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MH 91 14.98% (mh91-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: MH 91 14.98% (mh91-il)
Reynolds number: 100,000
Max Cl/Cd: 40.06 at α=7.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-mh91-il-100000-n5.txt
Download as CSV file: xf-mh91-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 91  14.98%                                   
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -12.750  -0.7090   0.08794   0.08254  -0.0120   1.0000   0.0220
 -12.500  -0.7331   0.07999   0.07444  -0.0176   1.0000   0.0219
 -12.250  -0.7573   0.07320   0.06745  -0.0219   1.0000   0.0218
 -12.000  -0.7786   0.06765   0.06169  -0.0246   1.0000   0.0218
 -11.750  -0.7907   0.06358   0.05747  -0.0258   1.0000   0.0216
 -11.500  -0.8111   0.05923   0.05284  -0.0262   1.0000   0.0217
 -11.250  -0.8224   0.05589   0.04930  -0.0256   1.0000   0.0217
 -11.000  -0.8345   0.05269   0.04582  -0.0241   1.0000   0.0218
 -10.750  -0.8439   0.04979   0.04263  -0.0220   1.0000   0.0219
 -10.500  -0.8474   0.04723   0.03980  -0.0198   1.0000   0.0219
 -10.250  -0.8478   0.04475   0.03701  -0.0174   1.0000   0.0220
 -10.000  -0.8394   0.04252   0.03462  -0.0159   1.0000   0.0222
  -9.750  -0.8277   0.04048   0.03243  -0.0146   1.0000   0.0225
  -9.500  -0.8138   0.03857   0.03037  -0.0135   1.0000   0.0228
  -9.250  -0.7978   0.03675   0.02840  -0.0124   1.0000   0.0232
  -9.000  -0.7798   0.03499   0.02648  -0.0115   1.0000   0.0236
  -8.750  -0.7604   0.03329   0.02464  -0.0107   1.0000   0.0243
  -8.500  -0.7395   0.03169   0.02289  -0.0100   1.0000   0.0249
  -8.250  -0.7181   0.03021   0.02127  -0.0092   1.0000   0.0257
  -8.000  -0.6991   0.02901   0.02011  -0.0084   1.0000   0.0270
  -7.750  -0.6795   0.02795   0.01904  -0.0076   1.0000   0.0284
  -7.500  -0.6600   0.02689   0.01789  -0.0067   1.0000   0.0304
  -7.250  -0.6420   0.02588   0.01696  -0.0058   0.9924   0.0318
  -7.000  -0.6096   0.02472   0.01571  -0.0074   0.9560   0.0342
  -6.750  -0.5815   0.02366   0.01459  -0.0081   0.9302   0.0370
  -6.500  -0.5585   0.02283   0.01368  -0.0075   0.9068   0.0415
  -6.250  -0.5394   0.02211   0.01285  -0.0060   0.8855   0.0471
  -6.000  -0.5226   0.02134   0.01207  -0.0040   0.8665   0.0549
  -5.750  -0.5063   0.02052   0.01129  -0.0020   0.8490   0.0684
  -5.500  -0.4905   0.01959   0.01054   0.0001   0.8327   0.0977
  -5.250  -0.4766   0.01847   0.00984   0.0022   0.8171   0.1693
  -5.000  -0.4628   0.01746   0.00935   0.0044   0.8025   0.2668
  -4.750  -0.4470   0.01676   0.00900   0.0066   0.7885   0.3514
  -4.500  -0.4297   0.01623   0.00875   0.0088   0.7750   0.4218
  -4.250  -0.4104   0.01584   0.00857   0.0107   0.7607   0.4850
  -4.000  -0.3898   0.01556   0.00845   0.0126   0.7472   0.5412
  -3.750  -0.3677   0.01538   0.00838   0.0144   0.7343   0.5892
  -3.500  -0.3438   0.01529   0.00830   0.0160   0.7215   0.6272
  -3.250  -0.3178   0.01527   0.00828   0.0170   0.7076   0.6567
  -3.000  -0.2919   0.01528   0.00822   0.0181   0.6944   0.6829
  -2.750  -0.2652   0.01535   0.00820   0.0192   0.6820   0.7060
  -2.500  -0.2385   0.01542   0.00817   0.0201   0.6686   0.7274
  -2.250  -0.2117   0.01550   0.00815   0.0209   0.6551   0.7466
  -2.000  -0.1844   0.01560   0.00813   0.0216   0.6424   0.7632
  -1.750  -0.1568   0.01571   0.00809   0.0224   0.6301   0.7780
  -1.500  -0.1291   0.01581   0.00809   0.0229   0.6163   0.7920
  -1.250  -0.1025   0.01590   0.00806   0.0236   0.6035   0.8058
  -1.000  -0.0751   0.01601   0.00804   0.0242   0.5912   0.8182
  -0.750  -0.0451   0.01616   0.00806   0.0244   0.5784   0.8284
  -0.500  -0.0187   0.01625   0.00805   0.0250   0.5653   0.8406
  -0.250   0.0122   0.01640   0.00809   0.0250   0.5525   0.8499
   0.000   0.0405   0.01652   0.00807   0.0253   0.5410   0.8603
   0.250   0.0704   0.01666   0.00813   0.0252   0.5275   0.8701
