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MH 106 13.07% (mh106-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: MH 106 13.07% (mh106-il)
Reynolds number: 50,000
Max Cl/Cd: 27.35 at α=9°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-mh106-il-50000-n5.txt
Download as CSV file: xf-mh106-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 106  13.07%                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.000  -0.6789   0.09708   0.09009  -0.0086   1.0000   0.0334
 -11.750  -0.6952   0.08959   0.08254  -0.0134   1.0000   0.0332
 -11.500  -0.7098   0.08311   0.07598  -0.0176   1.0000   0.0329
 -11.250  -0.7254   0.07712   0.06988  -0.0215   1.0000   0.0327
 -11.000  -0.7432   0.07153   0.06413  -0.0247   1.0000   0.0325
 -10.750  -0.7589   0.06688   0.05930  -0.0266   1.0000   0.0325
 -10.500  -0.7733   0.06282   0.05503  -0.0271   1.0000   0.0325
 -10.250  -0.7848   0.05925   0.05123  -0.0265   1.0000   0.0325
 -10.000  -0.7930   0.05606   0.04777  -0.0249   1.0000   0.0327
  -9.750  -0.7964   0.05301   0.04440  -0.0232   1.0000   0.0330
  -9.500  -0.7935   0.04999   0.04110  -0.0217   1.0000   0.0336
  -9.250  -0.7849   0.04732   0.03835  -0.0206   1.0000   0.0349
  -9.000  -0.7753   0.04503   0.03593  -0.0194   1.0000   0.0369
  -8.750  -0.7629   0.04275   0.03337  -0.0181   1.0000   0.0392
  -8.500  -0.7466   0.04048   0.03080  -0.0168   1.0000   0.0415
  -8.250  -0.7280   0.03835   0.02842  -0.0154   1.0000   0.0434
  -8.000  -0.7143   0.03634   0.02645  -0.0140   1.0000   0.0466
  -7.750  -0.6996   0.03463   0.02460  -0.0125   1.0000   0.0521
  -7.500  -0.6863   0.03282   0.02273  -0.0107   1.0000   0.0573
  -7.250  -0.6728   0.03115   0.02095  -0.0089   1.0000   0.0659
  -7.000  -0.6611   0.02931   0.01916  -0.0070   1.0000   0.0788
  -6.750  -0.6506   0.02728   0.01738  -0.0051   1.0000   0.1026
  -6.500  -0.6419   0.02514   0.01591  -0.0031   1.0000   0.1663
  -6.250  -0.6303   0.02407   0.01524  -0.0009   1.0000   0.2489
  -6.000  -0.6168   0.02358   0.01483   0.0013   1.0000   0.3049
  -5.750  -0.6035   0.02328   0.01461   0.0037   1.0000   0.3496
  -5.500  -0.5883   0.02300   0.01439   0.0060   1.0000   0.3849
  -5.250  -0.5705   0.02263   0.01399   0.0079   1.0000   0.4119
  -5.000  -0.5515   0.02220   0.01346   0.0095   1.0000   0.4341
  -4.750  -0.5324   0.02177   0.01301   0.0109   1.0000   0.4538
  -4.500  -0.5143   0.02139   0.01262   0.0124   1.0000   0.4724
  -4.250  -0.4858   0.02103   0.01217   0.0118   0.9861   0.4947
  -4.000  -0.4394   0.02067   0.01171   0.0081   0.9550   0.5208
  -3.750  -0.3940   0.02033   0.01129   0.0048   0.9251   0.5476
  -3.500  -0.3509   0.02005   0.01092   0.0022   0.8963   0.5753
  -3.250  -0.3130   0.01983   0.01059   0.0008   0.8677   0.6031
  -3.000  -0.2805   0.01967   0.01034   0.0006   0.8401   0.6309
  -2.750  -0.2513   0.01958   0.01016   0.0012   0.8146   0.6592
  -2.500  -0.2231   0.01954   0.01003   0.0020   0.7918   0.6879
  -2.250  -0.1952   0.01955   0.00994   0.0029   0.7696   0.7171
  -2.000  -0.1661   0.01961   0.00990   0.0036   0.7501   0.7468
  -1.750  -0.1350   0.01973   0.00991   0.0040   0.7314   0.7761
  -1.500  -0.1015   0.01988   0.00993   0.0038   0.7134   0.8041
  -1.250  -0.0656   0.02008   0.00998   0.0031   0.6966   0.8304
  -1.000  -0.0287   0.02028   0.01002   0.0020   0.6811   0.8555
  -0.750   0.0093   0.02049   0.01007   0.0006   0.6663   0.8792
  -0.500   0.0517   0.02070   0.01012  -0.0017   0.6521   0.8997
  -0.250   0.0954   0.02088   0.01014  -0.0046   0.6388   0.9189
   0.000   0.1369   0.02103   0.01015  -0.0072   0.6265   0.9387
   0.250   0.1811   0.02112   0.01010  -0.0105   0.6150   0.9566
   0.500   0.2264   0.02118   0.01009  -0.0142   0.6031   0.9737
