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MH 121 8.76% (mh121-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: MH 121 8.76% (mh121-il)
Reynolds number: 500,000
Max Cl/Cd: 125.75 at α=3°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-mh121-il-500000.txt
Download as CSV file: xf-mh121-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 121  8.76%                                   
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.4272   0.10526   0.10304  -0.0332   1.0000   0.0080
  -9.250  -0.4318   0.10266   0.10048  -0.0324   1.0000   0.0083
  -9.000  -0.4391   0.10030   0.09817  -0.0309   1.0000   0.0083
  -8.750  -0.4322   0.09629   0.09418  -0.0339   0.9988   0.0086
  -8.500  -0.4209   0.09157   0.08946  -0.0387   0.9968   0.0089
  -8.250  -0.4090   0.08679   0.08468  -0.0439   0.9947   0.0092
  -8.000  -0.3985   0.08196   0.07986  -0.0490   0.9919   0.0094
  -7.750  -0.3886   0.07684   0.07475  -0.0549   0.9875   0.0096
  -7.500  -0.3765   0.07094   0.06886  -0.0629   0.9833   0.0099
  -7.250  -0.3609   0.06305   0.06097  -0.0754   0.9762   0.0099
  -7.000  -0.3391   0.05374   0.05149  -0.0905   0.9711   0.0100
  -6.750  -0.3216   0.04767   0.04522  -0.0972   0.9658   0.0104
  -6.500  -0.3010   0.04226   0.03956  -0.1020   0.9609   0.0110
  -6.250  -0.2731   0.03714   0.03413  -0.1065   0.9586   0.0119
  -6.000  -0.2355   0.03586   0.03257  -0.1081   0.9575   0.0147
  -5.250  -0.1611   0.02014   0.01539  -0.1134   0.9474   0.0101
  -5.000  -0.1271   0.01664   0.01140  -0.1144   0.9464   0.0091
  -4.750  -0.0932   0.01515   0.00971  -0.1159   0.9456   0.0103
  -4.500  -0.0590   0.01451   0.00897  -0.1174   0.9447   0.0133
  -4.250  -0.0255   0.01277   0.00706  -0.1186   0.9439   0.0127
  -4.000  -0.0035   0.01171   0.00589  -0.1174   0.9386   0.0122
  -3.750   0.0276   0.01072   0.00475  -0.1182   0.9363   0.0122
  -3.500   0.0605   0.01001   0.00386  -0.1193   0.9346   0.0130
  -3.250   0.0939   0.00860   0.00297  -0.1211   0.9331   0.1819
  -3.000   0.1255   0.00747   0.00285  -0.1231   0.9317   0.4833
  -2.750   0.1534   0.00743   0.00275  -0.1232   0.9285   0.5073
  -2.500   0.1810   0.00740   0.00270  -0.1232   0.9250   0.5307
  -2.250   0.2115   0.00733   0.00263  -0.1239   0.9225   0.5497
  -2.000   0.2431   0.00726   0.00256  -0.1247   0.9204   0.5717
  -1.750   0.2750   0.00721   0.00252  -0.1257   0.9186   0.5940
  -1.500   0.3016   0.00722   0.00250  -0.1255   0.9150   0.6093
  -1.250   0.3290   0.00721   0.00250  -0.1255   0.9115   0.6213
  -1.000   0.3588   0.00716   0.00247  -0.1260   0.9087   0.6327
  -0.750   0.3897   0.00711   0.00244  -0.1268   0.9064   0.6441
  -0.500   0.4183   0.00711   0.00246  -0.1270   0.9033   0.6561
  -0.250   0.4443   0.00711   0.00252  -0.1267   0.8988   0.6686
   0.000   0.4735   0.00706   0.00252  -0.1270   0.8952   0.6823
   0.250   0.5046   0.00701   0.00250  -0.1277   0.8920   0.6970
   0.500   0.5290   0.00700   0.00257  -0.1270   0.8860   0.7127
   0.750   0.5582   0.00694   0.00256  -0.1272   0.8810   0.7300
   1.000   0.5847   0.00688   0.00262  -0.1268   0.8747   0.7484
   1.500   0.6375   0.00672   0.00262  -0.1259   0.8594   0.7926
   1.750   0.6635   0.00660   0.00259  -0.1252   0.8497   0.8189
   2.000   0.6875   0.00647   0.00255  -0.1240   0.8378   0.8501
   2.250   0.7093   0.00634   0.00253  -0.1223   0.8259   0.8898
   2.500   0.7318   0.00617   0.00255  -0.1207   0.8138   0.9591
   2.750   0.7600   0.00614   0.00254  -0.1207   0.7963   1.0000
   3.000   0.7784   0.00619   0.00236  -0.1182   0.7301   1.0000
   3.250   0.7711   0.00781   0.00267  -0.1107   0.4774   1.0000
   3.500   0.7771   0.00934   0.00328  -0.1070   0.2873   1.0000
   3.750   0.7923   0.01040   0.00377  -0.1050   0.1671   1.0000
   4.000   0.8066   0.01165   0.00436  -0.1028   0.0461   1.0000
   4.250   0.8266   0.01247   0.00499  -0.1013   0.0057   1.0000
   4.500   0.8497   0.01300   0.00567  -0.1002   0.0049   1.0000
   4.750   0.8714   0.01371   0.00658  -0.0989   0.0046   1.0000
   5.000   0.8910   0.01468   0.00770  -0.0971   0.0045   1.0000
   5.250   0.9091   0.01591   0.00907  -0.0950   0.0046   1.0000
   5.500   0.9278   0.01753   0.01086  -0.0930   0.0048   1.0000
   5.750   0.9510   0.01980   0.01332  -0.0917   0.0051   1.0000
   6.000   0.9801   0.02429   0.01813  -0.0913   0.0061   1.0000
   6.250   1.0048   0.02421   0.01809  -0.0904   0.0069   1.0000
  10.250   0.8413   0.09612   0.09429  -0.0509   0.0146   1.0000
  10.500   0.8199   0.10433   0.10258  -0.0560   0.0146   1.0000
  10.750   0.8044   0.11332   0.11165  -0.0623   0.0146   1.0000
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