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MH 62 9.3% (mh62-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: MH 62 9.3% (mh62-il)
Reynolds number: 200,000
Max Cl/Cd: 60.45 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-mh62-il-200000.txt
Download as CSV file: xf-mh62-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 62  9.3%                                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.4704   0.09617   0.09327   0.0070   1.0000   0.0416
  -9.000  -0.4677   0.09199   0.08911   0.0056   1.0000   0.0428
  -8.750  -0.5646   0.09010   0.08704   0.0006   1.0000   0.0399
  -8.500  -0.5578   0.08712   0.08408   0.0006   1.0000   0.0410
  -8.250  -0.5555   0.08335   0.08035  -0.0013   1.0000   0.0418
  -8.000  -0.5562   0.07916   0.07621  -0.0041   1.0000   0.0427
  -7.750  -0.5613   0.07424   0.07134  -0.0087   1.0000   0.0432
  -7.500  -0.5624   0.06823   0.06530  -0.0147   1.0000   0.0445
  -7.250  -0.5607   0.06229   0.05927  -0.0196   1.0000   0.0458
  -7.000  -0.5621   0.05701   0.05330  -0.0255   1.0000   0.0507
  -6.750  -0.5582   0.04930   0.04553  -0.0274   1.0000   0.0525
  -6.500  -0.5404   0.04610   0.04240  -0.0278   1.0000   0.0544
  -6.250  -0.5230   0.04281   0.03896  -0.0285   1.0000   0.0573
  -6.000  -0.5098   0.03003   0.02476  -0.0270   1.0000   0.0227
  -5.750  -0.4896   0.02595   0.01979  -0.0252   1.0000   0.0191
  -5.500  -0.4760   0.02433   0.01791  -0.0231   1.0000   0.0189
  -5.250  -0.4486   0.02120   0.01443  -0.0237   0.9937   0.0197
  -5.000  -0.4103   0.01977   0.01287  -0.0265   0.9851   0.0234
  -4.750  -0.3719   0.01792   0.01079  -0.0283   0.9765   0.0248
  -4.500  -0.3344   0.01629   0.00902  -0.0299   0.9680   0.0262
  -4.250  -0.3029   0.01469   0.00734  -0.0304   0.9570   0.0294
  -4.000  -0.2755   0.01355   0.00617  -0.0302   0.9446   0.0441
  -3.750  -0.2561   0.01172   0.00520  -0.0288   0.9317   0.2060
  -3.500  -0.2343   0.01125   0.00504  -0.0276   0.9195   0.3019
  -3.250  -0.2121   0.01099   0.00489  -0.0263   0.9081   0.3583
  -3.000  -0.1906   0.01073   0.00478  -0.0248   0.8973   0.4228
  -2.750  -0.1699   0.01044   0.00469  -0.0229   0.8872   0.4913
  -2.500  -0.1480   0.01014   0.00459  -0.0214   0.8761   0.5577
  -2.250  -0.1265   0.00984   0.00450  -0.0197   0.8657   0.6288
  -2.000  -0.1057   0.00953   0.00441  -0.0176   0.8561   0.7059
  -1.750  -0.0841   0.00924   0.00435  -0.0153   0.8468   0.7918
  -1.500  -0.0502   0.00906   0.00432  -0.0155   0.8371   0.8839
  -1.250   0.0025   0.00902   0.00418  -0.0197   0.8288   0.9464
  -1.000   0.0531   0.00903   0.00403  -0.0239   0.8196   0.9813
  -0.750   0.0997   0.00898   0.00384  -0.0277   0.8090   1.0000
  -0.500   0.1219   0.00898   0.00370  -0.0266   0.7977   1.0000
  -0.250   0.1446   0.00900   0.00359  -0.0255   0.7867   1.0000
   0.000   0.1675   0.00902   0.00349  -0.0243   0.7759   1.0000
   0.250   0.1916   0.00904   0.00342  -0.0234   0.7640   1.0000
   0.500   0.2161   0.00907   0.00336  -0.0226   0.7517   1.0000
   0.750   0.2407   0.00910   0.00330  -0.0218   0.7392   1.0000
   1.000   0.2656   0.00913   0.00326  -0.0210   0.7264   1.0000
   1.250   0.2906   0.00917   0.00322  -0.0202   0.7132   1.0000
   1.500   0.3157   0.00921   0.00320  -0.0194   0.6993   1.0000
   1.750   0.3411   0.00925   0.00317  -0.0187   0.6848   1.0000
