NACA four digit matlab code
Old instructions in Icelandic Wind tunnel test stand airfoil code A driver file for ReplicatorG
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ingij10
180
Instructions Matlab Codes and diver file/Foamcutter.m
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180
Instructions Matlab Codes and diver file/Foamcutter.m
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% Tveggja NACAmptt pr<EFBFBD>f<EFBFBD>la-reiknir sem t<EFBFBD>knbreytir ferlum yfir
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% <EFBFBD> G-k<EFBFBD><EFBFBD>a fyrir frau<EFBFBD>plastskera sem sta<EFBFBD>settur er <EFBFBD> vindgangar<EFBFBD>mi
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% H<EFBFBD>sk<EFBFBD>lans <EFBFBD> Reykjav<EFBFBD>k.
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% Innlagsbreytur: m, p, t, c, b, TEo, TEv, inc, n, filename
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% Hver innlagsbreyta fyrir sig er <EFBFBD>tsk<EFBFBD>r<EFBFBD> <EFBFBD>ar sem h<EFBFBD>n kemur fyrir <EFBFBD>
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%
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% k<EFBFBD><EFBFBD>anum
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% <EFBFBD>ttaksbreyta: G-k<EFBFBD><EFBFBD>i sem skrifa<EFBFBD>ur er <EFBFBD> skr<EFBFBD>nna 'filename.gcode'
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% H<EFBFBD>fundur: Kristj<EFBFBD>n Orri Magn<EFBFBD>sson, H<EFBFBD>sk<EFBFBD>linn <EFBFBD> Reykjav<EFBFBD>k, Haust 2011
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%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
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clear all
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% Nafn <EFBFBD>ttaksskr<EFBFBD>ar. Endingin skal vera .gcode.
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filename=['NACA0015test.gcode']
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%One digit max camber as % of chord, m2 er pr<EFBFBD>f<EFBFBD>llinn sem a<EFBFBD> A-B plan
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%frau<EFBFBD>plastskerans teiknar og m er fyrir X-Y plani<EFBFBD>.
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m=0
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m2=0
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%One digit describing the distance of maximum camber from the airfoil
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%leading edge in tens of percents of the chord. p->X-Y plan, p2->A-B plan
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p=0
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p2=0
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%Two digits describing maximum thickness of the airfoil as percent of the
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%chord. t-> X-Y plan, t2-> A-B plan
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t=15
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t2=15
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%chord length (mm). c ->X-Y plan c2->A-B plan
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c=130
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c2=130
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% Span length(mm). V<EFBFBD>nghaf v<EFBFBD>ngs sem skera <EFBFBD> <EFBFBD>t.
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b=500
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%T/E horizontal offset (mm). L<EFBFBD>r<EFBFBD>tt hli<EFBFBD>run trailing edge milli pr<EFBFBD>f<EFBFBD>la <EFBFBD>
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%XY og AB v<EFBFBD>ngsni<EFBFBD>um.
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TEo=10
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%T/E vertical offset (mm). L<EFBFBD><EFBFBD>r<EFBFBD>tt hli<EFBFBD>run trailing edge milli pr<EFBFBD>f<EFBFBD>la <EFBFBD>
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%XY og AB v<EFBFBD>ngsni<EFBFBD>um.
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TEv=30
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%Incline(rad). Vindingur, horn milli v<EFBFBD>ngl<EFBFBD>na sitt hvors pr<EFBFBD>f<EFBFBD>ls.
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inc=20*pi/180
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%number of points (80 is minimum for L/E precision)
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n=80
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%Total span (mm). Hornr<EFBFBD>tt vegalengd milli XY og AB plana, fasti.
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tsp=935
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%Scale up for shorter than tsp wings
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inc=inc*tsp/b;
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c2=c-(c-c2)*tsp/b;
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TEo=TEo*tsp/b;
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TEv=TEv*tsp/b;
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%scaling for machine units
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c=c*8.889;
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c2=c2*8.889;
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TEo=TEo*8.889; TEv=TEv*8.889;
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%dx <EFBFBD>arf a<EFBFBD> ganga upp <EFBFBD> c til a<EFBFBD> loka pr<EFBFBD>f<EFBFBD>lnum
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dx=c/n;
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dx2=c2/n;
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%Scaling for equations m=m/100;
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m2=m2/100;
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p=p/10;
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p2=p2/10;
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t=t/100;
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t2=t2/100;
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x=0:dx:c; %L<EFBFBD>r<EFBFBD>tt sta<EFBFBD>setning mi<EFBFBD>a<EFBFBD> vi<EFBFBD> v<EFBFBD>ngl<EFBFBD>nu <EFBFBD> XY plani
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x2=0:dx2:c2;%L<EFBFBD><EFBFBD>r<EFBFBD>tt sta<EFBFBD>setning mi<EFBFBD>a<EFBFBD> vi<EFBFBD> v<EFBFBD>ngl<EFBFBD>nu <EFBFBD> XY plani
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%symmetrical airfoil generator
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yt=(t*c/0.2).*(0.2969.*(x./c).^0.5-0.1281.*(x./c)- 0.3516.*(x./c).^2+0.2843.*(x./c).^3-0.1015.*(x./c).^4);
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yt2=(t2*c2/0.2).*(0.2969.*(x2./c2).^0.5-0.1281.*(x2./c2)- 0.3516.*(x2./c2).^2+0.2843.*(x2./c2).^3-0.1015.*(x2./c2).^4);
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%camber line 1 (XY plan)
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for i=1:length(x)
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if x(i)<p*c
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yc(i)=m.*(x(i)./p^2).*(2*p-x(i)./c)
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else
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yc(i)=m.*(c-x(i))./(1-p)^2.*(1+x(i)./c-2*p);
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end
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end
