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MH 113 14.62% (mh113-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: MH 113 14.62% (mh113-il)
Reynolds number: 200,000
Max Cl/Cd: 83.63 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-mh113-il-200000-n5.txt
Download as CSV file: xf-mh113-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750   0.0516   0.10641   0.10238  -0.1147   0.9275   0.0333
 -10.500   0.0571   0.10227   0.09822  -0.1204   0.9215   0.0357
 -10.250   0.0695   0.09778   0.09371  -0.1260   0.9173   0.0358
  -9.750   0.0978   0.08828   0.08415  -0.1320   0.9070   0.0270
  -9.250   0.1203   0.07850   0.07428  -0.1403   0.8951   0.0229
  -9.000   0.1336   0.07597   0.07173  -0.1423   0.8875   0.0227
  -8.750   0.1474   0.07246   0.06817  -0.1458   0.8814   0.0224
  -8.500   0.1498   0.06920   0.06491  -0.1472   0.8720   0.0223
  -8.250   0.1557   0.06532   0.06098  -0.1501   0.8649   0.0221
  -8.000   0.1510   0.06166   0.05735  -0.1511   0.8552   0.0219
  -7.750   0.1448   0.05676   0.05240  -0.1538   0.8472   0.0217
  -7.500   0.0387   0.03065   0.02530  -0.1772   0.8268   0.0202
  -7.250   0.0534   0.02811   0.02241  -0.1785   0.8201   0.0204
  -7.000   0.0766   0.02616   0.02013  -0.1800   0.8153   0.0209
  -6.750   0.1005   0.02453   0.01818  -0.1811   0.8106   0.0216
  -6.500   0.1225   0.02296   0.01625  -0.1813   0.8046   0.0224
  -6.250   0.1490   0.02153   0.01442  -0.1820   0.7998   0.0229
  -6.000   0.1781   0.02045   0.01320  -0.1829   0.7961   0.0234
  -5.750   0.2016   0.01971   0.01237  -0.1826   0.7903   0.0238
  -5.500   0.2279   0.01897   0.01152  -0.1826   0.7850   0.0244
  -5.250   0.2569   0.01823   0.01064  -0.1831   0.7808   0.0252
  -5.000   0.2845   0.01760   0.00988  -0.1833   0.7760   0.0260
  -4.750   0.3103   0.01706   0.00924  -0.1831   0.7704   0.0269
  -4.500   0.3386   0.01657   0.00871  -0.1834   0.7655   0.0280
  -4.000   0.3945   0.01581   0.00784  -0.1838   0.7555   0.0324
  -3.750   0.4224   0.01546   0.00742  -0.1839   0.7501   0.0349
  -3.500   0.4529   0.01508   0.00696  -0.1845   0.7457   0.0385
  -3.250   0.4801   0.01478   0.00665  -0.1845   0.7400   0.0441
  -3.000   0.5076   0.01450   0.00638  -0.1845   0.7343   0.0554
  -2.750   0.5375   0.01421   0.00610  -0.1850   0.7294   0.0738
  -2.500   0.5653   0.01401   0.00594  -0.1851   0.7239   0.0961
  -2.250   0.5922   0.01381   0.00585  -0.1851   0.7177   0.1283
  -2.000   0.6216   0.01360   0.00571  -0.1855   0.7125   0.1701
  -1.750   0.6493   0.01347   0.00565  -0.1856   0.7068   0.2075
  -1.500   0.6761   0.01336   0.00562  -0.1855   0.7004   0.2444
  -1.250   0.7053   0.01324   0.00554  -0.1858   0.6950   0.2843
  -1.000   0.7319   0.01317   0.00556  -0.1856   0.6886   0.3255
  -0.750   0.7590   0.01311   0.00557  -0.1855   0.6820   0.3689
  -0.250   0.8129   0.01305   0.00563  -0.1851   0.6693   0.4543
   0.000   0.8401   0.01303   0.00566  -0.1849   0.6628   0.4954
   0.250   0.8665   0.01303   0.00572  -0.1846   0.6563   0.5353
   0.500   0.8917   0.01305   0.00580  -0.1840   0.6491   0.5738
   0.750   0.9185   0.01306   0.00582  -0.1837   0.6428   0.6125
   1.000   0.9420   0.01311   0.00596  -0.1827   0.6350   0.6497
   1.250   0.9671   0.01314   0.00601  -0.1821   0.6280   0.6885
   1.500   0.9898   0.01318   0.00612  -0.1809   0.6206   0.7286
   1.750   1.0118   0.01320   0.00620  -0.1796   0.6131   0.7736
   2.000   1.0312   0.01320   0.00626  -0.1776   0.6058   0.8295
   2.250   1.0481   0.01305   0.00622  -0.1750   0.5980   1.0000
   2.500   1.0743   0.01324   0.00629  -0.1748   0.5905   1.0000
   2.750   1.0987   0.01343   0.00643  -0.1742   0.5819   1.0000
   3.000   1.1240   0.01363   0.00653  -0.1738   0.5743   1.0000
   3.250   1.1474   0.01385   0.00670  -0.1731   0.5655   1.0000
   3.500   1.1717   0.01407   0.00683  -0.1725   0.5577   1.0000
   3.750   1.1941   0.01431   0.00703  -0.1716   0.5488   1.0000