   0.750   0.2722   0.02121   0.01005  -0.0183   0.5918   0.9904
   1.000   0.3083   0.02123   0.01001  -0.0206   0.5824   1.0000
   1.250   0.3278   0.02137   0.01010  -0.0197   0.5740   1.0000
   1.500   0.3477   0.02156   0.01027  -0.0189   0.5657   1.0000
   1.750   0.3684   0.02176   0.01041  -0.0180   0.5581   1.0000
   2.000   0.3892   0.02205   0.01073  -0.0173   0.5500   1.0000
   2.250   0.4101   0.02230   0.01094  -0.0164   0.5430   1.0000
   2.500   0.4308   0.02266   0.01134  -0.0156   0.5349   1.0000
   2.750   0.4519   0.02295   0.01163  -0.0146   0.5283   1.0000
   3.000   0.4727   0.02338   0.01211  -0.0138   0.5202   1.0000
   3.250   0.4940   0.02371   0.01243  -0.0128   0.5135   1.0000
   3.500   0.5147   0.02421   0.01301  -0.0120   0.5055   1.0000
   3.750   0.5361   0.02456   0.01338  -0.0109   0.4988   1.0000
   4.000   0.5565   0.02511   0.01404  -0.0101   0.4905   1.0000
   4.250   0.5783   0.02546   0.01440  -0.0090   0.4837   1.0000
   4.500   0.5982   0.02608   0.01517  -0.0081   0.4750   1.0000
   4.750   0.6204   0.02638   0.01547  -0.0069   0.4682   1.0000
   5.000   0.6395   0.02707   0.01632  -0.0060   0.4587   1.0000
   5.250   0.6611   0.02746   0.01676  -0.0048   0.4510   1.0000
   5.500   0.6810   0.02801   0.01746  -0.0037   0.4417   1.0000
   5.750   0.7005   0.02859   0.01818  -0.0026   0.4322   1.0000
   6.000   0.7234   0.02878   0.01838  -0.0013   0.4241   1.0000
   6.250   0.7412   0.02947   0.01927  -0.0001   0.4128   1.0000
   6.500   0.7601   0.03001   0.01995   0.0012   0.4021   1.0000
   6.750   0.7813   0.03029   0.02034   0.0025   0.3920   1.0000
   7.000   0.8018   0.03057   0.02072   0.0039   0.3809   1.0000
   7.250   0.8193   0.03113   0.02146   0.0053   0.3683   1.0000
   7.500   0.8369   0.03162   0.02212   0.0068   0.3554   1.0000
   7.750   0.8545   0.03205   0.02270   0.0083   0.3422   1.0000
   8.000   0.8718   0.03245   0.02329   0.0098   0.3283   1.0000
   8.250   0.8882   0.03286   0.02385   0.0115   0.3137   1.0000
   8.500   0.9040   0.03327   0.02440   0.0131   0.2985   1.0000
   8.750   0.9190   0.03371   0.02495   0.0148   0.2829   1.0000
   9.000   0.9333   0.03413   0.02545   0.0166   0.2669   1.0000
   9.250   0.9461   0.03470   0.02604   0.0185   0.2509   1.0000
   9.500   0.9543   0.03570   0.02716   0.0204   0.2345   1.0000
   9.750   0.9615   0.03681   0.02829   0.0223   0.2193   1.0000
  10.000   0.9661   0.03809   0.02958   0.0243   0.2050   1.0000
  10.250   0.9685   0.03954   0.03101   0.0262   0.1923   1.0000
  10.500   0.9694   0.04101   0.03239   0.0284   0.1813   1.0000
  10.750   0.9639   0.04325   0.03475   0.0299   0.1710   1.0000
  11.000   0.9606   0.04559   0.03713   0.0308   0.1614   1.0000
  11.250   0.9607   0.04775   0.03923   0.0315   0.1522   1.0000
  11.500   0.9564   0.05067   0.04228   0.0315   0.1438   1.0000
  11.750   0.9539   0.05352   0.04517   0.0314   0.1360   1.0000
  12.000   0.9532   0.05619   0.04784   0.0314   0.1281   1.0000
  12.250   0.9472   0.05986   0.05166   0.0306   0.1217   1.0000
  12.500   0.9471   0.06267   0.05453   0.0303   0.1150   1.0000
  12.750   0.9397   0.06675   0.05875   0.0292   0.1096   1.0000
  13.000   0.9313   0.07106   0.06320   0.0277   0.1042   1.0000
  13.250   0.9332   0.07381   0.06591   0.0274   0.0987   1.0000
  13.500   0.9141   0.08033   0.07269   0.0244   0.0960   1.0000
  13.750   0.8938   0.08734   0.07989   0.0211   0.0934   1.0000
  14.000   0.9084   0.08775   0.08015   0.0221   0.0866   1.0000
  14.250   0.8800   0.09670   0.08933   0.0175   0.0858   1.0000
  14.500   0.8410   0.10874   0.10150   0.0109   0.0858   1.0000
  14.750   0.7938   0.12425   0.11694   0.0026   0.0859   1.0000
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