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MH 122 9.32% (mh122-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: MH 122 9.32% (mh122-il)
Reynolds number: 200,000
Max Cl/Cd: 87.59 at α=4°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-mh122-il-200000-n5.txt
Download as CSV file: xf-mh122-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 122  9.32%                                   
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3373   0.08638   0.08289  -0.0602   0.9825   0.0159
  -8.000  -0.3306   0.08076   0.07727  -0.0646   0.9758   0.0115
  -7.500  -0.3222   0.07161   0.06816  -0.0728   0.9635   0.0103
  -7.000  -0.3007   0.05738   0.05383  -0.0926   0.9490   0.0095
  -6.750  -0.2827   0.05003   0.04624  -0.1018   0.9451   0.0088
  -6.500  -0.2735   0.04419   0.04010  -0.1052   0.9376   0.0081
  -6.250  -0.2505   0.03659   0.03193  -0.1097   0.9340   0.0070
  -6.000  -0.2211   0.03240   0.02727  -0.1123   0.9323   0.0065
  -5.750  -0.2012   0.02995   0.02447  -0.1123   0.9273   0.0063
  -5.250  -0.1462   0.02441   0.01805  -0.1147   0.9222   0.0061
  -5.000  -0.1148   0.02188   0.01508  -0.1161   0.9208   0.0060
  -4.750  -0.0823   0.01983   0.01267  -0.1174   0.9196   0.0061
  -4.500  -0.0495   0.01820   0.01078  -0.1186   0.9186   0.0062
  -4.250  -0.0300   0.01688   0.00931  -0.1172   0.9137   0.0064
  -4.000  -0.0013   0.01562   0.00787  -0.1178   0.9113   0.0071
  -3.750   0.0303   0.01482   0.00686  -0.1188   0.9094   0.0082
  -3.500   0.0627   0.01432   0.00626  -0.1200   0.9078   0.0121
  -3.250   0.0961   0.01339   0.00544  -0.1215   0.9065   0.0526
  -3.000   0.1282   0.01179   0.00503  -0.1241   0.9055   0.3474
  -2.750   0.1505   0.01165   0.00507  -0.1231   0.9011   0.4371
  -2.500   0.1783   0.01156   0.00504  -0.1232   0.8982   0.4921
  -2.250   0.2083   0.01150   0.00496  -0.1237   0.8961   0.5310
  -2.000   0.2390   0.01143   0.00493  -0.1243   0.8943   0.5699
  -1.750   0.2711   0.01136   0.00483  -0.1252   0.8928   0.5911
  -1.500   0.2978   0.01138   0.00482  -0.1251   0.8898   0.6038
  -1.250   0.3225   0.01143   0.00483  -0.1245   0.8859   0.6156
  -1.000   0.3517   0.01141   0.00480  -0.1249   0.8833   0.6276
  -0.750   0.3825   0.01136   0.00476  -0.1256   0.8813   0.6402
  -0.500   0.4143   0.01131   0.00471  -0.1265   0.8796   0.6535
  -0.250   0.4397   0.01136   0.00479  -0.1260   0.8760   0.6669
   0.000   0.4647   0.01140   0.00488  -0.1255   0.8718   0.6815
   0.250   0.4943   0.01137   0.00490  -0.1259   0.8690   0.6972
   0.500   0.5257   0.01129   0.00488  -0.1266   0.8667   0.7140
   0.750   0.5513   0.01131   0.00498  -0.1262   0.8625   0.7320
   1.000   0.5761   0.01132   0.00509  -0.1255   0.8576   0.7524
   1.250   0.6061   0.01121   0.00507  -0.1258   0.8541   0.7746
   1.500   0.6320   0.01114   0.00512  -0.1253   0.8492   0.8003
   1.750   0.6560   0.01106   0.00515  -0.1242   0.8428   0.8311
