Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

MH 104 15.28% (mh104-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: MH 104 15.28% (mh104-il)
Reynolds number: 500,000
Max Cl/Cd: 95.55 at α=8.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-mh104-il-500000.txt
Download as CSV file: xf-mh104-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 104  15.28%                                  
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -14.750  -0.6441   0.11991   0.11753   0.0003   1.0000   0.0114
 -14.500  -0.6796   0.10640   0.10393  -0.0073   1.0000   0.0110
 -14.250  -0.7089   0.09516   0.09257  -0.0145   1.0000   0.0108
 -14.000  -0.7359   0.08531   0.08257  -0.0211   1.0000   0.0108
 -13.750  -0.7613   0.07656   0.07367  -0.0271   1.0000   0.0106
 -13.500  -0.7960   0.06687   0.06375  -0.0335   1.0000   0.0101
 -13.250  -0.8075   0.06169   0.05844  -0.0371   1.0000   0.0102
 -13.000  -0.8257   0.05591   0.05248  -0.0406   1.0000   0.0102
 -12.750  -0.8523   0.04958   0.04588  -0.0435   1.0000   0.0099
 -12.500  -0.8807   0.04378   0.03969  -0.0446   1.0000   0.0096
 -12.250  -0.8978   0.03984   0.03546  -0.0441   1.0000   0.0095
 -12.000  -0.9072   0.03672   0.03208  -0.0426   1.0000   0.0093
 -11.750  -0.9090   0.03464   0.02980  -0.0408   1.0000   0.0092
 -11.500  -0.9049   0.03336   0.02851  -0.0392   1.0000   0.0095
 -11.250  -0.9033   0.03146   0.02645  -0.0368   1.0000   0.0095
 -11.000  -0.8986   0.03000   0.02488  -0.0344   1.0000   0.0096
 -10.750  -0.8921   0.02879   0.02358  -0.0320   1.0000   0.0098
 -10.500  -0.8832   0.02769   0.02238  -0.0297   1.0000   0.0099
 -10.250  -0.8715   0.02650   0.02110  -0.0277   1.0000   0.0101
 -10.000  -0.8580   0.02530   0.01981  -0.0260   1.0000   0.0102
  -9.750  -0.8438   0.02399   0.01840  -0.0242   1.0000   0.0104
  -9.500  -0.8285   0.02282   0.01714  -0.0226   1.0000   0.0104
  -9.250  -0.8128   0.02170   0.01595  -0.0210   0.9997   0.0105
  -9.000  -0.7737   0.02030   0.01438  -0.0241   0.9182   0.0107
  -8.750  -0.7590   0.01955   0.01339  -0.0217   0.8692   0.0110
  -8.500  -0.7438   0.01886   0.01251  -0.0194   0.8380   0.0112
  -8.250  -0.7266   0.01821   0.01169  -0.0176   0.8141   0.0114
  -8.000  -0.7100   0.01740   0.01074  -0.0157   0.7935   0.0117
  -7.750  -0.6938   0.01651   0.00974  -0.0138   0.7751   0.0123
  -7.500  -0.6733   0.01595   0.00907  -0.0125   0.7579   0.0130
  -7.250  -0.6518   0.01544   0.00843  -0.0113   0.7419   0.0140
  -7.000  -0.6305   0.01486   0.00773  -0.0101   0.7269   0.0152
  -6.750  -0.6083   0.01433   0.00713  -0.0091   0.7130   0.0175
  -6.500  -0.5861   0.01376   0.00648  -0.0080   0.6999   0.0217
  -6.250  -0.5638   0.01317   0.00585  -0.0070   0.6874   0.0307
  -6.000  -0.5421   0.01253   0.00528  -0.0059   0.6751   0.0538
  -5.750  -0.5221   0.01168   0.00472  -0.0048   0.6629   0.1098
  -5.500  -0.5004   0.01104   0.00434  -0.0039   0.6512   0.1704
  -5.250  -0.4763   0.01067   0.00408  -0.0032   0.6402   0.2107
  -5.000  -0.4510   0.01042   0.00388  -0.0027   0.6292   0.2407
  -4.750  -0.4252   0.01021   0.00372  -0.0023   0.6186   0.2670
