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| author | priyanka | 2015-06-24 15:03:17 +0530 |
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| committer | priyanka | 2015-06-24 15:03:17 +0530 |
| commit | b1f5c3f8d6671b4331cef1dcebdf63b7a43a3a2b (patch) | |
| tree | ab291cffc65280e58ac82470ba63fbcca7805165 /548/DEPENDENCIES/5_01data.sci | |
| download | Scilab-TBC-Uploads-b1f5c3f8d6671b4331cef1dcebdf63b7a43a3a2b.tar.gz Scilab-TBC-Uploads-b1f5c3f8d6671b4331cef1dcebdf63b7a43a3a2b.tar.bz2 Scilab-TBC-Uploads-b1f5c3f8d6671b4331cef1dcebdf63b7a43a3a2b.zip | |
initial commit / add all books
Diffstat (limited to '548/DEPENDENCIES/5_01data.sci')
| -rwxr-xr-x | 548/DEPENDENCIES/5_01data.sci | 13 |
1 files changed, 13 insertions, 0 deletions
diff --git a/548/DEPENDENCIES/5_01data.sci b/548/DEPENDENCIES/5_01data.sci new file mode 100755 index 000000000..8760cd0b1 --- /dev/null +++ b/548/DEPENDENCIES/5_01data.sci @@ -0,0 +1,13 @@ +//A model wing is placed in a low speed subsonic wind tunnel.the wing has a NACA-2412 airfoil.
+c=1.3;//chord length in meter
+V=50; // velocity of flow in test section(m/s)
+a=4;//angle of attack in degree
+D=1.225;//standard sea level density,Kg/m^3
+u=1.789*10^-5;//Viscosity in kg/(m)(s)
+//from standard table for NACA-2412 airfoil with angle of attack 4 degree:
+Cl=0.63;//Lift coefficient
+Cm=-0.035;//moment coefficient about quarter chord
+Re=D*V*c/u //reynold's no.
+//from the value of Re and angle of attack and by using standard table we can get Cd:
+Cd=0.007;//coefficient of drag
+q=D*V^2/2 //dynamic pressure,N/m^2
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