   4.000   1.2171   0.01456   0.00720  -0.1708   0.5406   1.0000
   4.250   1.2385   0.01481   0.00743  -0.1697   0.5317   1.0000
   4.500   1.2597   0.01508   0.00763  -0.1685   0.5235   1.0000
   4.750   1.2792   0.01536   0.00789  -0.1671   0.5144   1.0000
   5.000   1.2991   0.01567   0.00814  -0.1658   0.5062   1.0000
   5.250   1.3180   0.01599   0.00843  -0.1643   0.4972   1.0000
   5.500   1.3370   0.01634   0.00873  -0.1628   0.4888   1.0000
   5.750   1.3552   0.01670   0.00908  -0.1612   0.4799   1.0000
   6.000   1.3734   0.01708   0.00942  -0.1597   0.4715   1.0000
   6.250   1.3905   0.01749   0.00981  -0.1580   0.4625   1.0000
   6.500   1.4079   0.01792   0.01022  -0.1564   0.4542   1.0000
   6.750   1.4241   0.01838   0.01067  -0.1547   0.4453   1.0000
   7.000   1.4405   0.01887   0.01114  -0.1530   0.4369   1.0000
   7.250   1.4559   0.01939   0.01164  -0.1512   0.4282   1.0000
   7.500   1.4714   0.01993   0.01218  -0.1495   0.4199   1.0000
   7.750   1.4860   0.02053   0.01277  -0.1476   0.4114   1.0000
   8.000   1.5007   0.02113   0.01338  -0.1459   0.4032   1.0000
   8.250   1.5143   0.02180   0.01404  -0.1441   0.3948   1.0000
   8.500   1.5283   0.02249   0.01475  -0.1423   0.3869   1.0000
   8.750   1.5410   0.02324   0.01550  -0.1404   0.3784   1.0000
   9.000   1.5540   0.02401   0.01628  -0.1387   0.3706   1.0000
   9.250   1.5660   0.02485   0.01713  -0.1369   0.3623   1.0000
   9.500   1.5782   0.02571   0.01802  -0.1351   0.3547   1.0000
   9.750   1.5897   0.02664   0.01897  -0.1334   0.3466   1.0000
  10.000   1.6006   0.02762   0.01996  -0.1316   0.3391   1.0000
  10.250   1.6116   0.02863   0.02101  -0.1299   0.3311   1.0000
  10.500   1.6214   0.02974   0.02214  -0.1282   0.3238   1.0000
  10.750   1.6315   0.03087   0.02332  -0.1266   0.3157   1.0000
  11.000   1.6401   0.03212   0.02456  -0.1248   0.3087   1.0000
  11.250   1.6497   0.03334   0.02586  -0.1233   0.3007   1.0000
  11.500   1.6568   0.03477   0.02729  -0.1216   0.2936   1.0000
  11.750   1.6661   0.03609   0.02869  -0.1202   0.2858   1.0000
  12.000   1.6718   0.03771   0.03031  -0.1186   0.2785   1.0000
  12.250   1.6805   0.03917   0.03185  -0.1173   0.2710   1.0000
  12.500   1.6856   0.04094   0.03364  -0.1158   0.2637   1.0000
  12.750   1.6927   0.04260   0.03538  -0.1146   0.2563   1.0000
  13.000   1.6973   0.04452   0.03733  -0.1132   0.2490   1.0000
  13.250   1.7029   0.04641   0.03928  -0.1121   0.2419   1.0000
  13.500   1.7067   0.04852   0.04143  -0.1109   0.2344   1.0000
  13.750   1.7111   0.05063   0.04361  -0.1099   0.2275   1.0000
  14.000   1.7140   0.05294   0.04597  -0.1089   0.2201   1.0000
  14.250   1.7169   0.05531   0.04839  -0.1080   0.2135   1.0000
  14.500   1.7196   0.05777   0.05092  -0.1072   0.2063   1.0000
  14.750   1.7203   0.06050   0.05369  -0.1064   0.1999   1.0000
  15.000   1.7229   0.06308   0.05636  -0.1058   0.1929   1.0000
  15.250   1.7214   0.06618   0.05948  -0.1052   0.1867   1.0000
  15.500   1.7237   0.06893   0.06234  -0.1049   0.1800   1.0000
  15.750   1.7215   0.07225   0.06570  -0.1045   0.1739   1.0000
  16.000   1.7225   0.07526   0.06880  -0.1043   0.1678   1.0000
  16.250   1.7204   0.07871   0.07231  -0.1042   0.1617   1.0000
  16.500   1.7187   0.08216   0.07583  -0.1042   0.1563   1.0000
  16.750   1.7175   0.08561   0.07937  -0.1044   0.1505   1.0000
  17.250   1.7126   0.09298   0.08690  -0.1050   0.1401   1.0000
  17.500   1.7086   0.09695   0.09094  -0.1055   0.1350   1.0000
  17.750   1.7052   0.10086   0.09492  -0.1061   0.1304   1.0000
  18.000   1.7031   0.10464   0.09880  -0.1068   0.1254   1.0000
  18.250   1.6977   0.10894   0.10316  -0.1078   0.1210   1.0000
  18.500   1.6954   0.11278   0.10711  -0.1087   0.1167   1.0000
  18.750   1.6924   0.11677   0.11118  -0.1098   0.1122   1.0000
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