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MH 113 14.62% (mh113-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: MH 113 14.62% (mh113-il)
Reynolds number: 100,000
Max Cl/Cd: 55.98 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-mh113-il-100000-n5.txt
Download as CSV file: xf-mh113-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 113  14.62%                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750   0.0178   0.10873   0.10344  -0.1041   0.9220   0.0609
  -9.500   0.0245   0.10535   0.10006  -0.1091   0.9178   0.0620
  -9.250   0.0382   0.10146   0.09616  -0.1142   0.9150   0.0623
  -8.750   0.0590   0.09207   0.08671  -0.1166   0.9038   0.0401
  -8.500   0.0736   0.08831   0.08293  -0.1202   0.9002   0.0397
  -8.250   0.0816   0.08514   0.07976  -0.1222   0.8941   0.0393
  -8.000   0.0869   0.08199   0.07662  -0.1239   0.8870   0.0392
  -7.750   0.0989   0.07809   0.07270  -0.1276   0.8828   0.0389
  -7.500   0.0958   0.07544   0.07009  -0.1276   0.8736   0.0382
  -7.250   0.0788   0.06820   0.06283  -0.1326   0.8653   0.0358
  -7.000   0.0693   0.06635   0.06103  -0.1307   0.8548   0.0356
  -6.750   0.0770   0.06216   0.05682  -0.1349   0.8493   0.0353
  -6.500   0.0680   0.05848   0.05315  -0.1364   0.8391   0.0349
  -6.000   0.0650   0.04205   0.03598  -0.1534   0.8217   0.0335
  -5.750   0.0898   0.03672   0.02999  -0.1592   0.8170   0.0336
  -5.500   0.1251   0.03287   0.02547  -0.1639   0.8144   0.0342
  -5.250   0.1437   0.03095   0.02313  -0.1638   0.8075   0.0348
  -5.000   0.1713   0.02918   0.02093  -0.1648   0.8024   0.0361
  -4.750   0.2051   0.02814   0.01980  -0.1665   0.7992   0.0382
  -4.500   0.2428   0.02666   0.01798  -0.1686   0.7968   0.0405
  -4.250   0.2596   0.02602   0.01720  -0.1670   0.7893   0.0417
  -4.000   0.2887   0.02521   0.01634  -0.1675   0.7846   0.0436
  -3.750   0.3241   0.02424   0.01520  -0.1689   0.7814   0.0467
  -3.500   0.3621   0.02340   0.01430  -0.1708   0.7789   0.0520
  -3.250   0.3760   0.02328   0.01418  -0.1686   0.7704   0.0563
  -3.000   0.4090   0.02261   0.01346  -0.1697   0.7662   0.0647
  -2.750   0.4463   0.02191   0.01272  -0.1715   0.7631   0.0820
  -2.500   0.4693   0.02167   0.01258  -0.1709   0.7566   0.1034
  -2.250   0.4969   0.02134   0.01233  -0.1711   0.7508   0.1368
  -2.000   0.5323   0.02083   0.01194  -0.1726   0.7471   0.1816
  -1.750   0.5642   0.02049   0.01168  -0.1734   0.7426   0.2286
  -1.500   0.5837   0.02053   0.01183  -0.1721   0.7350   0.2695
  -1.250   0.6169   0.02021   0.01159  -0.1730   0.7306   0.3239
  -1.000   0.6533   0.01986   0.01130  -0.1744   0.7271   0.3825
  -0.750   0.6683   0.02010   0.01166  -0.1722   0.7183   0.4252
  -0.500   0.7003   0.01988   0.01150  -0.1727   0.7136   0.4800
  -0.250   0.7315   0.01972   0.01137  -0.1730   0.7089   0.5327
   0.000   0.7491   0.01991   0.01165  -0.1711   0.7007   0.5761
   0.250   0.7801   0.01970   0.01148  -0.1712   0.6959   0.6268
   0.500   0.8025   0.01974   0.01157  -0.1700   0.6894   0.6736
   0.750   0.8223   0.01975   0.01166  -0.1681   0.6823   0.7219
   1.000   0.8499   0.01946   0.01140  -0.1674   0.6777   0.7808
   1.250   0.8570   0.01955   0.01163  -0.1631   0.6694   0.8527
   1.500   0.8842   0.01933   0.01137  -0.1626   0.6631   1.0000
   1.750   0.9148   0.01942   0.01131  -0.1632   0.6570   1.0000
   2.000   0.9371   0.01971   0.01150  -0.1624   0.6489   1.0000
   2.250   0.9728   0.01964   0.01127  -0.1637   0.6436   1.0000
   2.500   0.9901   0.02005   0.01164  -0.1621   0.6347   1.0000
   2.750   1.0215   0.02008   0.01155  -0.1626   0.6283   1.0000
   3.000   1.0433   0.02039   0.01179  -0.1617   0.6204   1.0000
   3.250   1.0698   0.02054   0.01186  -0.1615   0.6129   1.0000
