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

MH 93 15.98% (mh93-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: MH 93 15.98% (mh93-il)
Reynolds number: 200,000
Max Cl/Cd: 53.24 at α=9.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-mh93-il-200000-n5.txt
Download as CSV file: xf-mh93-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 93  15.98%                                   
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -15.500  -0.7798   0.11606   0.11199   0.0117   1.0000   0.0125
 -15.250  -0.8019   0.10595   0.10176   0.0051   1.0000   0.0123
 -15.000  -0.8306   0.09512   0.09072  -0.0021   1.0000   0.0122
 -14.750  -0.8544   0.08618   0.08157  -0.0080   1.0000   0.0122
 -14.500  -0.8764   0.07837   0.07354  -0.0128   1.0000   0.0122
 -14.250  -0.8949   0.07181   0.06675  -0.0166   1.0000   0.0121
 -14.000  -0.9092   0.06641   0.06114  -0.0192   1.0000   0.0121
 -13.750  -0.9218   0.06157   0.05610  -0.0210   1.0000   0.0121
 -13.500  -0.9329   0.05724   0.05155  -0.0222   1.0000   0.0122
 -13.250  -0.9400   0.05362   0.04772  -0.0227   1.0000   0.0122
 -13.000  -0.9469   0.05016   0.04402  -0.0227   1.0000   0.0123
 -12.750  -0.9522   0.04700   0.04059  -0.0222   1.0000   0.0124
 -12.500  -0.9523   0.04444   0.03781  -0.0214   1.0000   0.0125
 -12.250  -0.9486   0.04226   0.03552  -0.0206   1.0000   0.0126
 -12.000  -0.9429   0.04028   0.03343  -0.0196   1.0000   0.0127
 -11.750  -0.9359   0.03853   0.03160  -0.0186   1.0000   0.0128
 -11.500  -0.9274   0.03693   0.02990  -0.0175   1.0000   0.0130
 -11.250  -0.9181   0.03547   0.02837  -0.0163   1.0000   0.0132
 -11.000  -0.9076   0.03414   0.02696  -0.0151   1.0000   0.0136
 -10.750  -0.8957   0.03277   0.02549  -0.0139   1.0000   0.0138
 -10.500  -0.8829   0.03152   0.02413  -0.0126   1.0000   0.0143
 -10.250  -0.8687   0.03030   0.02279  -0.0114   1.0000   0.0147
 -10.000  -0.8536   0.02913   0.02149  -0.0102   1.0000   0.0152
  -9.750  -0.8390   0.02794   0.02028  -0.0090   1.0000   0.0155
  -9.500  -0.8239   0.02690   0.01924  -0.0078   1.0000   0.0158
  -9.250  -0.8083   0.02591   0.01824  -0.0066   1.0000   0.0162
  -9.000  -0.7894   0.02495   0.01724  -0.0060   0.9536   0.0166
  -8.750  -0.7687   0.02404   0.01619  -0.0054   0.9070   0.0173
  -8.250  -0.7442   0.02262   0.01451  -0.0003   0.8555   0.0183
  -8.000  -0.7326   0.02197   0.01378   0.0023   0.8368   0.0188
  -7.750  -0.7187   0.02135   0.01308   0.0047   0.8201   0.0197
  -7.500  -0.7028   0.02077   0.01238   0.0066   0.8050   0.0206
  -7.250  -0.6860   0.02017   0.01168   0.0085   0.7907   0.0219
  -7.000  -0.6675   0.01962   0.01107   0.0101   0.7769   0.0238
  -6.750  -0.6486   0.01908   0.01045   0.0116   0.7641   0.0261
  -6.500  -0.6290   0.01859   0.00986   0.0131   0.7519   0.0295
  -6.250  -0.6089   0.01804   0.00928   0.0144   0.7393   0.0340
  -6.000  -0.5887   0.01750   0.00872   0.0157   0.7274   0.0405
  -5.500  -0.5486   0.01634   0.00765   0.0183   0.7042   0.0752
  -5.250  -0.5298   0.01564   0.00714   0.0197   0.6933   0.1146