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th(1)=1;
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for i=2:length(x)
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th(i)=atan((yc(i)-yc(i-1))/dx); %Snertilhorn camber line (XY)
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end
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%camber line 2 (AB plan)
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for i=1:length(x2)
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if x2(i)<p2*c2
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yc2(i)=m2.*(x2(i)./p2^2).*(2*p2-x2(i)./c2);
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else
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yc2(i)=m2.*(c2-x2(i))./(1-p2)^2.*(1+x2(i)./c2-2*p2);
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end
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end
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th2(1)=1;
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for i=2:length(x2)
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th2(i)=atan((yc2(i)-yc2(i-1))/dx); %Snertilhorn camber line (AB)
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end
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%points for profile 1 (XY)
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xu=x-yt.*sin(th); % X upper
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xl=x+yt.*sin(th); % X lower
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yu=yc+yt.*cos(th); % Y upper
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yl=yc-yt.*cos(th); % Y lower
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xu=fliplr(xu); %Sn<EFBFBD>i<EFBFBD> vi<EFBFBD> til a<EFBFBD> f<EFBFBD> samfella hreyfingu yfir pr<EFBFBD>f<EFBFBD>linn
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yu=fliplr(yu);
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%points for profile 2 (AB)
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xu2=x2-yt2.*sin(th2)+100000; %A upper (<EFBFBD>n vindings)
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xl2=x2+yt2.*sin(th2)+100000; %A lower (<EFBFBD>n vindings)
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yu2=yc2+yt2.*cos(th2); %B upper
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yl2=yc2-yt2.*cos(th2); %B lower
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fu=atan(yu2./xu2); %V<EFBFBD>ngl<EFBFBD>nu AB pr<EFBFBD>f<EFBFBD>ls sn<EFBFBD>i<EFBFBD> um horni<EFBFBD> inc
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fl=atan(yl2./xl2);
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yu2=xu2.*sin(fu+inc)-100000*sin(inc);
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yl2=xl2.*sin(fl+inc)-100000*sin(inc);
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xu2=xu2.*cos(fu+inc)-100000*cos(inc);
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xl2=xl2.*cos(fl+inc)-100000*cos(inc);
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yu2=yu2-yu2(end)+TEv; %Hli<EFBFBD>run A upper <EFBFBD> l<EFBFBD>r<EFBFBD>tta stefnu
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yl2=yl2-yl2(end)+TEv; %Hli<EFBFBD>run A lower <EFBFBD> l<EFBFBD>r<EFBFBD>tta stefnu
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xu2=xu2+c-xu2(end)-TEo;%Hli<EFBFBD>run B upper <EFBFBD> l<EFBFBD><EFBFBD>r<EFBFBD>tta stefnu
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xl2=xl2+c-xl2(end)-TEo;
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%Hli<EFBFBD>rn B lower <EFBFBD> l<EFBFBD><EFBFBD>r<EFBFBD>tta stefnu
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xu2=fliplr(xu2); %Sn<EFBFBD>i<EFBFBD> vi<EFBFBD> til a<EFBFBD> f<EFBFBD> samfella hreyfingu yfir pr<EFBFBD>f<EFBFBD>linn
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yu2=fliplr(yu2);
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%Wing plotted in 3D for visualization
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z11=zeros(length(xu))
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z12=zeros(length(xl))
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z21=zeros(length(xu2))
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z22=zeros(length(xl2))
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z21=z21+tsp*8.889
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z22=z22+tsp*8.889
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figure(1)
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hold on
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plot3(xu,yu,z11,'r',xl,yl,z12,'r')
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plot3(xu2,yu2,z21,'r',xl2,yl2,z22,'r')
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for i=1:10:length(xu)
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plot3([xu(i) xu2(i)],[yu(i) yu2(i)],[z11(i) z21(i)])
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plot3([xl(i) xl2(i)],[yl(i) yl2(i)],[z11(i) z21(i)])
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end
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axis equal
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%grid on
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hold off
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% GCODE t<EFBFBD>knbreytir -> breytir l<EFBFBD>nuvigrum <EFBFBD> f<EFBFBD>rslul<EFBFBD>nur G-k<EFBFBD><EFBFBD>a.
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% Fyrst er vigrum breytt <EFBFBD>r sta<EFBFBD>setningarvigrum yfir <EFBFBD> f<EFBFBD>rsuvigra
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for i=1:n
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xx(i)=xu(i+1)-xu(i);
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yy(i)=yu(i+1)-yu(i);
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xx(i+length(x))=xl(i+1)-xl(i);
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yy(i+length(x))=yl(i+1)-yl(i);
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end
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for i=1:n
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aa(i)=xu2(i+1)-xu2(i);
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bb(i)=-1*(yu2(i+1)-yu2(i));
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aa(i+length(x2))=xl2(i+1)-xl2(i);
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bb(i+length(x2))=-1*(yl2(i+1)-yl2(i));
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end
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%Svo er skr<EFBFBD>in opnu<EFBFBD>
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fid=fopen(filename,'wt');
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%Og g-k<EFBFBD><EFBFBD>inn skrifa<EFBFBD>ur <EFBFBD> hana
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fprintf(fid,['G1 A' num2str(-TEo) ' B' num2str(-TEv) ' F3500\n'])
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%Hli<EFBFBD>run
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for i=1: 2*n+1
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fprintf(fid,['G1 X' num2str(xx(i)) ' Y' num2str(yy(i)) ' F4000\n']);
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fprintf(fid,['G1 A' num2str(aa(i)) ' B' num2str(bb(i)) ' F4000\n']);
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end
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