TSAGI HERITAGE, NACA23012, M=0.5, alpha = -1.2 grad

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TSAGI HERITAGE, NACA23012, M=0.5, alpha = -1.2 grad

Posted May 15, 2014 at 04:09 by skeptik

I have some useful papers totally on Russian.

I will post some experimental results about airfoils here as i will translate it to appliciable form.

Here are the results which could be easily plotted by GNUplot. They are from far away 1946, TSAGI (Central Aero-, Gas-Dynamics Institute) publisher.

Code:

#NACA 23012 exp. results alpha = -1°12' M=0.5
# Cp=(Pfoil - Pinfinity)/q; q = rho*U^2/2
#columns
#    x, %    Cp
#Upper
1    0.6
2.5    0.090    
5    -0.270
7.5    -0.460
10    -0.560
15    -0.610
20    -0.535
25    -0.470
30    -0.420
35    -0.370
40    -0.340
45    -0.310
50    -0.280
55    -0.250
60    -0.215
65    -0.170
70    -0.135
75    -0.100
80    -0.060
85    -0.020
90    0.050
95    0.130
100    0.240


#Lower
1    -0.780
2.5    -0.725    
5    -0.520
7.5    -0.375
10    -0.330
15    -0.330
20    -0.360
25    -0.365
30    -0.360
35    -0.340
40    -0.305
45    -0.275
50    -0.245
55    -0.210
60    -0.180
65    -0.145
70    -0.110
75    -0.080
80    -0.040
85    0.000
90    0.060
95    0.140
100    0.230

For instance comparation to numerical results (sonicFoam):