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RAF 27 AIRFOIL (raf27-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: RAF 27 AIRFOIL (raf27-il)
Reynolds number: 100,000
Max Cl/Cd: 36.46 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-raf27-il-100000-n5.txt
Download as CSV file: xf-raf27-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: RAF 27 AIRFOIL                                  
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.7089   0.08820   0.08311  -0.0170   1.0000   0.0240
 -11.250  -0.7727   0.06978   0.06447  -0.0313   1.0000   0.0220
 -11.000  -0.8030   0.06278   0.05724  -0.0353   1.0000   0.0217
 -10.750  -0.8253   0.05815   0.05239  -0.0361   1.0000   0.0215
 -10.500  -0.8433   0.05461   0.04864  -0.0347   1.0000   0.0216
 -10.250  -0.8571   0.05175   0.04559  -0.0320   1.0000   0.0218
 -10.000  -0.8655   0.04881   0.04241  -0.0295   1.0000   0.0221
  -9.750  -0.8680   0.04611   0.03947  -0.0273   1.0000   0.0225
  -9.500  -0.8662   0.04367   0.03677  -0.0251   1.0000   0.0233
  -9.250  -0.8611   0.04141   0.03424  -0.0230   1.0000   0.0245
  -9.000  -0.8546   0.03893   0.03141  -0.0208   1.0000   0.0259
  -8.750  -0.8455   0.03633   0.02838  -0.0186   1.0000   0.0272
  -8.500  -0.8328   0.03381   0.02544  -0.0165   1.0000   0.0283
  -8.250  -0.8175   0.03161   0.02288  -0.0147   1.0000   0.0296
  -8.000  -0.8023   0.02984   0.02109  -0.0133   1.0000   0.0319
  -7.750  -0.7850   0.02846   0.01957  -0.0118   1.0000   0.0347
  -7.500  -0.7665   0.02687   0.01771  -0.0102   1.0000   0.0375
  -7.250  -0.7492   0.02535   0.01608  -0.0086   1.0000   0.0408
  -7.000  -0.7317   0.02431   0.01502  -0.0071   1.0000   0.0453
  -6.750  -0.7133   0.02323   0.01376  -0.0054   1.0000   0.0495
  -6.500  -0.6966   0.02217   0.01273  -0.0037   1.0000   0.0552
  -6.250  -0.6782   0.02133   0.01177  -0.0020   1.0000   0.0616
  -6.000  -0.6610   0.02041   0.01086  -0.0002   1.0000   0.0692
  -5.750  -0.6431   0.01959   0.00994   0.0015   1.0000   0.0784
  -5.500  -0.6253   0.01877   0.00907   0.0033   1.0000   0.0894
  -5.250  -0.6082   0.01788   0.00828   0.0051   1.0000   0.1077
  -5.000  -0.5913   0.01698   0.00760   0.0068   1.0000   0.1416
  -4.750  -0.5741   0.01616   0.00706   0.0085   1.0000   0.1962
  -4.500  -0.5561   0.01552   0.00659   0.0101   1.0000   0.2514
  -4.250  -0.5378   0.01495   0.00621   0.0117   1.0000   0.3053
  -4.000  -0.5212   0.01434   0.00594   0.0137   1.0000   0.3760
  -3.750  -0.5044   0.01384   0.00575   0.0157   1.0000   0.4462
  -3.500  -0.4862   0.01347   0.00556   0.0177   1.0000   0.5020
  -3.250  -0.4670   0.01319   0.00542   0.0194   1.0000   0.5460
  -3.000  -0.4483   0.01296   0.00535   0.0214   1.0000   0.5972
  -2.750  -0.4295   0.01278   0.00535   0.0235   1.0000   0.6500
  -2.500  -0.4097   0.01267   0.00532   0.0253   1.0000   0.6938
  -2.250  -0.3883   0.01260   0.00529   0.0267   1.0000   0.7264
  -2.000  -0.3607   0.01258   0.00529   0.0268   0.9979   0.7567
  -1.750  -0.3209   0.01259   0.00530   0.0245   0.9904   0.7872
  -1.500  -0.2801   0.01264   0.00535   0.0220   0.9833   0.8163
  -1.250  -0.2377   0.01271   0.00540   0.0192   0.9763   0.8435
  -1.000  -0.1945   0.01278   0.00547   0.0163   0.9689   0.8686
