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MH 42 8.94% (mh42-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: MH 42 8.94% (mh42-il)
Reynolds number: 100,000
Max Cl/Cd: 49.92 at α=6.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-mh42-il-100000.txt
Download as CSV file: xf-mh42-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 42  8.94%                                    
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.4083   0.10082   0.09643  -0.0059   1.0000   0.0945
  -9.000  -0.4166   0.09706   0.09272  -0.0090   1.0000   0.0982
  -8.750  -0.4334   0.09331   0.08905  -0.0138   1.0000   0.0993
  -8.500  -0.4077   0.08856   0.08429  -0.0101   1.0000   0.1050
  -8.250  -0.4123   0.08469   0.08048  -0.0123   1.0000   0.1106
  -8.000  -0.4314   0.08069   0.07657  -0.0174   1.0000   0.1124
  -7.750  -0.4156   0.07594   0.07185  -0.0152   1.0000   0.1168
  -7.500  -0.4142   0.07210   0.06805  -0.0160   1.0000   0.1217
  -7.250  -0.4367   0.06784   0.06388  -0.0217   1.0000   0.1252
  -7.000  -0.4634   0.06206   0.05797  -0.0307   1.0000   0.1266
  -6.750  -0.5057   0.06778   0.06320  -0.0328   1.0000   0.1268
  -6.500  -0.4813   0.06455   0.06028  -0.0269   1.0000   0.1335
  -6.250  -0.4308   0.04925   0.04535  -0.0276   1.0000   0.1458
  -6.000  -0.4321   0.04429   0.04030  -0.0302   1.0000   0.1563
  -5.750  -0.4568   0.04006   0.03424  -0.0363   1.0000   0.0566
  -5.500  -0.4418   0.03598   0.02911  -0.0341   1.0000   0.0478
  -5.250  -0.4284   0.03195   0.02485  -0.0326   1.0000   0.0465
  -5.000  -0.4139   0.02880   0.02134  -0.0306   1.0000   0.0455
  -4.750  -0.3982   0.02629   0.01843  -0.0284   1.0000   0.0452
  -4.500  -0.3813   0.02417   0.01593  -0.0262   1.0000   0.0458
  -4.250  -0.3634   0.02258   0.01395  -0.0240   1.0000   0.0476
  -4.000  -0.3471   0.02068   0.01211  -0.0225   1.0000   0.0540
  -3.750  -0.3294   0.01923   0.01060  -0.0207   1.0000   0.0639
  -3.500  -0.3119   0.01813   0.00943  -0.0189   1.0000   0.0861
  -3.250  -0.2950   0.01690   0.00848  -0.0174   1.0000   0.1249
  -3.000  -0.2788   0.01531   0.00764  -0.0159   1.0000   0.2402
  -2.750  -0.2547   0.01436   0.00744  -0.0162   0.9965   0.3930
  -2.500  -0.2211   0.01332   0.00755  -0.0170   0.9870   0.6482
  -2.250  -0.1688   0.01299   0.00777  -0.0189   0.9834   0.9124
  -2.000  -0.0792   0.01303   0.00731  -0.0309   0.9840   1.0000
  -1.750  -0.0278   0.01313   0.00709  -0.0364   0.9727   1.0000
  -1.500   0.0234   0.01321   0.00690  -0.0416   0.9621   1.0000
  -1.250   0.0795   0.01323   0.00667  -0.0475   0.9533   1.0000
  -1.000   0.1289   0.01321   0.00648  -0.0520   0.9424   1.0000
  -0.750   0.1722   0.01319   0.00632  -0.0552   0.9297   1.0000
  -0.500   0.2106   0.01320   0.00619  -0.0573   0.9161   1.0000
  -0.250   0.2432   0.01323   0.00613  -0.0581   0.9019   1.0000
   0.000   0.2710   0.01331   0.00612  -0.0579   0.8874   1.0000
   0.250   0.2951   0.01342   0.00615  -0.0568   0.8726   1.0000
   0.500   0.3168   0.01358   0.00623  -0.0553   0.8573   1.0000