   2.000   0.3666   0.00929   0.00315  -0.0180   0.6696   1.0000
   2.250   0.3921   0.00935   0.00314  -0.0173   0.6536   1.0000
   2.500   0.4178   0.00941   0.00314  -0.0167   0.6368   1.0000
   2.750   0.4439   0.00949   0.00320  -0.0162   0.6175   1.0000
   3.000   0.4697   0.00959   0.00323  -0.0156   0.5982   1.0000
   3.250   0.4958   0.00970   0.00330  -0.0151   0.5769   1.0000
   3.500   0.5216   0.00985   0.00339  -0.0145   0.5554   1.0000
   3.750   0.5477   0.01002   0.00351  -0.0141   0.5317   1.0000
   4.000   0.5737   0.01022   0.00364  -0.0137   0.5078   1.0000
   4.250   0.5995   0.01046   0.00380  -0.0132   0.4840   1.0000
   4.500   0.6253   0.01073   0.00402  -0.0128   0.4591   1.0000
   4.750   0.6511   0.01101   0.00426  -0.0125   0.4339   1.0000
   5.000   0.6768   0.01132   0.00453  -0.0121   0.4087   1.0000
   5.250   0.7022   0.01167   0.00482  -0.0118   0.3835   1.0000
   5.500   0.7275   0.01204   0.00514  -0.0114   0.3582   1.0000
   5.750   0.7526   0.01245   0.00551  -0.0111   0.3328   1.0000
   6.000   0.7775   0.01288   0.00590  -0.0107   0.3068   1.0000
   6.250   0.8022   0.01333   0.00632  -0.0104   0.2806   1.0000
   6.500   0.8266   0.01383   0.00678  -0.0100   0.2546   1.0000
   6.750   0.8507   0.01437   0.00729  -0.0096   0.2294   1.0000
   7.000   0.8742   0.01497   0.00784  -0.0092   0.2057   1.0000
   7.250   0.8972   0.01563   0.00848  -0.0088   0.1828   1.0000
   7.500   0.9204   0.01626   0.00912  -0.0083   0.1605   1.0000
   7.750   0.9425   0.01699   0.00981  -0.0078   0.1391   1.0000
   8.000   0.9644   0.01773   0.01054  -0.0073   0.1181   1.0000
   8.250   0.9852   0.01863   0.01142  -0.0066   0.0978   1.0000
   8.500   1.0041   0.01973   0.01244  -0.0058   0.0777   1.0000
   8.750   1.0220   0.02098   0.01372  -0.0048   0.0601   1.0000
   9.000   1.0377   0.02243   0.01520  -0.0036   0.0474   1.0000
   9.250   1.0511   0.02411   0.01694  -0.0022   0.0389   1.0000
   9.500   1.0646   0.02559   0.01847  -0.0009   0.0318   1.0000
   9.750   1.0767   0.02738   0.02042   0.0007   0.0269   1.0000
  10.000   1.0833   0.02944   0.02250   0.0023   0.0216   1.0000
  10.250   1.0933   0.03128   0.02455   0.0040   0.0189   1.0000
  10.500   1.0999   0.03321   0.02665   0.0060   0.0170   1.0000
  10.750   1.1029   0.03519   0.02874   0.0080   0.0157   1.0000
  11.000   1.1049   0.03768   0.03136   0.0096   0.0150   1.0000
  11.250   1.0993   0.04192   0.03584   0.0112   0.0141   1.0000
  11.500   1.0947   0.04560   0.03978   0.0123   0.0139   1.0000
  11.750   1.0860   0.04886   0.04331   0.0127   0.0135   1.0000
  12.000   1.0808   0.05172   0.04640   0.0124   0.0130   1.0000
  12.250   1.0723   0.05554   0.05044   0.0117   0.0128   1.0000
  12.500   1.0586   0.06055   0.05569   0.0102   0.0131   1.0000
  12.750   1.0501   0.06464   0.05998   0.0080   0.0123   1.0000
  13.000   1.0299   0.07136   0.06692   0.0048   0.0129   1.0000
  13.250   1.0149   0.07750   0.07323   0.0013   0.0131   1.0000
  13.500   1.0078   0.08251   0.07840  -0.0026   0.0117   1.0000
  13.750   0.9782   0.09242   0.08849  -0.0081   0.0133   1.0000
  14.000   0.9558   0.10156   0.09776  -0.0137   0.0136   1.0000
  14.500   0.7835   0.12225   0.11918  -0.0230   0.0179   1.0000
  14.750   0.7429   0.13314   0.13013  -0.0297   0.0198   1.0000
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