  -0.750  -0.1476   0.01288   0.00556   0.0126   0.9626   0.8912
  -0.500  -0.1002   0.01297   0.00563   0.0088   0.9547   0.9095
  -0.250  -0.0496   0.01304   0.00569   0.0043   0.9476   0.9250
   0.000   0.0001   0.01306   0.00571   0.0000   0.9378   0.9378
   0.250   0.0496   0.01304   0.00569  -0.0043   0.9251   0.9476
   0.500   0.1002   0.01297   0.00563  -0.0088   0.9095   0.9547
   0.750   0.1476   0.01288   0.00555  -0.0126   0.8911   0.9626
   1.000   0.1945   0.01278   0.00547  -0.0163   0.8685   0.9689
   1.250   0.2377   0.01270   0.00540  -0.0192   0.8435   0.9763
   1.500   0.2800   0.01264   0.00534  -0.0220   0.8163   0.9834
   1.750   0.3209   0.01259   0.00529  -0.0245   0.7875   0.9904
   2.000   0.3606   0.01257   0.00528  -0.0268   0.7566   0.9979
   2.250   0.3881   0.01260   0.00529  -0.0267   0.7262   1.0000
   2.500   0.4096   0.01267   0.00532  -0.0253   0.6935   1.0000
   2.750   0.4294   0.01278   0.00535  -0.0235   0.6501   1.0000
   3.000   0.4481   0.01295   0.00535  -0.0214   0.5975   1.0000
   3.250   0.4668   0.01319   0.00541  -0.0194   0.5461   1.0000
   3.500   0.4860   0.01347   0.00556  -0.0176   0.5025   1.0000
   3.750   0.5043   0.01383   0.00575  -0.0157   0.4473   1.0000
   4.000   0.5211   0.01433   0.00594  -0.0137   0.3760   1.0000
   4.250   0.5376   0.01495   0.00621  -0.0117   0.3050   1.0000
   4.500   0.5559   0.01551   0.00659  -0.0101   0.2516   1.0000
   4.750   0.5740   0.01616   0.00706  -0.0085   0.1965   1.0000
   5.000   0.5911   0.01698   0.00760  -0.0068   0.1411   1.0000
   5.250   0.6081   0.01787   0.00828  -0.0050   0.1075   1.0000
   5.500   0.6252   0.01877   0.00907  -0.0033   0.0894   1.0000
   5.750   0.6430   0.01959   0.00994  -0.0015   0.0784   1.0000
   6.000   0.6609   0.02042   0.01086   0.0003   0.0691   1.0000
   6.250   0.6781   0.02133   0.01176   0.0020   0.0616   1.0000
   6.500   0.6965   0.02217   0.01273   0.0037   0.0553   1.0000
   6.750   0.7132   0.02323   0.01376   0.0054   0.0495   1.0000
   7.000   0.7316   0.02431   0.01501   0.0071   0.0451   1.0000
   7.250   0.7491   0.02536   0.01609   0.0086   0.0408   1.0000
   7.500   0.7665   0.02688   0.01771   0.0102   0.0374   1.0000
   7.750   0.7851   0.02847   0.01958   0.0118   0.0348   1.0000
   8.000   0.8023   0.02981   0.02106   0.0133   0.0319   1.0000
   8.250   0.8176   0.03160   0.02287   0.0147   0.0296   1.0000
   8.500   0.8330   0.03379   0.02542   0.0165   0.0283   1.0000
   8.750   0.8455   0.03636   0.02842   0.0186   0.0271   1.0000
   9.000   0.8548   0.03895   0.03143   0.0207   0.0259   1.0000
   9.250   0.8609   0.04155   0.03440   0.0230   0.0247   1.0000
   9.500   0.8663   0.04373   0.03684   0.0251   0.0233   1.0000
   9.750   0.8683   0.04614   0.03950   0.0272   0.0226   1.0000
  10.000   0.8657   0.04885   0.04246   0.0295   0.0220   1.0000
  10.250   0.8573   0.05181   0.04565   0.0320   0.0218   1.0000
  10.500   0.8428   0.05477   0.04882   0.0346   0.0217   1.0000
  10.750   0.8243   0.05839   0.05264   0.0359   0.0217   1.0000
  11.000   0.8015   0.06313   0.05761   0.0350   0.0218   1.0000
  11.250   0.7696   0.07054   0.06526   0.0305   0.0223   1.0000
  11.500   0.7050   0.08974   0.08465   0.0158   0.0246   1.0000
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