  -5.000  -0.5120   0.01486   0.00665   0.0212   0.6821   0.1758
  -4.750  -0.4945   0.01409   0.00622   0.0228   0.6712   0.2494
  -4.500  -0.4761   0.01349   0.00587   0.0243   0.6609   0.3167
  -4.250  -0.4561   0.01299   0.00559   0.0257   0.6496   0.3744
  -4.000  -0.4359   0.01256   0.00534   0.0271   0.6394   0.4282
  -3.750  -0.4147   0.01219   0.00514   0.0285   0.6284   0.4803
  -3.500  -0.3930   0.01187   0.00498   0.0298   0.6180   0.5301
  -3.250  -0.3701   0.01161   0.00485   0.0310   0.6075   0.5751
  -3.000  -0.3454   0.01144   0.00476   0.0319   0.5967   0.6098
  -2.500  -0.2934   0.01127   0.00463   0.0333   0.5755   0.6637
  -2.250  -0.2667   0.01126   0.00461   0.0339   0.5653   0.6875
  -2.000  -0.2398   0.01127   0.00459   0.0344   0.5545   0.7092
  -1.750  -0.2126   0.01130   0.00458   0.0349   0.5442   0.7276
  -1.500  -0.1851   0.01135   0.00457   0.0353   0.5338   0.7430
  -1.250  -0.1573   0.01141   0.00458   0.0356   0.5233   0.7565
  -1.000  -0.1301   0.01148   0.00457   0.0360   0.5134   0.7691
  -0.750  -0.1028   0.01154   0.00457   0.0363   0.5028   0.7812
  -0.500  -0.0746   0.01165   0.00461   0.0366   0.4931   0.7908
  -0.250  -0.0479   0.01171   0.00460   0.0370   0.4828   0.8017
   0.000  -0.0194   0.01183   0.00467   0.0371   0.4729   0.8098
   0.250   0.0070   0.01192   0.00467   0.0376   0.4630   0.8197
   0.500   0.0357   0.01205   0.00477   0.0377   0.4533   0.8269
   0.750   0.0611   0.01215   0.00476   0.0383   0.4439   0.8368
   1.000   0.0903   0.01230   0.00490   0.0383   0.4341   0.8431
   1.500   0.1443   0.01256   0.00505   0.0390   0.4158   0.8584
   1.750   0.1722   0.01273   0.00514   0.0392   0.4071   0.8644
   2.000   0.1972   0.01281   0.00519   0.0398   0.3982   0.8722
   2.250   0.2259   0.01298   0.00529   0.0398   0.3900   0.8766
   2.500   0.2545   0.01311   0.00542   0.0398   0.3811   0.8816
   3.000   0.3071   0.01337   0.00560   0.0404   0.3653   0.8931
   3.250   0.3360   0.01355   0.00573   0.0402   0.3575   0.8972
   3.500   0.3633   0.01370   0.00586   0.0403   0.3498   0.9024
   3.750   0.3871   0.01382   0.00595   0.0410   0.3428   0.9090
   4.000   0.4176   0.01402   0.00612   0.0405   0.3358   0.9123
   4.250   0.4468   0.01419   0.00629   0.0402   0.3282   0.9166
   4.500   0.4719   0.01438   0.00642   0.0406   0.3219   0.9226
   4.750   0.4998   0.01454   0.00660   0.0405   0.3155   0.9273
   5.000   0.5309   0.01475   0.00680   0.0397   0.3088   0.9306
   5.250   0.5600   0.01496   0.00700   0.0393   0.3027   0.9349
   5.500   0.5833   0.01512   0.00717   0.0400   0.2964   0.9411
   5.750   0.6150   0.01536   0.00739   0.0389   0.2905   0.9437
   6.000   0.6467   0.01559   0.00764   0.0379   0.2848   0.9465
   6.250   0.6768   0.01581   0.00789   0.0371   0.2786   0.9502
   6.500   0.7011   0.01606   0.00810   0.0375   0.2733   0.9555
   6.750   0.7327   0.01629   0.00839   0.0364   0.2676   0.9581
   7.000   0.7651   0.01656   0.00869   0.0350   0.2618   0.9606
   7.250   0.7956   0.01689   0.00897   0.0340   0.2567   0.9638
   7.500   0.8242   0.01714   0.00930   0.0334   0.2510   0.9677