   0.500   0.1016   0.01680   0.00817   0.0249   0.5148   0.8789
   0.750   0.1319   0.01694   0.00818   0.0248   0.5032   0.8881
   1.000   0.1635   0.01706   0.00821   0.0243   0.4907   0.8959
   1.250   0.1968   0.01719   0.00827   0.0234   0.4782   0.9031
   1.500   0.2252   0.01730   0.00827   0.0233   0.4672   0.9114
   1.750   0.2614   0.01743   0.00830   0.0218   0.4552   0.9167
   2.000   0.2886   0.01754   0.00836   0.0218   0.4438   0.9253
   2.250   0.3255   0.01766   0.00839   0.0201   0.4328   0.9298
   2.500   0.3609   0.01779   0.00844   0.0185   0.4216   0.9352
   2.750   0.3890   0.01792   0.00854   0.0183   0.4114   0.9428
   3.000   0.4268   0.01806   0.00857   0.0162   0.4013   0.9468
   3.250   0.4604   0.01820   0.00871   0.0148   0.3906   0.9526
   3.500   0.4916   0.01836   0.00880   0.0139   0.3816   0.9586
   3.750   0.5277   0.01851   0.00894   0.0120   0.3717   0.9632
   4.000   0.5590   0.01870   0.00909   0.0110   0.3630   0.9694
   4.250   0.5938   0.01886   0.00923   0.0093   0.3541   0.9739
   4.500   0.6276   0.01906   0.00943   0.0078   0.3456   0.9790
   4.750   0.6601   0.01926   0.00961   0.0064   0.3374   0.9841
   5.000   0.6946   0.01948   0.00983   0.0047   0.3296   0.9885
   5.250   0.7271   0.01972   0.01009   0.0033   0.3218   0.9934
   5.500   0.7607   0.01996   0.01032   0.0016   0.3145   0.9977
   5.750   0.7871   0.02024   0.01066   0.0013   0.3072   1.0000
   6.000   0.8059   0.02054   0.01090   0.0026   0.3020   1.0000
   6.250   0.8243   0.02089   0.01134   0.0038   0.2957   1.0000
   6.500   0.8423   0.02122   0.01171   0.0051   0.2898   1.0000
   7.000   0.8771   0.02197   0.01253   0.0080   0.2788   1.0000
   7.250   0.8940   0.02236   0.01295   0.0095   0.2735   1.0000
   7.500   0.9110   0.02274   0.01328   0.0111   0.2690   1.0000
   7.750   0.9262   0.02321   0.01389   0.0128   0.2632   1.0000
   8.000   0.9417   0.02364   0.01437   0.0145   0.2579   1.0000
   8.250   0.9579   0.02405   0.01475   0.0162   0.2536   1.0000
   8.500   0.9719   0.02459   0.01541   0.0180   0.2482   1.0000
   8.750   0.9863   0.02508   0.01597   0.0198   0.2429   1.0000
   9.000   1.0020   0.02552   0.01639   0.0215   0.2384   1.0000
   9.250   1.0155   0.02612   0.01710   0.0233   0.2333   1.0000
   9.500   1.0290   0.02669   0.01776   0.0250   0.2280   1.0000
   9.750   1.0444   0.02718   0.01824   0.0266   0.2235   1.0000
  10.000   1.0577   0.02786   0.01902   0.0282   0.2185   1.0000
  10.250   1.0702   0.02855   0.01984   0.0298   0.2133   1.0000
  10.500   1.0845   0.02914   0.02044   0.0312   0.2089   1.0000
  10.750   1.0966   0.02990   0.02127   0.0328   0.2044   1.0000
  11.000   1.1055   0.03079   0.02232   0.0345   0.1995   1.0000
  11.250   1.1154   0.03153   0.02310   0.0362   0.1952   1.0000
  11.500   1.1251   0.03229   0.02386   0.0379   0.1914   1.0000
  11.750   1.1255   0.03358   0.02534   0.0399   0.1869   1.0000
  12.000   1.1301   0.03476   0.02661   0.0413   0.1827   1.0000
  12.250   1.1389   0.03575   0.02761   0.0423   0.1789   1.0000
  12.500   1.1397   0.03745   0.02945   0.0433   0.1749   1.0000
  12.750   1.1391   0.03937   0.03153   0.0439   0.1707   1.0000
  13.000   1.1426   0.04100   0.03321   0.0444   0.1668   1.0000
  13.250   1.1497   0.04246   0.03466   0.0447   0.1633   1.0000
  13.500   1.1397   0.04562   0.03806   0.0444   0.1594   1.0000
  13.750   1.1348   0.04844   0.04103   0.0440   0.1556   1.0000
  14.000   1.1380   0.05048   0.04308   0.0438   0.1521   1.0000
  14.250   1.1345   0.05338   0.04607   0.0431   0.1488   1.0000
  14.500   1.1140   0.05853   0.05145   0.0412   0.1454   1.0000
  14.750   1.1003   0.06304   0.05609   0.0393   0.1420   1.0000
  15.000   1.1055   0.06513   0.05818   0.0388   0.1387   1.0000
  15.250   1.0890   0.07036   0.06353   0.0365   0.1357   1.0000
  15.500   0.9233   0.10108   0.09463   0.0200   0.1287   1.0000
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