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TSAGI 8% AIRFOIL (tsagi8-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: TSAGI 8% AIRFOIL (tsagi8-il)
Reynolds number: 500,000
Max Cl/Cd: 72.21 at α=3.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-tsagi8-il-500000.txt
Download as CSV file: xf-tsagi8-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: TSAGI 8% AIRFOIL                                
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.5643   0.08259   0.08040  -0.0123   1.0000   0.0169
  -8.500  -0.5723   0.07753   0.07538  -0.0167   1.0000   0.0171
  -8.250  -0.5836   0.07312   0.07096  -0.0189   1.0000   0.0171
  -8.000  -0.5901   0.06847   0.06627  -0.0205   1.0000   0.0173
  -7.750  -0.5925   0.06352   0.06124  -0.0217   1.0000   0.0177
  -5.750  -0.5608   0.02779   0.02361  -0.0062   1.0000   0.0174
  -5.500  -0.5585   0.02168   0.01675  -0.0007   1.0000   0.0150
  -5.250  -0.5395   0.02141   0.01644   0.0008   1.0000   0.0168
  -5.000  -0.5260   0.01853   0.01315   0.0040   1.0000   0.0161
  -4.750  -0.5096   0.01642   0.01072   0.0067   1.0000   0.0161
  -4.500  -0.4843   0.01494   0.00904   0.0074   0.9988   0.0169
  -4.250  -0.4475   0.01369   0.00760   0.0056   0.9951   0.0181
  -4.000  -0.4112   0.01290   0.00670   0.0038   0.9904   0.0193
  -3.750  -0.3774   0.01146   0.00519   0.0024   0.9851   0.0231
  -3.500  -0.3417   0.01083   0.00451   0.0007   0.9790   0.0266
  -3.250  -0.3063   0.01020   0.00381  -0.0009   0.9721   0.0304
  -3.000  -0.2712   0.00961   0.00319  -0.0025   0.9640   0.0401
  -2.750  -0.2348   0.00907   0.00265  -0.0043   0.9551   0.0550
  -2.500  -0.2024   0.00845   0.00231  -0.0054   0.9414   0.1203
  -2.250  -0.1748   0.00770   0.00205  -0.0057   0.9231   0.2535
  -2.000  -0.1542   0.00677   0.00181  -0.0045   0.9014   0.4561
  -1.750  -0.1434   0.00577   0.00163  -0.0008   0.8782   0.6913
  -1.500  -0.1157   0.00528   0.00173   0.0000   0.8601   0.8767
  -1.250  -0.0648   0.00548   0.00189  -0.0045   0.8446   0.9273
  -1.000  -0.0293   0.00569   0.00197  -0.0058   0.8256   0.9431
  -0.750   0.0118   0.00603   0.00219  -0.0082   0.8076   0.9563
  -0.500   0.0584   0.00628   0.00231  -0.0120   0.7897   0.9611
  -0.250   0.1035   0.00661   0.00251  -0.0154   0.7722   0.9713
   0.000   0.1559   0.00683   0.00263  -0.0206   0.7538   0.9786
   0.250   0.1996   0.00695   0.00264  -0.0239   0.7358   0.9850
   0.500   0.2454   0.00696   0.00256  -0.0279   0.7181   0.9903
   0.750   0.2826   0.00699   0.00251  -0.0300   0.7006   0.9946
   1.000   0.3201   0.00690   0.00236  -0.0322   0.6828   0.9977
   1.250   0.3538   0.00687   0.00227  -0.0337   0.6653   1.0000
   1.500   0.3764   0.00690   0.00225  -0.0327   0.6490   1.0000
   1.750   0.3992   0.00694   0.00224  -0.0317   0.6320   1.0000
   2.000   0.4221   0.00698   0.00224  -0.0308   0.6139   1.0000
   2.250   0.4449   0.00703   0.00227  -0.0299   0.5956   1.0000
   2.500   0.4678   0.00710   0.00230  -0.0289   0.5765   1.0000
   2.750   0.4906   0.00718   0.00233  -0.0279   0.5523   1.0000
   3.000   0.5126   0.00732   0.00235  -0.0268   0.5132   1.0000
   3.250   0.5344   0.00752   0.00239  -0.0257   0.4693   1.0000
   3.500   0.5568   0.00772   0.00250  -0.0247   0.4313   1.0000
   3.750   0.5784   0.00801   0.00262  -0.0236   0.3807   1.0000
   4.000   0.5988   0.00851   0.00279  -0.0224   0.2980   1.0000
   4.250   0.6145   0.00973   0.00324  -0.0208   0.1306   1.0000
   4.500   0.6313   0.01095   0.00397  -0.0191   0.0320   1.0000
   4.750   0.6515   0.01163   0.00473  -0.0176   0.0241   1.0000
   5.000   0.6731   0.01204   0.00521  -0.0164   0.0217   1.0000
   5.250   0.6935   0.01259   0.00584  -0.0150   0.0199   1.0000
   5.500   0.7129   0.01328   0.00659  -0.0134   0.0183   1.0000
   5.750   0.7271   0.01467   0.00808  -0.0110   0.0162   1.0000
   6.000   0.7454   0.01554   0.00904  -0.0092   0.0153   1.0000
   6.250   0.7646   0.01634   0.00994  -0.0076   0.0146   1.0000
   6.500   0.7828   0.01747   0.01117  -0.0057   0.0141   1.0000
   6.750   0.8012   0.01877   0.01259  -0.0039   0.0133   1.0000
   7.000   0.8193   0.02053   0.01452  -0.0020   0.0132   1.0000
   7.250   0.8366   0.02297   0.01721   0.0001   0.0137   1.0000
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