   7.750   0.8532   0.01743   0.00963   0.0327   0.2457   0.9711
   8.250   0.9168   0.01811   0.01038   0.0299   0.2351   0.9765
   8.500   0.9450   0.01845   0.01076   0.0292   0.2298   0.9804
   8.750   0.9734   0.01887   0.01115   0.0283   0.2250   0.9837
   9.000   1.0052   0.01921   0.01162   0.0268   0.2192   0.9866
   9.250   1.0345   0.01962   0.01206   0.0256   0.2137   0.9904
   9.500   1.0624   0.02009   0.01255   0.0247   0.2088   0.9942
   9.750   1.0920   0.02051   0.01308   0.0234   0.2032   0.9978
  10.000   1.1114   0.02097   0.01356   0.0240   0.1985   1.0000
  10.250   1.1151   0.02140   0.01398   0.0274   0.1955   1.0000
  10.500   1.1203   0.02177   0.01445   0.0307   0.1919   1.0000
  10.750   1.1243   0.02218   0.01492   0.0340   0.1883   1.0000
  11.000   1.1252   0.02265   0.01541   0.0377   0.1850   1.0000
  11.250   1.1251   0.02324   0.01599   0.0412   0.1820   1.0000
  11.500   1.1313   0.02392   0.01673   0.0435   0.1787   1.0000
  11.750   1.1396   0.02468   0.01758   0.0451   0.1747   1.0000
  12.000   1.1470   0.02558   0.01852   0.0466   0.1709   1.0000
  12.250   1.1533   0.02665   0.01959   0.0478   0.1676   1.0000
  12.500   1.1623   0.02771   0.02075   0.0487   0.1638   1.0000
  12.750   1.1703   0.02888   0.02202   0.0494   0.1600   1.0000
  13.000   1.1762   0.03025   0.02343   0.0501   0.1563   1.0000
  13.250   1.1808   0.03180   0.02499   0.0506   0.1529   1.0000
  13.500   1.1876   0.03331   0.02663   0.0509   0.1489   1.0000
  13.750   1.1920   0.03504   0.02845   0.0511   0.1452   1.0000
  14.000   1.1939   0.03703   0.03045   0.0512   0.1418   1.0000
  14.250   1.1967   0.03905   0.03257   0.0511   0.1383   1.0000
  14.500   1.1991   0.04120   0.03483   0.0509   0.1346   1.0000
  14.750   1.1986   0.04366   0.03735   0.0505   0.1311   1.0000
  15.000   1.1961   0.04634   0.04004   0.0500   0.1280   1.0000
  15.250   1.1961   0.04897   0.04281   0.0493   0.1245   1.0000
  15.500   1.1938   0.05190   0.04584   0.0485   0.1212   1.0000
  15.750   1.1895   0.05515   0.04913   0.0474   0.1180   1.0000
  16.000   1.1857   0.05842   0.05245   0.0463   0.1153   1.0000
  16.250   1.1814   0.06194   0.05611   0.0450   0.1120   1.0000
  16.500   1.1756   0.06572   0.05997   0.0435   0.1089   1.0000
  16.750   1.1694   0.06960   0.06388   0.0418   0.1062   1.0000
  17.000   1.1634   0.07355   0.06790   0.0402   0.1035   1.0000
  17.250   1.1556   0.07791   0.07239   0.0382   0.1006   1.0000
  17.500   1.1475   0.08238   0.07695   0.0362   0.0979   1.0000
  17.750   1.1414   0.08656   0.08115   0.0342   0.0953   1.0000
  18.000   1.1336   0.09112   0.08578   0.0321   0.0927   1.0000
  18.250   1.1237   0.09614   0.09093   0.0296   0.0902   1.0000
  18.500   1.1143   0.10115   0.09602   0.0271   0.0877   1.0000
  18.750   1.1102   0.10525   0.10013   0.0250   0.0853   1.0000
  19.000   1.1029   0.11000   0.10495   0.0226   0.0830   1.0000
  19.250   1.0905   0.11579   0.11088   0.0196   0.0806   1.0000
<< Back to MH 93 15.98% (mh93-il)

Polar data table (+)

Polar graphs


<< Back to MH 93 15.98% (mh93-il)