf(2))/10; %read position of max camber t=str2num(airf(3:4))/100; %read thickness to chord ratio else error('The airfoil descriptor should have 4 characters') end

x=zeros(N+2,1); z=x; for i=1:N+1 xt=1-0.5*(1-cos(2*pi*(i-1)/N)); %calculate panel endpoint x using cos distribution %calculate y ordinate for symmetric airfoil if i==1 i==N+1 yt=0; %ensure airfoil comes back to a point. else yt=5*t*(0.2969*sqrt(xt)-0.126*xt-0.3516*xt^2+0.2843*xt^3-0.1015*xt^4); end %calculate cambeline height and angle if (c>0) if xt<=p %if forward of max caber point theta=c*2*(p-xt)/p^2; yc=c*(2*p*xt-xt^2)/p^2; else %if aft of max camber point theta=c*2*(p-xt)/(1-p)^2; yc=c*((1-2*p)+2*p*xt-xt^2)/(1-p)^2; end else %if no camber theta=0; yc=0; end %apply camber and get final airfoil shape if i-1>=0.5*N x(i)=xt-yt*sin(theta); z(i)=yc+yt*cos(theta); else x(i)=xt+yt*sin(theta); z(i)=yc-yt*cos(theta); end end %add wake panel endpoint

x(N+2)=10000*cos(AoA);

z(N+2)=10000*sin(AoA);