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MH 112 Airfoil (mh112-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: MH 112 Airfoil (mh112-il)
Reynolds number: 1,000,000
Max Cl/Cd: 147.7 at α=4°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-mh112-il-1000000.txt
Download as CSV file: xf-mh112-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 112  Airfoil                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000   0.2272   0.08713   0.08444  -0.1645   0.8418   0.0171
 -10.750   0.2377   0.08562   0.08290  -0.1647   0.8347   0.0173
 -10.500   0.1201   0.06060   0.05780  -0.1719   0.8245   0.0143
 -10.250  -0.0059   0.03933   0.03621  -0.1836   0.8108   0.0137
 -10.000  -0.0448   0.03180   0.02846  -0.1888   0.8005   0.0135
  -9.750  -0.0669   0.02722   0.02373  -0.1931   0.7924   0.0134
  -9.500  -0.0667   0.02445   0.02068  -0.1953   0.7857   0.0134
  -9.250  -0.0581   0.02227   0.01826  -0.1961   0.7801   0.0134
  -9.000  -0.0425   0.02066   0.01647  -0.1965   0.7754   0.0134
  -8.750  -0.0241   0.01922   0.01483  -0.1968   0.7705   0.0134
  -8.500  -0.0032   0.01809   0.01350  -0.1969   0.7655   0.0134
  -8.250   0.0197   0.01708   0.01235  -0.1971   0.7612   0.0134
  -8.000   0.0437   0.01615   0.01129  -0.1972   0.7571   0.0134
  -7.750   0.0684   0.01533   0.01035  -0.1973   0.7526   0.0135
  -7.500   0.0938   0.01468   0.00957  -0.1974   0.7480   0.0135
  -7.250   0.1200   0.01409   0.00887  -0.1975   0.7435   0.0136
  -7.000   0.1467   0.01355   0.00826  -0.1976   0.7397   0.0137
  -6.750   0.1740   0.01317   0.00782  -0.1977   0.7354   0.0139
  -6.500   0.2010   0.01273   0.00729  -0.1977   0.7311   0.0140
  -6.250   0.2283   0.01239   0.00685  -0.1978   0.7263   0.0140
  -6.000   0.2555   0.01170   0.00610  -0.1980   0.7224   0.0142
  -5.750   0.2834   0.01114   0.00549  -0.1983   0.7183   0.0144
  -5.500   0.3114   0.01075   0.00505  -0.1985   0.7140   0.0147
  -5.250   0.3393   0.01047   0.00471  -0.1986   0.7093   0.0150
  -5.000   0.3677   0.01023   0.00442  -0.1987   0.7050   0.0154
  -4.750   0.3963   0.00998   0.00415  -0.1989   0.7008   0.0160
  -4.500   0.4248   0.00977   0.00390  -0.1990   0.6963   0.0167
  -4.250   0.4531   0.00952   0.00359  -0.1991   0.6917   0.0178
  -4.000   0.4815   0.00937   0.00340  -0.1992   0.6870   0.0193
  -3.750   0.5103   0.00916   0.00320  -0.1994   0.6827   0.0217
  -3.500   0.5388   0.00898   0.00301  -0.1995   0.6779   0.0261
  -3.250   0.5670   0.00883   0.00286  -0.1995   0.6730   0.0352
  -3.000   0.5953   0.00870   0.00276  -0.1996   0.6683   0.0486
  -2.750   0.6240   0.00856   0.00267  -0.1998   0.6636   0.0619
  -2.500   0.6521   0.00847   0.00260  -0.1998   0.6584   0.0762
  -2.250   0.6797   0.00841   0.00255  -0.1998   0.6532   0.0932
  -2.000   0.7082   0.00830   0.00252  -0.2000   0.6486   0.1154
  -1.750   0.7366   0.00819   0.00249  -0.2001   0.6433   0.1427
  -1.500   0.7642   0.00812   0.00248  -0.2001   0.6378   0.1739
  -1.250   0.7917   0.00806   0.00248  -0.2001   0.6324   0.2078
  -0.750   0.8472   0.00795   0.00250  -0.2001   0.6206   0.2739
  -0.500   0.8737   0.00797   0.00254  -0.1998   0.6141   0.3038
  -0.250   0.9014   0.00792   0.00257  -0.1998   0.6077   0.3370
   0.000   0.9277   0.00795   0.00261  -0.1995   0.6009   0.3691
   0.250   0.9545   0.00796   0.00268  -0.1993   0.5951   0.4044
   0.500   0.9817   0.00797   0.00274  -0.1992   0.5892   0.4365
   0.750   1.0074   0.00802   0.00282  -0.1988   0.5828   0.4674
   1.000   1.0336   0.00807   0.00290  -0.1985   0.5770   0.4964
   1.250   1.0602   0.00811   0.00298  -0.1982   0.5712   0.5230
   1.500   1.0851   0.00821   0.00307  -0.1977   0.5648   0.5471
   1.750   1.1105   0.00828   0.00318  -0.1972   0.5590   0.5714
   2.000   1.1364   0.00834   0.00327  -0.1968   0.5531   0.5947
   2.250   1.1603   0.00844   0.00339  -0.1961   0.5467   0.6182
   2.500   1.1844   0.00853   0.00350  -0.1953   0.5408   0.6440
   3.000   1.2296   0.00870   0.00375  -0.1933   0.5284   0.7000
   3.250   1.2522   0.00878   0.00390  -0.1923   0.5225   0.7358
   3.500   1.2745   0.00884   0.00406  -0.1912   0.5163   0.7828
