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FX 69-PR-281 (fx69pr281-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: FX 69-PR-281 (fx69pr281-il)
Reynolds number: 100,000
Max Cl/Cd: 26.09 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx69pr281-il-100000-n5.txt
Download as CSV file: xf-fx69pr281-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 69-PR-281                                    
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000   0.2364   0.09986   0.09303  -0.1253   0.8287   0.1314
 -10.500   0.2537   0.09210   0.08507  -0.1324   0.8032   0.1389
 -10.250   0.2859   0.09103   0.08390  -0.1348   0.7883   0.1401
 -10.000   0.3055   0.08970   0.08252  -0.1357   0.7723   0.1419
  -9.750   0.2939   0.08425   0.07692  -0.1393   0.7628   0.1480
  -9.500   0.3140   0.08374   0.07639  -0.1390   0.7476   0.1492
  -9.000   0.3367   0.08012   0.07263  -0.1405   0.7242   0.1548
  -7.500   0.3206   0.06402   0.05620  -0.1430   0.6675   0.1786
  -7.250   0.3423   0.06410   0.05623  -0.1419   0.6563   0.1797
  -6.750  -0.0048   0.03632   0.02792  -0.1416   0.6562   0.2035
  -6.500   0.0281   0.03658   0.02819  -0.1412   0.6480   0.2050
  -6.250   0.0373   0.03640   0.02808  -0.1386   0.6381   0.2066
  -6.000   0.0475   0.03580   0.02741  -0.1370   0.6294   0.2088
  -5.750   0.0540   0.03447   0.02586  -0.1362   0.6222   0.2119
  -5.500   0.0456   0.03281   0.02396  -0.1337   0.6136   0.2155
  -5.250   0.0576   0.03196   0.02297  -0.1323   0.6050   0.2181
  -5.000   0.0860   0.03185   0.02283  -0.1320   0.5974   0.2200
  -4.750   0.1009   0.03167   0.02268  -0.1300   0.5889   0.2220
  -4.500   0.1170   0.03128   0.02225  -0.1285   0.5805   0.2245
  -4.250   0.1382   0.03062   0.02140  -0.1281   0.5732   0.2278
  -4.000   0.1555   0.02977   0.02027  -0.1276   0.5661   0.2316
  -3.750   0.1716   0.02946   0.01997  -0.1258   0.5578   0.2338
  -3.500   0.1939   0.02934   0.01986  -0.1247   0.5502   0.2359
  -3.250   0.2216   0.02916   0.01959  -0.1245   0.5436   0.2386
  -3.000   0.2359   0.02897   0.01943  -0.1225   0.5356   0.2413
  -2.750   0.2550   0.02864   0.01900  -0.1213   0.5281   0.2446
  -2.500   0.2804   0.02817   0.01827  -0.1213   0.5213   0.2485
  -2.250   0.3008   0.02794   0.01800  -0.1202   0.5142   0.2511
  -2.000   0.3175   0.02789   0.01802  -0.1182   0.5062   0.2533
  -1.750   0.3394   0.02779   0.01790  -0.1171   0.4991   0.2561
  -1.500   0.3639   0.02768   0.01769  -0.1165   0.4926   0.2594
  -1.250   0.3783   0.02758   0.01758  -0.1144   0.4850   0.2625
  -1.000   0.3985   0.02741   0.01728  -0.1133   0.4781   0.2662
  -0.750   0.4256   0.02722   0.01691  -0.1132   0.4720   0.2697
  -0.500   0.4423   0.02726   0.01702  -0.1113   0.4652   0.2722
  -0.250   0.4578   0.02733   0.01715  -0.1093   0.4578   0.2750
   0.000   0.4788   0.02734   0.01711  -0.1081   0.4513   0.2784
   0.250   0.5025   0.02735   0.01701  -0.1075   0.4454   0.2823
   0.500   0.5176   0.02747   0.01713  -0.1056   0.4383   0.2860
   0.750   0.5376   0.02754   0.01708  -0.1045   0.4319   0.2897
   1.000   0.5614   0.02756   0.01708  -0.1038   0.4265   0.2930
   1.250   0.5779   0.02783   0.01740  -0.1021   0.4204   0.2964
   1.500   0.5946   0.02809   0.01769  -0.1005   0.4140   0.3001
   1.750   0.6156   0.02826   0.01778  -0.0995   0.4085   0.3045
   2.000   0.6414   0.02837   0.01773  -0.0993   0.4038   0.3094
   2.250   0.6553   0.02876   0.01816  -0.0975   0.3979   0.3134
   2.500   0.6718   0.02908   0.01855  -0.0960   0.3924   0.3172
   2.750   0.6923   0.02934   0.01878  -0.0950   0.3877   0.3216
   3.000   0.7172   0.02955   0.01889  -0.0946   0.3834   0.3269
   3.250   0.7300   0.03009   0.01949  -0.0928   0.3784   0.3318
   3.500   0.7464   0.03055   0.01991  -0.0916   0.3736   0.3371
   3.750   0.7648   0.03089   0.02030  -0.0905   0.3694   0.3420
   4.000   0.7897   0.03112   0.02048  -0.0901   0.3657   0.3480
   4.250   0.8054   0.03169   0.02107  -0.0888   0.3616   0.3540
   4.500   0.8178   0.03238   0.02179  -0.0873   0.3573   0.3602
   4.750   0.8336   0.03295   0.02238  -0.0861   0.3534   0.3665
   5.000   0.8524   0.03340   0.02286  -0.0852   0.3498   0.3733
   5.250   0.8784   0.03367   0.02306  -0.0850   0.3467   0.3820
   5.500   0.8932   0.03441   0.02380  -0.0839   0.3433   0.3900
   5.750   0.8996   0.03543   0.02496  -0.0820   0.3394   0.3966
   6.000   0.9105   0.03631   0.02594  -0.0806   0.3357   0.4040
   6.250   0.9267   0.03702   0.02667  -0.0797   0.3324   0.4136
   6.500   0.9484   0.03753   0.02711  -0.0793   0.3295   0.4244
   6.750   0.9784   0.03770   0.02725  -0.0795   0.3269   0.4364
   7.000   0.9733   0.03944   0.02918  -0.0771   0.3234   0.4444
   7.250   0.9737   0.04106   0.03090  -0.0754   0.3198   0.4536
   7.500   0.9815   0.04231   0.03225  -0.0742   0.3164   0.4634
   7.750   0.9969   0.04319   0.03317  -0.0735   0.3135   0.4762
   8.000   1.0198   0.04370   0.03361  -0.0733   0.3110   0.4909
   8.250   1.0424   0.04424   0.03417  -0.0730   0.3087   0.5056
   8.500   1.0195   0.04757   0.03776  -0.0706   0.3050   0.5128
   9.000   1.0128   0.05225   0.04271  -0.0684   0.2982   0.5352
   9.250   1.0315   0.05305   0.04349  -0.0681   0.2957   0.5537
   9.500   1.0596   0.05308   0.04352  -0.0680   0.2937   0.5749
   9.750   1.0307   0.05782   0.04849  -0.0667   0.2899   0.5828
  10.000   0.9318   0.07025   0.06138  -0.0664   0.2818   0.5689
  10.250   0.9545   0.07065   0.06179  -0.0662   0.2798   0.5917
  10.500   0.9880   0.06983   0.06097  -0.0658   0.2785   0.6218
  10.750   1.0247   0.06865   0.05979  -0.0653   0.2774   0.6573
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