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RAF 32 MOD AIRFOIL (raf32md-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: RAF 32 MOD AIRFOIL (raf32md-il)
Reynolds number: 100,000
Max Cl/Cd: 61.33 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-raf32md-il-100000-n5.txt
Download as CSV file: xf-raf32md-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: RAF 32 MOD 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
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3984   0.09219   0.08745  -0.0414   1.0000   0.0367
  -8.500  -0.4118   0.08954   0.08488  -0.0400   1.0000   0.0364
  -8.250  -0.4280   0.08711   0.08255  -0.0382   1.0000   0.0362
  -8.000  -0.4329   0.08297   0.07847  -0.0409   0.9962   0.0363
  -7.750  -0.4265   0.07578   0.07129  -0.0498   0.9880   0.0359
  -7.500  -0.4165   0.06470   0.06015  -0.0646   0.9785   0.0353
  -7.250  -0.4108   0.04953   0.04448  -0.0815   0.9683   0.0348
  -7.000  -0.3949   0.04354   0.03800  -0.0867   0.9607   0.0358
  -6.750  -0.3705   0.03898   0.03286  -0.0908   0.9558   0.0384
  -6.500  -0.3489   0.03471   0.02789  -0.0930   0.9494   0.0402
  -6.250  -0.3184   0.03128   0.02371  -0.0955   0.9460   0.0419
  -6.000  -0.2959   0.02904   0.02109  -0.0958   0.9398   0.0443
  -5.750  -0.2656   0.02739   0.01922  -0.0971   0.9360   0.0465
  -5.500  -0.2342   0.02584   0.01736  -0.0983   0.9325   0.0484
  -5.250  -0.2089   0.02479   0.01603  -0.0982   0.9263   0.0515
  -5.000  -0.1761   0.02363   0.01458  -0.0994   0.9229   0.0540
  -4.750  -0.1440   0.02247   0.01328  -0.1004   0.9196   0.0556
  -4.500  -0.1201   0.02168   0.01246  -0.0999   0.9130   0.0576
  -4.250  -0.0871   0.02098   0.01167  -0.1011   0.9093   0.0611
  -4.000  -0.0512   0.02034   0.01088  -0.1028   0.9068   0.0663
  -3.750  -0.0299   0.01985   0.01038  -0.1017   0.8989   0.0701
  -3.500   0.0035   0.01929   0.00973  -0.1029   0.8952   0.0769
  -3.250   0.0396   0.01867   0.00910  -0.1045   0.8925   0.0927
  -3.000   0.0618   0.01826   0.00877  -0.1036   0.8847   0.1214
  -2.750   0.0941   0.01772   0.00837  -0.1047   0.8805   0.1685
  -2.500   0.1286   0.01717   0.00815  -0.1062   0.8775   0.2537
  -2.250   0.1513   0.01700   0.00814  -0.1054   0.8695   0.3184
  -2.000   0.1838   0.01668   0.00792  -0.1064   0.8652   0.3728
  -1.750   0.2175   0.01628   0.00771  -0.1074   0.8619   0.4332
  -1.500   0.2384   0.01613   0.00781  -0.1060   0.8535   0.4990
  -1.250   0.2709   0.01589   0.00766  -0.1066   0.8493   0.5702
  -1.000   0.2970   0.01576   0.00762  -0.1061   0.8427   0.6256
  -0.750   0.3235   0.01548   0.00755  -0.1053   0.8368   0.6964
  -0.500   0.3548   0.01502   0.00735  -0.1052   0.8330   0.7962
  -0.250   0.4021   0.01474   0.00724  -0.1089   0.8270   1.0000
   0.000   0.4328   0.01475   0.00710  -0.1095   0.8208   1.0000
   0.250   0.4640   0.01475   0.00698  -0.1101   0.8151   1.0000
   0.500   0.4900   0.01485   0.00700  -0.1097   0.8070   1.0000
   0.750   0.5243   0.01479   0.00684  -0.1108   0.8023   1.0000
   1.000   0.5470   0.01497   0.00697  -0.1099   0.7929   1.0000
   1.250   0.5801   0.01494   0.00687  -0.1107   0.7877   1.0000
   1.500   0.6033   0.01512   0.00703  -0.1099   0.7783   1.0000
   1.750   0.6359   0.01509   0.00695  -0.1106   0.7727   1.0000
   2.000   0.6589   0.01529   0.00716  -0.1097   0.7630   1.0000
   2.250   0.6906   0.01529   0.00713  -0.1102   0.7568   1.0000
   2.750   0.7421   0.01557   0.00745  -0.1093   0.7393   1.0000