  -4.500  -0.3990   0.01006   0.00356  -0.0019   0.6086   0.2900
  -4.250  -0.3725   0.00993   0.00341  -0.0016   0.5982   0.3082
  -4.000  -0.3461   0.00978   0.00328  -0.0012   0.5882   0.3271
  -3.750  -0.3199   0.00966   0.00316  -0.0008   0.5789   0.3507
  -3.500  -0.2932   0.00954   0.00305  -0.0005   0.5694   0.3713
  -3.250  -0.2666   0.00943   0.00294  -0.0002   0.5610   0.3884
  -3.000  -0.2399   0.00933   0.00283   0.0001   0.5524   0.4053
  -2.750  -0.2131   0.00923   0.00273   0.0004   0.5445   0.4230
  -2.500  -0.1864   0.00914   0.00264   0.0007   0.5364   0.4416
  -2.250  -0.1595   0.00906   0.00257   0.0010   0.5287   0.4612
  -2.000  -0.1328   0.00897   0.00249   0.0013   0.5213   0.4817
  -1.750  -0.1064   0.00888   0.00243   0.0017   0.5147   0.5040
  -1.500  -0.0798   0.00879   0.00238   0.0020   0.5079   0.5284
  -1.250  -0.0539   0.00872   0.00234   0.0025   0.5020   0.5551
  -1.000  -0.0276   0.00859   0.00232   0.0029   0.4959   0.5843
  -0.750  -0.0019   0.00851   0.00230   0.0034   0.4900   0.6160
  -0.500   0.0238   0.00843   0.00230   0.0040   0.4846   0.6497
  -0.250   0.0496   0.00832   0.00230   0.0046   0.4792   0.6842
   0.000   0.0750   0.00826   0.00232   0.0052   0.4743   0.7199
   0.250   0.1005   0.00821   0.00236   0.0059   0.4698   0.7551
   0.500   0.1266   0.00813   0.00241   0.0065   0.4649   0.7897
   0.750   0.1533   0.00810   0.00246   0.0069   0.4602   0.8235
   1.000   0.1810   0.00816   0.00254   0.0072   0.4559   0.8541
   1.250   0.2115   0.00817   0.00264   0.0069   0.4517   0.8815
   1.500   0.2446   0.00824   0.00274   0.0061   0.4471   0.9045
   1.750   0.2793   0.00838   0.00285   0.0048   0.4428   0.9223
   2.000   0.3168   0.00855   0.00300   0.0030   0.4386   0.9344
   2.250   0.3534   0.00867   0.00313   0.0013   0.4342   0.9443
   2.500   0.3861   0.00882   0.00325   0.0004   0.4300   0.9547
   2.750   0.4274   0.00905   0.00340  -0.0023   0.4257   0.9587
   3.000   0.4654   0.00918   0.00354  -0.0044   0.4217   0.9645
   3.250   0.5016   0.00930   0.00367  -0.0061   0.4175   0.9704
   3.500   0.5421   0.00944   0.00377  -0.0087   0.4133   0.9739
   3.750   0.5791   0.00963   0.00392  -0.0106   0.4093   0.9790
   4.000   0.6167   0.00971   0.00404  -0.0127   0.4052   0.9833
   4.250   0.6576   0.00978   0.00411  -0.0155   0.4009   0.9864
   4.500   0.6961   0.00991   0.00420  -0.0178   0.3966   0.9903
   4.750   0.7344   0.01002   0.00433  -0.0201   0.3924   0.9940
   5.000   0.7752   0.01003   0.00438  -0.0230   0.3874   0.9972
   5.250   0.8140   0.01010   0.00443  -0.0254   0.3826   1.0000
   5.500   0.8368   0.01022   0.00454  -0.0246   0.3784   1.0000
   5.750   0.8601   0.01026   0.00464  -0.0239   0.3740   1.0000
   6.000   0.8832   0.01033   0.00474  -0.0231   0.3694   1.0000
   6.250   0.9058   0.01050   0.00487  -0.0223   0.3648   1.0000
   6.500   0.9291   0.01056   0.00501  -0.0215   0.3602   1.0000
   6.750   0.9523   0.01065   0.00514  -0.0207   0.3550   1.0000
   7.000   0.9748   0.01083   0.00528  -0.0198   0.3498   1.0000
   7.250   0.9982   0.01091   0.00545  -0.0191   0.3443   1.0000
