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MH 30 7.84% (mh30-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: MH 30 7.84% (mh30-il)
Reynolds number: 50,000
Max Cl/Cd: 34.78 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-mh30-il-50000.txt
Download as CSV file: xf-mh30-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 30  7.84%                                    
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.4972   0.11899   0.11218  -0.0052   1.0000   0.1951
  -9.250  -0.4807   0.11385   0.10694  -0.0044   1.0000   0.2018
  -9.000  -0.4973   0.11308   0.10631  -0.0073   1.0000   0.2091
  -8.750  -0.4750   0.10749   0.10070  -0.0057   1.0000   0.2190
  -8.500  -0.4735   0.10418   0.09746  -0.0064   1.0000   0.2264
  -8.250  -0.4894   0.10304   0.09647  -0.0084   1.0000   0.2362
  -8.000  -0.4707   0.09816   0.09159  -0.0071   1.0000   0.2478
  -7.750  -0.4628   0.09429   0.08777  -0.0066   1.0000   0.2584
  -7.500  -0.4604   0.09106   0.08462  -0.0065   1.0000   0.2694
  -7.250  -0.4611   0.08811   0.08176  -0.0063   1.0000   0.2810
  -6.500  -0.4590   0.07912   0.07305  -0.0039   1.0000   0.3220
  -6.250  -0.4610   0.07659   0.07061  -0.0030   1.0000   0.3424
  -5.750  -0.4665   0.05534   0.04844  -0.0378   1.0000   0.1277
  -5.500  -0.4525   0.04984   0.04272  -0.0382   1.0000   0.1105
  -5.250  -0.4379   0.04472   0.03701  -0.0386   1.0000   0.0988
  -5.000  -0.4217   0.04033   0.03209  -0.0381   1.0000   0.0925
  -4.750  -0.4017   0.03669   0.02753  -0.0371   1.0000   0.0883
  -4.500  -0.3836   0.03379   0.02461  -0.0360   1.0000   0.0944
  -4.250  -0.3619   0.03124   0.02145  -0.0347   1.0000   0.1006
  -4.000  -0.3390   0.02838   0.01830  -0.0334   1.0000   0.1061
  -3.750  -0.3145   0.02599   0.01552  -0.0319   1.0000   0.1171
  -3.500  -0.2923   0.02408   0.01370  -0.0305   1.0000   0.1478
  -3.250  -0.2664   0.02179   0.01147  -0.0290   1.0000   0.1949
  -3.000  -0.2469   0.01909   0.00999  -0.0271   1.0000   0.3713
  -2.750  -0.2436   0.01689   0.00968  -0.0199   1.0000   0.6728
  -2.500  -0.1462   0.01617   0.00843  -0.0287   1.0000   1.0000
  -2.250  -0.1375   0.01600   0.00785  -0.0265   1.0000   1.0000
  -2.000  -0.1229   0.01594   0.00741  -0.0249   1.0000   1.0000
  -1.750  -0.1059   0.01595   0.00706  -0.0235   1.0000   1.0000
  -1.500  -0.0877   0.01600   0.00679  -0.0224   1.0000   1.0000
  -1.250  -0.0688   0.01608   0.00659  -0.0213   1.0000   1.0000
  -1.000  -0.0495   0.01620   0.00641  -0.0203   1.0000   1.0000
  -0.750  -0.0300   0.01636   0.00634  -0.0194   1.0000   1.0000
  -0.500  -0.0103   0.01654   0.00633  -0.0186   1.0000   1.0000
  -0.250   0.0094   0.01676   0.00638  -0.0178   1.0000   1.0000
   0.000   0.0290   0.01701   0.00649  -0.0171   1.0000   1.0000
   0.250   0.0484   0.01731   0.00662  -0.0164   1.0000   1.0000
   0.500   0.0676   0.01764   0.00685  -0.0157   1.0000   1.0000
   0.750   0.0865   0.01802   0.00715  -0.0151   1.0000   1.0000
   1.000   0.1050   0.01844   0.00751  -0.0146   1.0000   1.0000
   1.250   0.1232   0.01893   0.00796  -0.0141   1.0000   1.0000
   1.500   0.1409   0.01947   0.00847  -0.0137   1.0000   1.0000
   1.750   0.1581   0.02008   0.00907  -0.0134   1.0000   1.0000
   2.000   0.1747   0.02077   0.00976  -0.0131   1.0000   1.0000
   2.250   0.1908   0.02154   0.01055  -0.0130   1.0000   1.0000
   2.500   0.2480   0.02303   0.01214  -0.0206   0.9814   1.0000
   2.750   0.3146   0.02433   0.01364  -0.0294   0.9539   1.0000
   3.000   0.3753   0.02523   0.01475  -0.0363   0.9245   1.0000
   3.250   0.4351   0.02579   0.01557  -0.0423   0.8940   1.0000
   3.500   0.5017   0.02586   0.01608  -0.0485   0.8629   1.0000
   3.750   0.5609   0.02549   0.01607  -0.0523   0.8296   1.0000
   4.000   0.6166   0.02459   0.01554  -0.0541   0.7955   1.0000
   4.250   0.6575   0.02371   0.01504  -0.0531   0.7574   1.0000
   4.500   0.6937   0.02275   0.01429  -0.0507   0.7157   1.0000
   4.750   0.7221   0.02215   0.01378  -0.0475   0.6675   1.0000
   5.000   0.7471   0.02192   0.01352  -0.0440   0.6126   1.0000
   5.250   0.7697   0.02213   0.01355  -0.0406   0.5529   1.0000
   5.500   0.7890   0.02279   0.01402  -0.0374   0.4892   1.0000
   5.750   0.8077   0.02372   0.01467  -0.0345   0.4257   1.0000
   6.000   0.8260   0.02492   0.01567  -0.0319   0.3636   1.0000
   6.250   0.8428   0.02638   0.01692  -0.0295   0.3028   1.0000
   6.500   0.8602   0.02817   0.01843  -0.0273   0.2474   1.0000
   6.750   0.8792   0.03037   0.02034  -0.0254   0.2007   1.0000
   7.000   0.8971   0.03248   0.02223  -0.0237   0.1622   1.0000
   7.250   0.9191   0.03557   0.02563  -0.0221   0.1394   1.0000
   7.500   0.9364   0.03818   0.02840  -0.0206   0.1191   1.0000
   7.750   0.9559   0.04180   0.03226  -0.0192   0.1082   1.0000
   8.000   0.9688   0.04611   0.03733  -0.0170   0.1034   1.0000
   8.250   0.9804   0.05050   0.04216  -0.0153   0.0999   1.0000
   8.500   0.9868   0.05490   0.04690  -0.0136   0.0948   1.0000
   8.750   0.9830   0.05937   0.05196  -0.0117   0.0921   1.0000
   9.000   0.9772   0.06397   0.05697  -0.0103   0.0903   1.0000
   9.250   0.9652   0.06901   0.06234  -0.0092   0.0908   1.0000
   9.500   0.9495   0.07417   0.06773  -0.0087   0.0925   1.0000
   9.750   0.9325   0.07904   0.07272  -0.0083   0.0940   1.0000
  10.000   0.9179   0.08402   0.07776  -0.0088   0.0953   1.0000
  10.250   0.9078   0.08961   0.08336  -0.0099   0.0963   1.0000
  10.500   0.7317   0.10380   0.09782  -0.0232   0.1325   1.0000
  10.750   0.7377   0.10965   0.10373  -0.0235   0.1363   1.0000
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