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RAF 32 AIRFOIL (raf32-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: RAF 32 AIRFOIL (raf32-il)
Reynolds number: 100,000
Max Cl/Cd: 56.15 at α=8.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-raf32-il-100000.txt
Download as CSV file: xf-raf32-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: RAF 32 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.4037   0.11342   0.10892  -0.0281   1.0000   0.1320
  -8.500  -0.4400   0.11299   0.10862  -0.0282   1.0000   0.1338
  -8.250  -0.4760   0.11241   0.10817  -0.0274   1.0000   0.1343
  -8.000  -0.4271   0.10715   0.10282  -0.0232   1.0000   0.1396
  -7.750  -0.4243   0.10459   0.10027  -0.0248   0.9973   0.1451
  -7.500  -0.4627   0.10095   0.09675  -0.0385   0.9855   0.1500
  -7.250  -0.4080   0.09724   0.09293  -0.0322   0.9858   0.1555
  -6.750  -0.3968   0.09038   0.08608  -0.0399   0.9718   0.1695
  -6.250  -0.4205   0.05366   0.04829  -0.0809   0.9515   0.1072
  -6.000  -0.3955   0.04618   0.03997  -0.0866   0.9463   0.1036
  -5.750  -0.3604   0.04129   0.03417  -0.0914   0.9427   0.1057
  -5.500  -0.3436   0.03898   0.03176  -0.0910   0.9358   0.1081
  -5.250  -0.3124   0.03767   0.03030  -0.0926   0.9311   0.1135
  -5.000  -0.2725   0.03546   0.02740  -0.0957   0.9277   0.1178
  -4.750  -0.2554   0.03405   0.02568  -0.0946   0.9201   0.1215
  -4.500  -0.2215   0.03303   0.02456  -0.0963   0.9155   0.1267
  -4.250  -0.1847   0.03224   0.02339  -0.0982   0.9117   0.1332
  -4.000  -0.1669   0.03140   0.02247  -0.0969   0.9043   0.1373
  -3.750  -0.1319   0.03079   0.02178  -0.0984   0.8998   0.1441
  -3.500  -0.0988   0.03022   0.02106  -0.0996   0.8954   0.1518
  -3.250  -0.0797   0.02991   0.02078  -0.0984   0.8883   0.1582
  -3.000  -0.0437   0.02943   0.02029  -0.1000   0.8840   0.1699
  -2.750  -0.0172   0.02919   0.02009  -0.1000   0.8784   0.1841
  -2.500   0.0056   0.02897   0.01998  -0.0994   0.8719   0.2034
  -2.250   0.0421   0.02853   0.01981  -0.1010   0.8679   0.2619
  -2.000   0.0608   0.02855   0.02006  -0.0998   0.8611   0.3274
  -1.750   0.0870   0.02858   0.02022  -0.0998   0.8551   0.3782
  -1.500   0.1260   0.02850   0.02026  -0.1017   0.8514   0.4267
  -1.250   0.1375   0.02887   0.02074  -0.0993   0.8430   0.4563
  -1.000   0.1694   0.02888   0.02086  -0.0999   0.8379   0.4988
  -0.750   0.2084   0.02878   0.02095  -0.1014   0.8348   0.5567
  -0.500   0.2119   0.02928   0.02159  -0.0976   0.8248   0.5971
  -0.250   0.2468   0.02908   0.02162  -0.0982   0.8208   0.6669
   0.000   0.2633   0.02922   0.02201  -0.0962   0.8136   0.7358
   0.250   0.3134   0.02869   0.02193  -0.1004   0.8085   1.0000
   0.500   0.3575   0.02878   0.02173  -0.1036   0.8048   1.0000
   0.750   0.3714   0.02956   0.02237  -0.1021   0.7959   1.0000
   1.000   0.4053   0.02978   0.02244  -0.1033   0.7907   1.0000
   1.250   0.4501   0.02970   0.02223  -0.1059   0.7878   1.0000
   1.500   0.4539   0.03077   0.02322  -0.1029   0.7767   1.0000
   1.750   0.4942   0.03076   0.02312  -0.1048   0.7732   1.0000
   2.000   0.5041   0.03173   0.02403  -0.1026   0.7633   1.0000
   2.250   0.5400   0.03179   0.02403  -0.1038   0.7586   1.0000
   2.500   0.5847   0.03155   0.02374  -0.1061   0.7560   1.0000
   2.750   0.5860   0.03287   0.02504  -0.1029   0.7441   1.0000
   3.000   0.6295   0.03257   0.02471  -0.1049   0.7411   1.0000
   3.250   0.6327   0.03393   0.02606  -0.1020   0.7296   1.0000
   3.500   0.6743   0.03363   0.02577  -0.1036   0.7262   1.0000
   3.750   0.7184   0.03319   0.02533  -0.1055   0.7236   1.0000
