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MH 30 7.84% (mh30-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: MH 30 7.84% (mh30-il)
Reynolds number: 500,000
Max Cl/Cd: 85.05 at α=3.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-mh30-il-500000.txt
Download as CSV file: xf-mh30-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.4677   0.08494   0.08275  -0.0230   1.0000   0.0156
  -8.250  -0.4679   0.08061   0.07845  -0.0254   1.0000   0.0157
  -8.000  -0.4692   0.07637   0.07425  -0.0281   1.0000   0.0157
  -7.750  -0.4747   0.07169   0.06961  -0.0318   1.0000   0.0157
  -7.500  -0.4736   0.06568   0.06357  -0.0375   1.0000   0.0157
  -7.250  -0.4724   0.06034   0.05815  -0.0405   1.0000   0.0157
  -7.000  -0.4719   0.05589   0.05359  -0.0416   1.0000   0.0157
  -6.750  -0.4729   0.05196   0.04953  -0.0412   1.0000   0.0157
  -6.500  -0.4754   0.04873   0.04616  -0.0393   1.0000   0.0157
  -6.250  -0.4775   0.04582   0.04310  -0.0369   1.0000   0.0157
  -6.000  -0.4846   0.03615   0.03304  -0.0381   0.9982   0.0170
  -5.750  -0.4560   0.03266   0.02934  -0.0409   0.9953   0.0178
  -5.500  -0.4260   0.02963   0.02603  -0.0432   0.9924   0.0189
  -5.250  -0.3957   0.02666   0.02276  -0.0448   0.9886   0.0203
  -5.000  -0.3629   0.02382   0.01955  -0.0464   0.9855   0.0218
  -4.750  -0.3289   0.01820   0.01317  -0.0464   0.9831   0.0127
  -4.500  -0.2946   0.01458   0.00902  -0.0469   0.9815   0.0097
  -4.250  -0.2646   0.01312   0.00734  -0.0470   0.9774   0.0088
  -4.000  -0.2313   0.01200   0.00608  -0.0480   0.9743   0.0085
  -3.750  -0.1964   0.01097   0.00493  -0.0494   0.9718   0.0086
  -3.500  -0.1609   0.01007   0.00388  -0.0508   0.9694   0.0093
  -3.250  -0.1296   0.00950   0.00319  -0.0513   0.9647   0.0130
  -3.000  -0.1001   0.00864   0.00264  -0.0517   0.9593   0.0989
  -2.750  -0.0690   0.00804   0.00241  -0.0527   0.9552   0.1975
  -2.500  -0.0452   0.00743   0.00227  -0.0521   0.9473   0.3234
  -2.250  -0.0187   0.00689   0.00214  -0.0519   0.9417   0.4452
  -2.000   0.0037   0.00643   0.00207  -0.0507   0.9332   0.5630
  -1.750   0.0277   0.00609   0.00198  -0.0497   0.9264   0.6524
  -1.500   0.0507   0.00581   0.00193  -0.0483   0.9180   0.7290
  -1.250   0.0736   0.00558   0.00190  -0.0468   0.9098   0.7989
  -1.000   0.0968   0.00540   0.00184  -0.0452   0.9017   0.8593
  -0.750   0.1223   0.00527   0.00181  -0.0441   0.8917   0.9113
  -0.500   0.1581   0.00522   0.00173  -0.0454   0.8828   0.9503
  -0.250   0.1997   0.00519   0.00163  -0.0481   0.8744   0.9733
   0.000   0.2415   0.00516   0.00156  -0.0510   0.8635   0.9885
   0.250   0.2836   0.00514   0.00149  -0.0540   0.8516   1.0000
   0.500   0.3068   0.00515   0.00143  -0.0529   0.8371   1.0000
   0.750   0.3304   0.00517   0.00138  -0.0519   0.8214   1.0000
   1.000   0.3544   0.00521   0.00135  -0.0510   0.8035   1.0000
   1.250   0.3786   0.00526   0.00132  -0.0501   0.7833   1.0000
