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RAF 38 AIRFOIL (raf38-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: RAF 38 AIRFOIL (raf38-il)
Reynolds number: 1,000,000
Max Cl/Cd: 114.68 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-raf38-il-1000000.txt
Download as CSV file: xf-raf38-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: RAF 38 AIRFOIL                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -17.250  -0.9501   0.09311   0.09065  -0.0379   1.0000   0.0134
 -17.000  -1.0062   0.07984   0.07721  -0.0457   1.0000   0.0132
 -16.750  -1.0632   0.06642   0.06355  -0.0539   1.0000   0.0128
 -16.500  -1.0981   0.05648   0.05344  -0.0607   1.0000   0.0129
 -16.250  -1.1211   0.04880   0.04559  -0.0663   1.0000   0.0129
 -16.000  -1.1395   0.04233   0.03894  -0.0711   1.0000   0.0129
 -15.750  -1.1475   0.03809   0.03456  -0.0737   1.0000   0.0130
 -15.500  -1.1502   0.03503   0.03140  -0.0750   1.0000   0.0132
 -15.250  -1.1562   0.03212   0.02836  -0.0754   1.0000   0.0133
 -15.000  -1.1527   0.03041   0.02656  -0.0749   1.0000   0.0136
 -14.750  -1.1534   0.02860   0.02464  -0.0737   1.0000   0.0137
 -14.500  -1.1510   0.02723   0.02316  -0.0719   1.0000   0.0139
 -14.250  -1.1482   0.02603   0.02186  -0.0696   1.0000   0.0141
 -14.000  -1.1429   0.02511   0.02085  -0.0670   1.0000   0.0143
 -13.750  -1.1401   0.02423   0.01987  -0.0637   1.0000   0.0144
 -13.500  -1.1325   0.02359   0.01916  -0.0608   1.0000   0.0146
 -13.250  -1.1318   0.02227   0.01774  -0.0572   1.0000   0.0150
 -13.000  -1.1238   0.02133   0.01674  -0.0545   1.0000   0.0154
 -12.750  -1.1120   0.02061   0.01597  -0.0522   1.0000   0.0158
 -12.500  -1.0975   0.02006   0.01536  -0.0502   1.0000   0.0162
 -12.250  -1.0833   0.01948   0.01472  -0.0480   1.0000   0.0166
 -12.000  -1.0688   0.01892   0.01410  -0.0459   1.0000   0.0170
 -11.750  -1.0542   0.01836   0.01348  -0.0437   1.0000   0.0174
 -11.500  -1.0379   0.01795   0.01301  -0.0418   1.0000   0.0178
 -11.250  -1.0280   0.01712   0.01210  -0.0389   1.0000   0.0184
 -11.000  -1.0005   0.01642   0.01137  -0.0394   0.9987   0.0192
 -10.750  -0.9669   0.01589   0.01080  -0.0410   0.9964   0.0200
 -10.500  -0.9327   0.01540   0.01026  -0.0427   0.9939   0.0209
 -10.250  -0.9011   0.01494   0.00973  -0.0438   0.9903   0.0216
 -10.000  -0.8696   0.01422   0.00900  -0.0450   0.9862   0.0231
  -9.750  -0.8344   0.01380   0.00856  -0.0468   0.9830   0.0243
  -9.500  -0.8045   0.01343   0.00815  -0.0474   0.9758   0.0254
  -9.250  -0.7695   0.01285   0.00754  -0.0492   0.9708   0.0271
  -9.000  -0.7344   0.01252   0.00722  -0.0509   0.9624   0.0288
  -8.750  -0.6946   0.01226   0.00691  -0.0535   0.9532   0.0304
  -8.500  -0.6579   0.01181   0.00645  -0.0557   0.9363   0.0327
  -8.250  -0.6244   0.01166   0.00624  -0.0568   0.9112   0.0346
  -8.000  -0.5971   0.01159   0.00604  -0.0566   0.8848   0.0359
  -7.750  -0.5743   0.01130   0.00566  -0.0556   0.8625   0.0379
  -7.500  -0.5493   0.01124   0.00554  -0.0550   0.8455   0.0396
  -7.250  -0.5238   0.01118   0.00541  -0.0544   0.8312   0.0412
  -7.000  -0.4979   0.01112   0.00529  -0.0540   0.8191   0.0424
  -6.750  -0.4745   0.01081   0.00490  -0.0531   0.8084   0.0443