   4.000   0.7203   0.03464   0.02680  -0.1025   0.7112   1.0000
   4.250   0.7669   0.03395   0.02615  -0.1045   0.7091   1.0000
   4.500   0.7674   0.03555   0.02776  -0.1014   0.6962   1.0000
   4.750   0.7846   0.03632   0.02857  -0.1001   0.6873   1.0000
   5.000   0.8249   0.03552   0.02783  -0.1009   0.6812   1.0000
   5.250   0.8895   0.03300   0.02538  -0.1039   0.6794   1.0000
   5.500   0.9586   0.03063   0.02313  -0.1082   0.6780   1.0000
   5.750   0.9585   0.03189   0.02444  -0.1042   0.6651   1.0000
   6.000   1.0228   0.03004   0.02273  -0.1084   0.6630   1.0000
   6.250   1.0253   0.03111   0.02386  -0.1046   0.6508   1.0000
   6.500   1.1030   0.02854   0.02146  -0.1105   0.6476   1.0000
   6.750   1.1284   0.02810   0.02111  -0.1092   0.6353   1.0000
   7.000   1.1774   0.02636   0.01945  -0.1107   0.6225   1.0000
   7.250   1.2185   0.02514   0.01831  -0.1114   0.6082   1.0000
   7.500   1.2486   0.02435   0.01757  -0.1105   0.5912   1.0000
   7.750   1.2720   0.02384   0.01711  -0.1087   0.5728   1.0000
   8.000   1.2929   0.02350   0.01683  -0.1066   0.5540   1.0000
   8.250   1.3084   0.02330   0.01667  -0.1036   0.5336   1.0000
   8.500   1.3090   0.02353   0.01696  -0.0984   0.5118   1.0000
   8.750   1.3159   0.02364   0.01703  -0.0943   0.4860   1.0000
   9.000   1.3186   0.02402   0.01735  -0.0897   0.4563   1.0000
   9.250   1.3166   0.02476   0.01802  -0.0848   0.4223   1.0000
   9.500   1.3109   0.02584   0.01892  -0.0797   0.3807   1.0000
   9.750   1.2995   0.02744   0.02027  -0.0744   0.3293   1.0000
  10.000   1.2823   0.02972   0.02212  -0.0690   0.2728   1.0000
  10.250   1.2628   0.03260   0.02455  -0.0642   0.2216   1.0000
  10.500   1.2470   0.03563   0.02718  -0.0602   0.1820   1.0000
  10.750   1.2383   0.03838   0.02966  -0.0571   0.1541   1.0000
  11.000   1.2355   0.04081   0.03189  -0.0547   0.1363   1.0000
  11.250   1.2367   0.04303   0.03398  -0.0526   0.1227   1.0000
  11.500   1.2418   0.04504   0.03586  -0.0508   0.1119   1.0000
  11.750   1.2517   0.04678   0.03763  -0.0492   0.1024   1.0000
  12.000   1.2678   0.04837   0.03913  -0.0479   0.0942   1.0000
  12.250   1.2982   0.04965   0.04013  -0.0474   0.0857   1.0000
  12.500   1.3126   0.05137   0.04210  -0.0462   0.0810   1.0000
  12.750   1.3645   0.05299   0.04348  -0.0475   0.0736   1.0000
  13.000   1.3718   0.05505   0.04588  -0.0459   0.0711   1.0000
  13.250   1.3892   0.05723   0.04827  -0.0450   0.0679   1.0000
  13.500   1.4102   0.05961   0.05077  -0.0446   0.0653   1.0000
  13.750   1.4426   0.06339   0.05465  -0.0453   0.0622   1.0000
  14.000   1.4340   0.06619   0.05780  -0.0429   0.0614   1.0000
  14.250   1.4243   0.06934   0.06130  -0.0408   0.0605   1.0000
  14.500   1.4146   0.07293   0.06523  -0.0390   0.0598   1.0000
  14.750   1.4026   0.07690   0.06952  -0.0375   0.0594   1.0000
  15.000   1.3874   0.08126   0.07419  -0.0364   0.0593   1.0000
  15.250   1.3693   0.08598   0.07922  -0.0357   0.0592   1.0000
  15.500   1.3486   0.09115   0.08468  -0.0356   0.0593   1.0000
  15.750   1.3252   0.09678   0.09059  -0.0361   0.0595   1.0000
  16.000   1.2994   0.10302   0.09709  -0.0374   0.0598   1.0000
  16.250   1.2725   0.10987   0.10418  -0.0396   0.0602   1.0000
  16.500   1.2444   0.11741   0.11194  -0.0427   0.0607   1.0000
  16.750   1.2164   0.12570   0.12041  -0.0468   0.0613   1.0000
  17.000   1.1915   0.13435   0.12920  -0.0513   0.0619   1.0000
  17.250   1.1721   0.14301   0.13795  -0.0557   0.0626   1.0000
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