   1.500   0.4029   0.00533   0.00132  -0.0492   0.7599   1.0000
   1.750   0.4271   0.00544   0.00132  -0.0483   0.7330   1.0000
   2.000   0.4513   0.00558   0.00134  -0.0474   0.7023   1.0000
   2.250   0.4754   0.00575   0.00138  -0.0465   0.6688   1.0000
   2.750   0.5237   0.00620   0.00157  -0.0449   0.5957   1.0000
   3.000   0.5480   0.00646   0.00169  -0.0442   0.5582   1.0000
   3.250   0.5724   0.00673   0.00182  -0.0435   0.5190   1.0000
   3.500   0.5967   0.00703   0.00197  -0.0429   0.4783   1.0000
   3.750   0.6210   0.00736   0.00215  -0.0422   0.4354   1.0000
   4.000   0.6451   0.00772   0.00237  -0.0416   0.3914   1.0000
   4.250   0.6694   0.00809   0.00259  -0.0411   0.3495   1.0000
   4.500   0.6938   0.00847   0.00282  -0.0405   0.3102   1.0000
   4.750   0.7179   0.00889   0.00309  -0.0400   0.2684   1.0000
   5.000   0.7416   0.00937   0.00338  -0.0394   0.2224   1.0000
   5.250   0.7654   0.00987   0.00370  -0.0389   0.1806   1.0000
   5.500   0.7894   0.01033   0.00404  -0.0384   0.1489   1.0000
   5.750   0.8132   0.01083   0.00446  -0.0378   0.1161   1.0000
   6.000   0.8363   0.01143   0.00488  -0.0372   0.0827   1.0000
   6.250   0.8593   0.01204   0.00535  -0.0366   0.0535   1.0000
   6.500   0.8822   0.01267   0.00588  -0.0359   0.0338   1.0000
   6.750   0.9053   0.01328   0.00643  -0.0353   0.0203   1.0000
   7.000   0.9246   0.01461   0.00780  -0.0337   0.0069   1.0000
   7.250   0.9462   0.01549   0.00882  -0.0326   0.0059   1.0000
   7.500   0.9665   0.01654   0.01001  -0.0313   0.0052   1.0000
   7.750   0.9857   0.01771   0.01133  -0.0299   0.0050   1.0000
   8.000   1.0035   0.01913   0.01293  -0.0283   0.0048   1.0000
   8.250   1.0205   0.02074   0.01473  -0.0266   0.0047   1.0000
   8.500   1.0365   0.02269   0.01697  -0.0248   0.0047   1.0000
   8.750   1.0511   0.02513   0.01971  -0.0228   0.0049   1.0000
   9.000   1.0625   0.02838   0.02334  -0.0205   0.0051   1.0000
   9.250   1.0679   0.03250   0.02794  -0.0176   0.0055   1.0000
   9.500   1.0664   0.03697   0.03287  -0.0144   0.0059   1.0000
   9.750   1.0586   0.04132   0.03761  -0.0110   0.0063   1.0000
  10.000   1.0446   0.04514   0.04174  -0.0073   0.0066   1.0000
  10.250   1.0250   0.04859   0.04541  -0.0036   0.0068   1.0000
  10.500   1.0057   0.05225   0.04927  -0.0017   0.0069   1.0000
  10.750   0.9882   0.05620   0.05339  -0.0013   0.0069   1.0000
  11.000   0.9687   0.06115   0.05850  -0.0028   0.0070   1.0000
  11.250   0.9509   0.06689   0.06440  -0.0061   0.0070   1.0000
  11.500   0.9318   0.07426   0.07192  -0.0115   0.0070   1.0000
  11.750   0.9147   0.08295   0.08073  -0.0183   0.0069   1.0000
  12.000   0.9027   0.09172   0.08959  -0.0248   0.0068   1.0000
  12.250   0.8855   0.10308   0.10103  -0.0318   0.0067   1.0000
  12.500   0.8620   0.11646   0.11436  -0.0382   0.0068   1.0000
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