   3.500   1.0956   0.02074   0.01198  -0.1612   0.6057   1.0000
   3.750   1.1173   0.02102   0.01222  -0.1602   0.5973   1.0000
   4.000   1.1458   0.02114   0.01225  -0.1603   0.5903   1.0000
   4.250   1.1631   0.02152   0.01262  -0.1586   0.5814   1.0000
   4.500   1.1931   0.02162   0.01262  -0.1589   0.5745   1.0000
   4.750   1.2073   0.02208   0.01310  -0.1567   0.5652   1.0000
   5.000   1.2377   0.02218   0.01309  -0.1571   0.5583   1.0000
   5.250   1.2502   0.02272   0.01367  -0.1547   0.5487   1.0000
   5.500   1.2792   0.02285   0.01371  -0.1549   0.5415   1.0000
   5.750   1.2914   0.02344   0.01434  -0.1525   0.5321   1.0000
   6.000   1.3185   0.02362   0.01445  -0.1524   0.5245   1.0000
   6.250   1.3305   0.02425   0.01512  -0.1500   0.5150   1.0000
   6.500   1.3561   0.02449   0.01529  -0.1497   0.5075   1.0000
   6.750   1.3676   0.02517   0.01602  -0.1474   0.4980   1.0000
   7.000   1.3913   0.02548   0.01628  -0.1468   0.4903   1.0000
   7.250   1.4027   0.02620   0.01706  -0.1446   0.4810   1.0000
   7.500   1.4241   0.02660   0.01741  -0.1437   0.4731   1.0000
   7.750   1.4356   0.02737   0.01823  -0.1416   0.4640   1.0000
   8.000   1.4553   0.02785   0.01869  -0.1405   0.4561   1.0000
   8.250   1.4661   0.02869   0.01958  -0.1384   0.4469   1.0000
   8.500   1.4841   0.02926   0.02013  -0.1372   0.4391   1.0000
   8.750   1.4943   0.03018   0.02111  -0.1351   0.4301   1.0000
   9.000   1.5110   0.03083   0.02177  -0.1338   0.4223   1.0000
   9.250   1.5202   0.03185   0.02285  -0.1318   0.4134   1.0000
   9.500   1.5357   0.03260   0.02359  -0.1304   0.4056   1.0000
   9.750   1.5439   0.03374   0.02482  -0.1284   0.3969   1.0000
  10.000   1.5583   0.03457   0.02565  -0.1270   0.3892   1.0000
  10.250   1.5651   0.03586   0.02702  -0.1250   0.3806   1.0000
  10.500   1.5788   0.03676   0.02792  -0.1237   0.3731   1.0000
  10.750   1.5840   0.03823   0.02951  -0.1217   0.3645   1.0000
  11.000   1.5973   0.03920   0.03046  -0.1204   0.3572   1.0000
  11.250   1.6005   0.04088   0.03228  -0.1184   0.3487   1.0000
  11.500   1.6132   0.04191   0.03328  -0.1171   0.3414   1.0000
  11.750   1.6146   0.04385   0.03537  -0.1152   0.3331   1.0000
  12.250   1.6261   0.04716   0.03883  -0.1122   0.3177   1.0000
  12.500   1.6359   0.04849   0.04016  -0.1110   0.3106   1.0000
  12.750   1.6355   0.05083   0.04265  -0.1095   0.3025   1.0000
  13.000   1.6424   0.05249   0.04434  -0.1083   0.2953   1.0000
  13.250   1.6427   0.05492   0.04690  -0.1070   0.2876   1.0000
  13.500   1.6469   0.05694   0.04897  -0.1059   0.2802   1.0000
  13.750   1.6474   0.05946   0.05160  -0.1048   0.2728   1.0000
  14.000   1.6490   0.06188   0.05410  -0.1039   0.2654   1.0000
  14.250   1.6504   0.06443   0.05673  -0.1031   0.2583   1.0000
  14.500   1.6492   0.06733   0.05975  -0.1023   0.2509   1.0000
  14.750   1.6516   0.06985   0.06231  -0.1017   0.2442   1.0000
  15.000   1.6473   0.07330   0.06591  -0.1012   0.2368   1.0000
  15.250   1.6510   0.07571   0.06833  -0.1007   0.2302   1.0000
  15.500   1.6438   0.07974   0.07255  -0.1006   0.2230   1.0000
  15.750   1.6480   0.08212   0.07493  -0.1003   0.2167   1.0000
  16.000   1.6390   0.08661   0.07961  -0.1005   0.2098   1.0000
  16.250   1.6390   0.08972   0.08276  -0.1005   0.2034   1.0000
  16.500   1.6340   0.09371   0.08689  -0.1009   0.1971   1.0000
  16.750   1.6295   0.09765   0.09094  -0.1014   0.1907   1.0000
  17.000   1.6293   0.10094   0.09427  -0.1018   0.1849   1.0000
  17.250   1.6205   0.10573   0.09923  -0.1028   0.1787   1.0000
  17.500   1.6247   0.10827   0.10175  -0.1031   0.1732   1.0000
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