   3.750   1.2920   0.00892   0.00426  -0.1891   0.5099   0.8538
   4.000   1.3086   0.00886   0.00435  -0.1868   0.5044   1.0000
   4.250   1.3311   0.00903   0.00450  -0.1858   0.4978   1.0000
   4.500   1.3506   0.00929   0.00470  -0.1843   0.4909   1.0000
   4.750   1.3740   0.00945   0.00485  -0.1836   0.4850   1.0000
   5.000   1.3950   0.00968   0.00504  -0.1824   0.4779   1.0000
   5.250   1.4142   0.00995   0.00527  -0.1810   0.4712   1.0000
   5.500   1.4363   0.01015   0.00546  -0.1800   0.4646   1.0000
   5.750   1.4546   0.01046   0.00573  -0.1784   0.4570   1.0000
   6.000   1.4749   0.01072   0.00597  -0.1772   0.4501   1.0000
   6.250   1.4939   0.01103   0.00625  -0.1758   0.4424   1.0000
   6.500   1.5117   0.01138   0.00657  -0.1742   0.4351   1.0000
   6.750   1.5307   0.01169   0.00687  -0.1729   0.4272   1.0000
   7.000   1.5465   0.01214   0.00727  -0.1710   0.4186   1.0000
   7.250   1.5648   0.01250   0.00762  -0.1696   0.4102   1.0000
   7.500   1.5794   0.01301   0.00809  -0.1676   0.4013   1.0000
   7.750   1.5965   0.01345   0.00850  -0.1661   0.3924   1.0000
   8.000   1.6103   0.01403   0.00905  -0.1641   0.3829   1.0000
   8.250   1.6250   0.01459   0.00958  -0.1623   0.3731   1.0000
   8.500   1.6387   0.01522   0.01018  -0.1605   0.3638   1.0000
   8.750   1.6506   0.01596   0.01087  -0.1584   0.3535   1.0000
   9.000   1.6649   0.01661   0.01151  -0.1567   0.3447   1.0000
   9.250   1.6749   0.01749   0.01234  -0.1544   0.3347   1.0000
   9.500   1.6891   0.01819   0.01304  -0.1528   0.3265   1.0000
   9.750   1.6990   0.01914   0.01395  -0.1507   0.3177   1.0000
  10.000   1.7124   0.01993   0.01474  -0.1491   0.3101   1.0000
  10.250   1.7213   0.02100   0.01577  -0.1471   0.3016   1.0000
  10.500   1.7352   0.02181   0.01659  -0.1457   0.2953   1.0000
  10.750   1.7441   0.02294   0.01770  -0.1437   0.2871   1.0000
  11.000   1.7566   0.02388   0.01865  -0.1423   0.2815   1.0000
  11.250   1.7675   0.02494   0.01971  -0.1407   0.2745   1.0000
  11.500   1.7758   0.02622   0.02097  -0.1389   0.2681   1.0000
  11.750   1.7888   0.02720   0.02197  -0.1376   0.2623   1.0000
  12.000   1.7962   0.02861   0.02337  -0.1359   0.2556   1.0000
  12.250   1.8073   0.02977   0.02455  -0.1346   0.2501   1.0000
  12.500   1.8171   0.03106   0.02585  -0.1332   0.2440   1.0000
  12.750   1.8229   0.03269   0.02746  -0.1316   0.2373   1.0000
  13.000   1.8348   0.03388   0.02869  -0.1305   0.2323   1.0000
  13.250   1.8411   0.03556   0.03036  -0.1291   0.2258   1.0000
  13.500   1.8491   0.03711   0.03193  -0.1278   0.2201   1.0000
  13.750   1.8571   0.03872   0.03355  -0.1266   0.2142   1.0000
  14.000   1.8606   0.04075   0.03557  -0.1252   0.2076   1.0000
  14.250   1.8698   0.04231   0.03717  -0.1242   0.2024   1.0000
  14.500   1.8744   0.04433   0.03918  -0.1230   0.1962   1.0000
  14.750   1.8796   0.04633   0.04120  -0.1220   0.1907   1.0000
  15.000   1.8859   0.04825   0.04314  -0.1210   0.1852   1.0000
  15.250   1.8866   0.05079   0.04568  -0.1199   0.1792   1.0000
  15.500   1.8944   0.05264   0.04757  -0.1192   0.1745   1.0000
  15.750   1.8958   0.05520   0.05015  -0.1183   0.1689   1.0000
  16.000   1.8993   0.05756   0.05254  -0.1175   0.1640   1.0000
  16.250   1.9030   0.05996   0.05496  -0.1169   0.1591   1.0000
  16.500   1.9017   0.06295   0.05796  -0.1162   0.1536   1.0000
  16.750   1.9066   0.06529   0.06035  -0.1157   0.1494   1.0000
  17.000   1.9071   0.06817   0.06326  -0.1152   0.1446   1.0000
  17.250   1.9069   0.07118   0.06629  -0.1148   0.1400   1.0000
  17.500   1.9094   0.07390   0.06906  -0.1145   0.1360   1.0000
  17.750   1.9083   0.07710   0.07228  -0.1143   0.1313   1.0000
  18.000   1.9074   0.08035   0.07557  -0.1141   0.1274   1.0000
  18.250   1.9093   0.08322   0.07849  -0.1141   0.1233   1.0000
  18.500   1.9047   0.08702   0.08231  -0.1141   0.1192   1.0000
  18.750   1.9054   0.09012   0.08546  -0.1142   0.1156   1.0000
  19.000   1.9041   0.09354   0.08893  -0.1144   0.1120   1.0000
  19.250   1.8986   0.09757   0.09298  -0.1148   0.1080   1.0000
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