   7.500   1.0211   0.01103   0.00560  -0.0183   0.3381   1.0000
   7.750   1.0437   0.01119   0.00579  -0.0174   0.3321   1.0000
   8.000   1.0667   0.01131   0.00596  -0.0166   0.3249   1.0000
   8.250   1.0888   0.01150   0.00616  -0.0157   0.3179   1.0000
   8.500   1.1113   0.01166   0.00636  -0.0148   0.3092   1.0000
   8.750   1.1332   0.01186   0.00660  -0.0139   0.3001   1.0000
   9.000   1.1541   0.01212   0.00685  -0.0128   0.2896   1.0000
   9.250   1.1749   0.01239   0.00713  -0.0117   0.2778   1.0000
   9.500   1.1947   0.01272   0.00745  -0.0105   0.2648   1.0000
   9.750   1.2132   0.01313   0.00784  -0.0092   0.2506   1.0000
  10.000   1.2302   0.01361   0.00828  -0.0076   0.2359   1.0000
  10.250   1.2460   0.01414   0.00877  -0.0059   0.2213   1.0000
  10.500   1.2603   0.01472   0.00932  -0.0040   0.2065   1.0000
  10.750   1.2732   0.01536   0.00991  -0.0020   0.1919   1.0000
  11.000   1.2851   0.01600   0.01052   0.0002   0.1788   1.0000
  11.250   1.2950   0.01669   0.01120   0.0026   0.1661   1.0000
  11.500   1.3026   0.01740   0.01191   0.0053   0.1556   1.0000
  11.750   1.3021   0.01820   0.01269   0.0093   0.1464   1.0000
  12.000   1.3020   0.01919   0.01366   0.0126   0.1368   1.0000
  12.250   1.3048   0.02029   0.01480   0.0149   0.1285   1.0000
  12.500   1.3050   0.02181   0.01632   0.0167   0.1204   1.0000
  12.750   1.3069   0.02347   0.01800   0.0180   0.1120   1.0000
  13.000   1.3078   0.02540   0.01995   0.0188   0.1040   1.0000
  13.500   1.3059   0.03007   0.02467   0.0197   0.0892   1.0000
  13.750   1.3018   0.03287   0.02749   0.0198   0.0825   1.0000
  14.000   1.2995   0.03557   0.03023   0.0198   0.0768   1.0000
  14.250   1.2930   0.03877   0.03345   0.0196   0.0707   1.0000
  14.500   1.2878   0.04188   0.03660   0.0194   0.0653   1.0000
  14.750   1.2795   0.04537   0.04012   0.0190   0.0605   1.0000
  15.000   1.2732   0.04869   0.04348   0.0186   0.0556   1.0000
  15.250   1.2626   0.05261   0.04742   0.0180   0.0513   1.0000
  15.500   1.2576   0.05601   0.05088   0.0173   0.0472   1.0000
  15.750   1.2479   0.06004   0.05494   0.0165   0.0438   1.0000
  16.000   1.2412   0.06381   0.05876   0.0156   0.0400   1.0000
  16.250   1.2330   0.06781   0.06279   0.0146   0.0367   1.0000
  16.500   1.2239   0.07203   0.06705   0.0135   0.0341   1.0000
  16.750   1.2190   0.07576   0.07085   0.0125   0.0319   1.0000
  17.000   1.2103   0.08003   0.07517   0.0112   0.0294   1.0000
  17.250   1.2012   0.08447   0.07965   0.0099   0.0275   1.0000
  17.500   1.1966   0.08835   0.08361   0.0087   0.0255   1.0000
  17.750   1.1890   0.09266   0.08797   0.0073   0.0242   1.0000
  18.000   1.1783   0.09752   0.09288   0.0057   0.0229   1.0000
  18.250   1.1700   0.10212   0.09756   0.0041   0.0218   1.0000
  18.500   1.1673   0.10590   0.10141   0.0027   0.0201   1.0000
  18.750   1.1586   0.11067   0.10623   0.0009   0.0191   1.0000
  19.000   1.1487   0.11570   0.11132  -0.0011   0.0184   1.0000
<< Back to MH 104 15.28% (mh104-il)

Polar data table (+)

Polar graphs


<< Back to MH 104 15.28% (mh104-il)