   3.000   0.7689   0.01568   0.00759  -0.1089   0.7307   1.0000
   3.250   0.7944   0.01584   0.00778  -0.1084   0.7215   1.0000
   3.500   0.8242   0.01588   0.00787  -0.1086   0.7137   1.0000
   3.750   0.8476   0.01610   0.00815  -0.1077   0.7032   1.0000
   4.000   0.8746   0.01622   0.00833  -0.1073   0.6939   1.0000
   4.250   0.9025   0.01630   0.00847  -0.1071   0.6842   1.0000
   4.500   0.9269   0.01642   0.00866  -0.1062   0.6706   1.0000
   4.750   0.9526   0.01643   0.00869  -0.1053   0.6539   1.0000
   5.000   0.9747   0.01652   0.00882  -0.1039   0.6333   1.0000
   5.250   0.9978   0.01662   0.00896  -0.1026   0.6120   1.0000
   5.500   1.0190   0.01676   0.00910  -0.1009   0.5863   1.0000
   5.750   1.0387   0.01696   0.00927  -0.0990   0.5565   1.0000
   6.000   1.0573   0.01724   0.00952  -0.0970   0.5241   1.0000
   6.250   1.0757   0.01760   0.00988  -0.0951   0.4918   1.0000
   6.500   1.0923   0.01805   0.01026  -0.0928   0.4533   1.0000
   6.750   1.1051   0.01869   0.01071  -0.0900   0.4015   1.0000
   7.000   1.1130   0.01961   0.01131  -0.0866   0.3371   1.0000
   7.250   1.1169   0.02083   0.01214  -0.0827   0.2678   1.0000
   7.500   1.1174   0.02224   0.01316  -0.0786   0.2054   1.0000
   7.750   1.1196   0.02371   0.01431  -0.0749   0.1565   1.0000
   8.000   1.1236   0.02515   0.01553  -0.0716   0.1195   1.0000
   8.250   1.1300   0.02649   0.01671  -0.0688   0.0957   1.0000
   8.500   1.1368   0.02781   0.01796  -0.0661   0.0808   1.0000
   8.750   1.1449   0.02909   0.01927  -0.0637   0.0704   1.0000
   9.000   1.1506   0.03058   0.02075  -0.0611   0.0620   1.0000
   9.250   1.1582   0.03198   0.02226  -0.0588   0.0545   1.0000
   9.500   1.1628   0.03368   0.02399  -0.0563   0.0483   1.0000
   9.750   1.1708   0.03518   0.02560  -0.0543   0.0427   1.0000
  10.000   1.1744   0.03712   0.02757  -0.0521   0.0394   1.0000
  10.250   1.1840   0.03873   0.02937  -0.0503   0.0359   1.0000
  10.500   1.1923   0.04034   0.03106  -0.0487   0.0328   1.0000
  10.750   1.1983   0.04230   0.03301  -0.0471   0.0307   1.0000
  11.000   1.2098   0.04414   0.03507  -0.0455   0.0288   1.0000
  11.250   1.2213   0.04610   0.03720  -0.0441   0.0271   1.0000
  11.500   1.2304   0.04801   0.03924  -0.0428   0.0255   1.0000
  11.750   1.2375   0.05004   0.04134  -0.0417   0.0243   1.0000
  12.000   1.2450   0.05241   0.04380  -0.0405   0.0231   1.0000
  12.250   1.2543   0.05493   0.04668  -0.0393   0.0221   1.0000
  12.500   1.2610   0.05785   0.04990  -0.0380   0.0214   1.0000
  12.750   1.2638   0.06105   0.05340  -0.0369   0.0208   1.0000
  13.000   1.2627   0.06457   0.05721  -0.0358   0.0204   1.0000
  13.250   1.2575   0.06837   0.06130  -0.0350   0.0200   1.0000
  13.500   1.2495   0.07241   0.06562  -0.0346   0.0196   1.0000
  13.750   1.2392   0.07674   0.07021  -0.0346   0.0193   1.0000
  14.000   1.2264   0.08154   0.07527  -0.0351   0.0191   1.0000
  14.250   1.2119   0.08673   0.08071  -0.0362   0.0189   1.0000
  14.500   1.1958   0.09246   0.08668  -0.0379   0.0187   1.0000
  14.750   1.1769   0.09905   0.09351  -0.0406   0.0187   1.0000
  15.000   1.1548   0.10679   0.10151  -0.0443   0.0188   1.0000
  15.250   1.1268   0.11659   0.11157  -0.0499   0.0191   1.0000
  15.500   1.0889   0.13023   0.12547  -0.0586   0.0200   1.0000
  15.750   1.0515   0.14645   0.14179  -0.0693   0.0209   1.0000
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