  -6.500  -0.4496   0.01063   0.00469  -0.0525   0.7981   0.0461
  -6.250  -0.4239   0.01050   0.00452  -0.0520   0.7881   0.0477
  -5.750  -0.3720   0.01030   0.00421  -0.0511   0.7683   0.0503
  -5.500  -0.3472   0.01008   0.00391  -0.0504   0.7595   0.0517
  -5.250  -0.3227   0.00975   0.00356  -0.0497   0.7511   0.0541
  -5.000  -0.2970   0.00960   0.00337  -0.0492   0.7439   0.0559
  -4.750  -0.2707   0.00944   0.00319  -0.0489   0.7369   0.0576
  -4.500  -0.2445   0.00932   0.00302  -0.0484   0.7301   0.0591
  -4.250  -0.2178   0.00920   0.00287  -0.0481   0.7238   0.0601
  -4.000  -0.1920   0.00899   0.00262  -0.0476   0.7171   0.0626
  -3.750  -0.1661   0.00882   0.00242  -0.0472   0.7113   0.0654
  -3.500  -0.1394   0.00867   0.00226  -0.0468   0.7053   0.0680
  -3.250  -0.1128   0.00857   0.00213  -0.0465   0.6993   0.0704
  -3.000  -0.0862   0.00844   0.00198  -0.0461   0.6935   0.0746
  -2.750  -0.0598   0.00826   0.00184  -0.0458   0.6875   0.0833
  -2.500  -0.0363   0.00785   0.00168  -0.0450   0.6818   0.1501
  -2.250  -0.0108   0.00761   0.00160  -0.0445   0.6766   0.1964
  -2.000   0.0154   0.00744   0.00152  -0.0442   0.6709   0.2256
  -1.750   0.0409   0.00726   0.00144  -0.0437   0.6652   0.2632
  -1.500   0.0655   0.00695   0.00137  -0.0431   0.6597   0.3334
  -1.250   0.0901   0.00667   0.00132  -0.0424   0.6538   0.4064
  -1.000   0.1148   0.00648   0.00129  -0.0418   0.6482   0.4674
  -0.750   0.1404   0.00629   0.00127  -0.0413   0.6429   0.5169
  -0.500   0.1653   0.00612   0.00125  -0.0406   0.6370   0.5700
  -0.250   0.1890   0.00594   0.00124  -0.0397   0.6311   0.6333
   0.000   0.2134   0.00576   0.00125  -0.0388   0.6250   0.6914
   0.250   0.2379   0.00566   0.00126  -0.0380   0.6187   0.7364
   0.500   0.2630   0.00558   0.00129  -0.0372   0.6127   0.7740
   0.750   0.2876   0.00548   0.00131  -0.0363   0.6050   0.8150
   1.000   0.3125   0.00541   0.00134  -0.0355   0.5964   0.8558
   1.250   0.3397   0.00538   0.00139  -0.0351   0.5864   0.8912
   1.500   0.3722   0.00541   0.00147  -0.0359   0.5759   0.9246
   1.750   0.4108   0.00552   0.00157  -0.0381   0.5640   0.9456
   2.250   0.4816   0.00577   0.00172  -0.0412   0.5360   0.9639
   2.500   0.5146   0.00592   0.00180  -0.0422   0.5178   0.9709
   2.750   0.5534   0.00608   0.00190  -0.0445   0.5022   0.9742
   3.000   0.5898   0.00625   0.00201  -0.0464   0.4874   0.9789
   3.250   0.6226   0.00643   0.00213  -0.0474   0.4721   0.9833
   3.500   0.6594   0.00660   0.00222  -0.0494   0.4528   0.9853
   3.750   0.6950   0.00676   0.00232  -0.0512   0.4390   0.9877
   4.000   0.7294   0.00693   0.00244  -0.0527   0.4262   0.9905
   4.500   0.7983   0.00724   0.00266  -0.0558   0.3981   0.9952
   4.750   0.8344   0.00740   0.00276  -0.0577   0.3818   0.9974
   5.000   0.8716   0.00760   0.00288  -0.0599   0.3590   0.9996
   5.250   0.8957   0.00782   0.00302  -0.0593   0.3355   1.0000
   5.500   0.9138   0.00816   0.00320  -0.0576   0.3006   1.0000
   5.750   0.9293   0.00866   0.00347  -0.0553   0.2565   1.0000
   6.000   0.9453   0.00912   0.00377  -0.0532   0.2223   1.0000
   6.250   0.9616   0.00957   0.00407  -0.0511   0.1927   1.0000
   6.500   0.9765   0.01010   0.00441  -0.0487   0.1575   1.0000
