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MH 23 8% (mh23-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: MH 23 8% (mh23-il)
Reynolds number: 100,000
Max Cl/Cd: 49.99 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-mh23-il-100000.txt
Download as CSV file: xf-mh23-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 23  8%                                       
  
 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  -0.4955   0.10216   0.09726  -0.0253   1.0000   0.0806
  -9.000  -0.5100   0.09915   0.09434  -0.0305   1.0000   0.0814
  -8.750  -0.5267   0.09583   0.09110  -0.0350   1.0000   0.0816
  -8.500  -0.4913   0.09100   0.08624  -0.0268   1.0000   0.0869
  -8.250  -0.4948   0.08768   0.08299  -0.0279   1.0000   0.0900
  -8.000  -0.5084   0.08448   0.07987  -0.0301   1.0000   0.0922
  -7.750  -0.5301   0.08175   0.07719  -0.0316   1.0000   0.0938
  -7.500  -0.5555   0.07977   0.07509  -0.0325   1.0000   0.0948
  -7.250  -0.5429   0.07471   0.07020  -0.0296   1.0000   0.0976
  -7.000  -0.5403   0.07203   0.06755  -0.0274   1.0000   0.1012
  -6.750  -0.5521   0.06940   0.06480  -0.0270   1.0000   0.1067
  -6.500  -0.5593   0.06572   0.06105  -0.0256   1.0000   0.1102
  -6.250  -0.5517   0.06289   0.05828  -0.0231   1.0000   0.1149
  -6.000  -0.5584   0.05987   0.05501  -0.0220   1.0000   0.1234
  -5.750  -0.5494   0.05693   0.05214  -0.0196   1.0000   0.1292
  -5.500  -0.5471   0.05387   0.04895  -0.0179   1.0000   0.1391
  -4.250  -0.4746   0.03263   0.02515  -0.0072   1.0000   0.0525
  -4.000  -0.4532   0.02996   0.02164  -0.0041   1.0000   0.0435
  -3.750  -0.4324   0.02725   0.01867  -0.0024   1.0000   0.0413
  -3.500  -0.4104   0.02491   0.01601  -0.0009   1.0000   0.0396
  -3.250  -0.3865   0.02295   0.01374   0.0007   1.0000   0.0388
  -3.000  -0.3621   0.02127   0.01184   0.0021   1.0000   0.0387
  -2.750  -0.3390   0.01995   0.01040   0.0035   1.0000   0.0400
  -2.500  -0.1452   0.01416   0.00799  -0.0246   1.0000   1.0000
  -2.250  -0.1352   0.01405   0.00764  -0.0218   1.0000   1.0000
  -2.000  -0.1241   0.01398   0.00734  -0.0190   1.0000   1.0000
  -1.750  -0.1122   0.01395   0.00711  -0.0164   1.0000   1.0000
  -1.500  -0.0995   0.01394   0.00692  -0.0140   1.0000   1.0000
  -1.250  -0.0863   0.01397   0.00673  -0.0116   1.0000   1.0000
  -1.000  -0.0725   0.01401   0.00663  -0.0093   1.0000   1.0000
  -0.750  -0.0584   0.01409   0.00658  -0.0071   1.0000   1.0000
  -0.500  -0.0440   0.01419   0.00656  -0.0051   1.0000   1.0000
  -0.250  -0.0293   0.01432   0.00658  -0.0031   1.0000   1.0000
   0.000  -0.0144   0.01448   0.00665  -0.0011   1.0000   1.0000
   0.250   0.0005   0.01467   0.00673   0.0007   1.0000   1.0000
   0.500   0.0155   0.01490   0.00689   0.0025   1.0000   1.0000
   0.750   0.0304   0.01516   0.00710   0.0041   1.0000   1.0000
   1.000   0.0453   0.01546   0.00736   0.0057   1.0000   1.0000
   1.250   0.0696   0.01587   0.00776   0.0053   0.9975   1.0000
   1.500   0.1269   0.01656   0.00847  -0.0016   0.9850   1.0000
   1.750   0.1840   0.01712   0.00909  -0.0082   0.9717   1.0000
   2.000   0.2409   0.01752   0.00957  -0.0145   0.9576   1.0000
   2.250   0.2987   0.01774   0.00992  -0.0207   0.9433   1.0000
   2.500   0.3536   0.01774   0.01010  -0.0260   0.9273   1.0000
   2.750   0.4064   0.01753   0.01007  -0.0305   0.9096   1.0000
   3.000   0.4696   0.01700   0.00979  -0.0366   0.8928   1.0000
   3.250   0.5201   0.01625   0.00939  -0.0398   0.8718   1.0000
   3.500   0.5604   0.01538   0.00875  -0.0405   0.8462   1.0000
   3.750   0.5933   0.01454   0.00811  -0.0396   0.8132   1.0000
   4.000   0.6267   0.01377   0.00747  -0.0386   0.7657   1.0000
   4.250   0.6585   0.01337   0.00706  -0.0373   0.6939   1.0000
   4.500   0.6809   0.01362   0.00700  -0.0349   0.6020   1.0000
   4.750   0.6968   0.01429   0.00725  -0.0318   0.5066   1.0000
   5.000   0.7097   0.01518   0.00769  -0.0286   0.4115   1.0000
   5.250   0.7214   0.01625   0.00828  -0.0256   0.3201   1.0000
   5.500   0.7325   0.01753   0.00906  -0.0227   0.2358   1.0000
   5.750   0.7436   0.01902   0.01006  -0.0199   0.1652   1.0000
   6.000   0.7565   0.02068   0.01142  -0.0171   0.1188   1.0000
   6.250   0.7712   0.02224   0.01277  -0.0149   0.0901   1.0000
   6.500   0.7909   0.02444   0.01487  -0.0131   0.0755   1.0000
   6.750   0.8142   0.02643   0.01707  -0.0116   0.0665   1.0000
   7.000   0.8330   0.02835   0.01932  -0.0099   0.0555   1.0000
   7.250   0.8539   0.03214   0.02331  -0.0083   0.0501   1.0000
   7.500   0.8684   0.03409   0.02578  -0.0055   0.0434   1.0000
   7.750   0.8776   0.03808   0.02997  -0.0032   0.0383   1.0000
   8.000   0.8849   0.04152   0.03401   0.0004   0.0376   1.0000
   8.250   0.8887   0.04524   0.03823   0.0038   0.0374   1.0000
   8.500   0.8887   0.04891   0.04235   0.0073   0.0371   1.0000
   8.750   0.8849   0.05256   0.04642   0.0107   0.0367   1.0000
   9.000   0.8789   0.05643   0.05060   0.0138   0.0370   1.0000
   9.250   0.8668   0.05997   0.05446   0.0170   0.0364   1.0000
   9.500   0.8561   0.06402   0.05865   0.0194   0.0374   1.0000
   9.750   0.8398   0.06751   0.06228   0.0222   0.0377   1.0000
  10.000   0.8252   0.07159   0.06643   0.0237   0.0382   1.0000
  10.250   0.7035   0.07088   0.06638   0.0242   0.0472   1.0000
  10.500   0.6834   0.07722   0.07276   0.0211   0.0481   1.0000
  10.750   0.6665   0.08425   0.07980   0.0176   0.0490   1.0000
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