   2.000   0.6847   0.01084   0.00505  -0.1240   0.8375   0.8698
   2.250   0.7100   0.01064   0.00504  -0.1230   0.8285   0.9460
   2.500   0.7398   0.01051   0.00495  -0.1232   0.8178   1.0000
   2.750   0.7679   0.01037   0.00482  -0.1230   0.8038   1.0000
   3.000   0.7963   0.01021   0.00467  -0.1227   0.7863   1.0000
   3.250   0.8204   0.01019   0.00472  -0.1217   0.7675   1.0000
   3.500   0.8461   0.01017   0.00473  -0.1210   0.7467   1.0000
   3.750   0.8710   0.01017   0.00474  -0.1201   0.7161   1.0000
   4.000   0.8969   0.01024   0.00464  -0.1193   0.6560   1.0000
   4.250   0.9124   0.01089   0.00470  -0.1164   0.5471   1.0000
   4.500   0.9193   0.01194   0.00518  -0.1123   0.4423   1.0000
   4.750   0.9265   0.01306   0.00579  -0.1086   0.3448   1.0000
   5.000   0.9362   0.01416   0.00650  -0.1056   0.2560   1.0000
   5.250   0.9500   0.01511   0.00713  -0.1034   0.1905   1.0000
   5.500   0.9655   0.01601   0.00777  -0.1015   0.1395   1.0000
   5.750   0.9825   0.01679   0.00840  -0.0998   0.1046   1.0000
   6.000   1.0004   0.01749   0.00905  -0.0982   0.0836   1.0000
   6.250   1.0182   0.01821   0.00972  -0.0966   0.0652   1.0000
   6.500   1.0359   0.01895   0.01043  -0.0950   0.0512   1.0000
   6.750   1.0537   0.01970   0.01125  -0.0934   0.0419   1.0000
   7.000   1.0710   0.02053   0.01211  -0.0917   0.0330   1.0000
   7.250   1.0866   0.02157   0.01315  -0.0898   0.0254   1.0000
   7.500   1.1052   0.02231   0.01403  -0.0885   0.0182   1.0000
   7.750   1.1215   0.02335   0.01515  -0.0868   0.0125   1.0000
   8.000   1.1344   0.02492   0.01678  -0.0845   0.0087   1.0000
   8.250   1.1494   0.02629   0.01836  -0.0825   0.0075   1.0000
   8.500   1.1640   0.02794   0.02021  -0.0805   0.0065   1.0000
   8.750   1.1795   0.02971   0.02217  -0.0787   0.0059   1.0000
   9.000   1.1952   0.03158   0.02425  -0.0770   0.0055   1.0000
   9.250   1.2092   0.03336   0.02623  -0.0753   0.0050   1.0000
   9.500   1.2173   0.03652   0.02968  -0.0731   0.0042   1.0000
   9.750   1.2307   0.03776   0.03118  -0.0713   0.0037   1.0000
  10.000   1.2407   0.03953   0.03322  -0.0692   0.0031   1.0000
  10.250   1.2468   0.04173   0.03571  -0.0668   0.0028   1.0000
  10.500   1.2480   0.04452   0.03883  -0.0640   0.0027   1.0000
  10.750   1.2454   0.04755   0.04220  -0.0610   0.0025   1.0000
  11.000   1.2397   0.05070   0.04565  -0.0583   0.0024   1.0000
  11.250   1.2299   0.05434   0.04962  -0.0556   0.0024   1.0000
  11.500   1.2179   0.05821   0.05385  -0.0534   0.0023   1.0000
  11.750   1.2016   0.06285   0.05879  -0.0518   0.0023   1.0000
  12.000   1.1824   0.06810   0.06432  -0.0509   0.0023   1.0000
  12.250   1.1618   0.07392   0.07040  -0.0512   0.0023   1.0000
  12.500   1.1367   0.08117   0.07785  -0.0531   0.0024   1.0000
  12.750   1.1124   0.08929   0.08618  -0.0568   0.0024   1.0000
  13.000   1.0857   0.09974   0.09684  -0.0631   0.0025   1.0000
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