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MH 24 9.01% (mh24-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: MH 24 9.01% (mh24-il)
Reynolds number: 100,000
Max Cl/Cd: 50.87 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-mh24-il-100000.txt
Download as CSV file: xf-mh24-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 24  9.01%                                    
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3979   0.08928   0.08481  -0.0319   1.0000   0.0951
  -8.750  -0.4069   0.08581   0.08140  -0.0325   1.0000   0.0984
  -8.500  -0.4290   0.08234   0.07802  -0.0346   1.0000   0.1006
  -8.250  -0.4567   0.07884   0.07461  -0.0367   1.0000   0.1011
  -8.000  -0.4828   0.07629   0.07210  -0.0353   1.0000   0.1013
  -7.750  -0.5113   0.07404   0.06985  -0.0329   1.0000   0.1015
  -7.500  -0.4792   0.06859   0.06450  -0.0304   1.0000   0.1065
  -7.250  -0.4943   0.06586   0.06180  -0.0280   1.0000   0.1083
  -7.000  -0.5116   0.06278   0.05871  -0.0262   1.0000   0.1113
  -6.750  -0.5488   0.06070   0.05639  -0.0246   1.0000   0.1149
  -6.500  -0.5995   0.06753   0.06265  -0.0218   1.0000   0.1149
  -6.000  -0.5858   0.05992   0.05520  -0.0177   1.0000   0.1232
  -5.750  -0.5870   0.05677   0.05189  -0.0156   1.0000   0.1321
  -5.500  -0.5853   0.05418   0.04910  -0.0135   1.0000   0.1440
  -5.250  -0.5752   0.05138   0.04624  -0.0113   1.0000   0.1514
  -5.000  -0.5696   0.04893   0.04360  -0.0091   1.0000   0.1670
  -4.500  -0.5216   0.03535   0.02769  -0.0031   1.0000   0.0485
  -4.250  -0.5049   0.03176   0.02384  -0.0013   1.0000   0.0444
  -4.000  -0.4837   0.02875   0.02014   0.0012   1.0000   0.0394
  -3.750  -0.4602   0.02753   0.01844   0.0033   1.0000   0.0370
  -3.500  -0.4370   0.02562   0.01622   0.0047   1.0000   0.0364
  -3.250  -0.4132   0.02371   0.01409   0.0060   1.0000   0.0363
  -3.000  -0.3907   0.02164   0.01201   0.0072   1.0000   0.0403
  -2.750  -0.1441   0.01663   0.01033  -0.0280   1.0000   1.0000
  -2.500  -0.1354   0.01646   0.00994  -0.0252   1.0000   1.0000
  -2.250  -0.1261   0.01633   0.00961  -0.0224   1.0000   1.0000
  -2.000  -0.1163   0.01623   0.00935  -0.0196   1.0000   1.0000
  -1.750  -0.1060   0.01617   0.00913  -0.0169   1.0000   1.0000
  -1.500  -0.0954   0.01614   0.00895  -0.0143   1.0000   1.0000
  -1.250  -0.0847   0.01614   0.00882  -0.0116   1.0000   1.0000
  -1.000  -0.0738   0.01616   0.00869  -0.0090   1.0000   1.0000
  -0.750  -0.0628   0.01621   0.00863  -0.0065   1.0000   1.0000
  -0.500  -0.0518   0.01629   0.00862  -0.0039   1.0000   1.0000
  -0.250  -0.0406   0.01639   0.00864  -0.0015   1.0000   1.0000
   0.000  -0.0292   0.01653   0.00870   0.0009   1.0000   1.0000
   0.250  -0.0177   0.01670   0.00879   0.0032   1.0000   1.0000
   0.500  -0.0061   0.01690   0.00894   0.0054   1.0000   1.0000
   0.750   0.0058   0.01715   0.00911   0.0075   1.0000   1.0000
   1.000   0.0275   0.01752   0.00945   0.0075   0.9977   1.0000
   1.250   0.0827   0.01822   0.01014   0.0010   0.9860   1.0000
   1.500   0.1361   0.01882   0.01076  -0.0050   0.9737   1.0000
   1.750   0.1883   0.01928   0.01125  -0.0105   0.9605   1.0000
   2.000   0.2397   0.01961   0.01165  -0.0157   0.9470   1.0000
   2.250   0.2916   0.01979   0.01195  -0.0207   0.9332   1.0000
   2.500   0.3446   0.01979   0.01207  -0.0257   0.9191   1.0000
   2.750   0.3993   0.01959   0.01203  -0.0307   0.9047   1.0000
   3.000   0.4581   0.01912   0.01176  -0.0360   0.8902   1.0000
   3.250   0.5077   0.01849   0.01141  -0.0394   0.8722   1.0000
   3.500   0.5589   0.01756   0.01072  -0.0425   0.8529   1.0000
   3.750   0.5986   0.01657   0.00996  -0.0432   0.8288   1.0000
   4.000   0.6383   0.01551   0.00916  -0.0435   0.7981   1.0000
   4.250   0.6773   0.01464   0.00841  -0.0437   0.7501   1.0000
   4.750   0.7366   0.01448   0.00784  -0.0414   0.5881   1.0000
   5.000   0.7506   0.01513   0.00809  -0.0381   0.5011   1.0000
   5.250   0.7608   0.01595   0.00850  -0.0344   0.4185   1.0000
   5.500   0.7694   0.01689   0.00914  -0.0308   0.3399   1.0000
   5.750   0.7770   0.01798   0.00981  -0.0271   0.2662   1.0000
   6.000   0.7845   0.01925   0.01066  -0.0235   0.2026   1.0000
   6.250   0.7923   0.02062   0.01166  -0.0201   0.1497   1.0000
   6.500   0.8029   0.02215   0.01300  -0.0169   0.1149   1.0000
   6.750   0.8159   0.02370   0.01442  -0.0142   0.0916   1.0000
   7.000   0.8323   0.02529   0.01601  -0.0120   0.0761   1.0000
   7.250   0.8555   0.02766   0.01840  -0.0109   0.0673   1.0000
   7.500   0.8779   0.02985   0.02079  -0.0095   0.0606   1.0000
   7.750   0.8936   0.03211   0.02333  -0.0073   0.0529   1.0000
   8.000   0.9101   0.03483   0.02633  -0.0049   0.0484   1.0000
   8.250   0.9178   0.03824   0.03009  -0.0019   0.0441   1.0000
   8.500   0.9225   0.04043   0.03281   0.0021   0.0405   1.0000
   8.750   0.9243   0.04388   0.03673   0.0061   0.0393   1.0000
   9.000   0.9216   0.04759   0.04090   0.0103   0.0395   1.0000
   9.250   0.9137   0.05152   0.04526   0.0146   0.0400   1.0000
   9.500   0.9028   0.05542   0.04950   0.0186   0.0408   1.0000
   9.750   0.8886   0.05918   0.05354   0.0225   0.0415   1.0000
  10.000   0.8741   0.06252   0.05704   0.0260   0.0426   1.0000
  10.250   0.8571   0.06605   0.06071   0.0289   0.0434   1.0000
  10.500   0.8350   0.06978   0.06460   0.0310   0.0434   1.0000
  10.750   0.8250   0.07430   0.06915   0.0315   0.0447   1.0000
  11.000   0.8028   0.07886   0.07384   0.0310   0.0447   1.0000
  11.250   0.7071   0.07642   0.07176   0.0314   0.0448   1.0000
  11.500   0.6452   0.09329   0.08887   0.0194   0.0603   1.0000
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