   0.750   0.3383   0.01373   0.00632  -0.0538   0.8424   1.0000
   1.000   0.3597   0.01389   0.00642  -0.0521   0.8278   1.0000
   1.250   0.3812   0.01404   0.00653  -0.0505   0.8134   1.0000
   1.500   0.4029   0.01419   0.00665  -0.0489   0.7991   1.0000
   1.750   0.4250   0.01435   0.00676  -0.0473   0.7848   1.0000
   2.000   0.4473   0.01449   0.00688  -0.0458   0.7703   1.0000
   2.250   0.4700   0.01464   0.00699  -0.0443   0.7558   1.0000
   2.500   0.4930   0.01477   0.00715  -0.0429   0.7410   1.0000
   2.750   0.5163   0.01490   0.00727  -0.0415   0.7260   1.0000
   3.000   0.5398   0.01502   0.00737  -0.0401   0.7108   1.0000
   3.250   0.5636   0.01512   0.00746  -0.0388   0.6954   1.0000
   3.500   0.5873   0.01526   0.00762  -0.0375   0.6781   1.0000
   3.750   0.6112   0.01539   0.00781  -0.0363   0.6600   1.0000
   4.000   0.6355   0.01547   0.00789  -0.0350   0.6422   1.0000
   4.250   0.6596   0.01557   0.00802  -0.0338   0.6227   1.0000
   4.500   0.6838   0.01566   0.00813  -0.0326   0.6020   1.0000
   4.750   0.7079   0.01575   0.00831  -0.0313   0.5796   1.0000
   5.000   0.7321   0.01583   0.00837  -0.0301   0.5565   1.0000
   5.250   0.7559   0.01593   0.00849  -0.0288   0.5306   1.0000
   5.500   0.7793   0.01608   0.00867  -0.0276   0.5010   1.0000
   5.750   0.8021   0.01627   0.00889  -0.0263   0.4678   1.0000
   6.000   0.8244   0.01654   0.00914  -0.0250   0.4314   1.0000
   6.250   0.8457   0.01694   0.00948  -0.0237   0.3891   1.0000
   6.500   0.8657   0.01752   0.01001  -0.0223   0.3419   1.0000
   6.750   0.8843   0.01835   0.01066  -0.0209   0.2898   1.0000
   7.000   0.9013   0.01945   0.01152  -0.0194   0.2369   1.0000
   7.250   0.9168   0.02084   0.01259  -0.0180   0.1902   1.0000
   7.500   0.9320   0.02241   0.01392  -0.0164   0.1501   1.0000
   7.750   0.9475   0.02402   0.01543  -0.0149   0.1172   1.0000
   8.000   0.9634   0.02605   0.01728  -0.0134   0.0957   1.0000
   8.250   0.9811   0.02794   0.01923  -0.0119   0.0792   1.0000
   8.500   0.9999   0.03014   0.02145  -0.0107   0.0677   1.0000
   8.750   1.0211   0.03321   0.02444  -0.0099   0.0594   1.0000
   9.000   1.0366   0.03479   0.02651  -0.0082   0.0516   1.0000
   9.250   1.0538   0.03892   0.03079  -0.0072   0.0469   1.0000
   9.500   1.0641   0.04126   0.03366  -0.0052   0.0422   1.0000
   9.750   1.0750   0.04379   0.03635  -0.0038   0.0384   1.0000
  10.000   1.0805   0.04877   0.04161  -0.0025   0.0368   1.0000
  10.250   1.0781   0.05384   0.04711  -0.0007   0.0365   1.0000
  10.500   1.0714   0.05827   0.05192   0.0011   0.0364   1.0000
  10.750   1.0584   0.06209   0.05604   0.0031   0.0362   1.0000
  11.000   1.0435   0.06593   0.06010   0.0049   0.0363   1.0000
  11.500   0.9179   0.06621   0.06137   0.0076   0.0392   1.0000
  11.750   0.8781   0.07430   0.06973   0.0038   0.0409   1.0000
  12.000   0.8451   0.08285   0.07845  -0.0009   0.0425   1.0000
  12.250   0.8171   0.09172   0.08742  -0.0056   0.0448   1.0000
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