   6.750   0.9857   0.01093   0.00493  -0.0455   0.1027   1.0000
   7.000   0.9993   0.01150   0.00535  -0.0429   0.0792   1.0000
   7.250   1.0170   0.01185   0.00568  -0.0411   0.0714   1.0000
   7.500   1.0342   0.01223   0.00602  -0.0391   0.0656   1.0000
   7.750   1.0531   0.01250   0.00631  -0.0375   0.0626   1.0000
   8.000   1.0717   0.01280   0.00661  -0.0358   0.0599   1.0000
   8.250   1.0888   0.01316   0.00697  -0.0339   0.0566   1.0000
   8.500   1.1057   0.01353   0.00735  -0.0320   0.0536   1.0000
   8.750   1.1250   0.01378   0.00762  -0.0305   0.0517   1.0000
   9.000   1.1426   0.01410   0.00795  -0.0287   0.0492   1.0000
   9.250   1.1576   0.01454   0.00837  -0.0265   0.0460   1.0000
   9.500   1.1749   0.01485   0.00872  -0.0248   0.0440   1.0000
   9.750   1.1897   0.01515   0.00903  -0.0225   0.0416   1.0000
  10.000   1.2009   0.01557   0.00943  -0.0197   0.0389   1.0000
  10.250   1.2142   0.01596   0.00985  -0.0173   0.0365   1.0000
  10.500   1.2278   0.01639   0.01028  -0.0151   0.0340   1.0000
  10.750   1.2392   0.01697   0.01085  -0.0127   0.0314   1.0000
  11.000   1.2535   0.01745   0.01137  -0.0108   0.0295   1.0000
  11.250   1.2655   0.01810   0.01201  -0.0088   0.0278   1.0000
  11.500   1.2760   0.01887   0.01282  -0.0067   0.0260   1.0000
  11.750   1.2892   0.01954   0.01354  -0.0051   0.0248   1.0000
  12.000   1.3009   0.02035   0.01437  -0.0035   0.0237   1.0000
  12.250   1.3099   0.02139   0.01544  -0.0018   0.0224   1.0000
  12.500   1.3190   0.02249   0.01659  -0.0003   0.0215   1.0000
  12.750   1.3303   0.02350   0.01767   0.0009   0.0208   1.0000
  13.000   1.3422   0.02450   0.01870   0.0019   0.0198   1.0000
  13.250   1.3502   0.02584   0.02009   0.0030   0.0191   1.0000
  13.500   1.3557   0.02745   0.02174   0.0042   0.0184   1.0000
  13.750   1.3611   0.02912   0.02348   0.0052   0.0177   1.0000
  14.000   1.3693   0.03061   0.02504   0.0059   0.0174   1.0000
  14.250   1.3773   0.03215   0.02664   0.0066   0.0169   1.0000
  14.500   1.3835   0.03387   0.02843   0.0073   0.0165   1.0000
  14.750   1.3901   0.03560   0.03022   0.0078   0.0160   1.0000
  15.000   1.3929   0.03773   0.03242   0.0083   0.0156   1.0000
  15.250   1.3916   0.04030   0.03505   0.0087   0.0151   1.0000
  15.500   1.3867   0.04334   0.03817   0.0090   0.0147   1.0000
  15.750   1.3906   0.04555   0.04046   0.0092   0.0145   1.0000
  16.000   1.3908   0.04822   0.04322   0.0092   0.0144   1.0000
  16.250   1.3946   0.05057   0.04565   0.0091   0.0140   1.0000
  16.500   1.3957   0.05330   0.04846   0.0089   0.0137   1.0000
  16.750   1.3955   0.05622   0.05146   0.0085   0.0135   1.0000
  17.000   1.3943   0.05933   0.05465   0.0080   0.0133   1.0000
  17.250   1.3933   0.06251   0.05791   0.0074   0.0130   1.0000
  17.500   1.3895   0.06612   0.06160   0.0066   0.0128   1.0000
  17.750   1.3841   0.06998   0.06555   0.0057   0.0126   1.0000
  18.000   1.3767   0.07421   0.06985   0.0045   0.0123   1.0000
  18.250   1.3701   0.07840   0.07413   0.0033   0.0123   1.0000
  18.500   1.3563   0.08365   0.07947   0.0017   0.0121   1.0000
  18.750   1.3458   0.08851   0.08443   0.0001   0.0120   1.0000
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