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MH 112 Airfoil (mh112-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: MH 112 Airfoil (mh112-il)
Reynolds number: 500,000
Max Cl/Cd: 119.97 at α=3.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-mh112-il-500000.txt
Download as CSV file: xf-mh112-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000   0.2405   0.09474   0.09170  -0.1599   0.8974   0.0252
 -10.750   0.2293   0.08904   0.08596  -0.1641   0.8862   0.0269
 -10.500   0.2431   0.08659   0.08344  -0.1656   0.8783   0.0270
 -10.250   0.2593   0.08549   0.08232  -0.1650   0.8706   0.0274
 -10.000   0.2700   0.08344   0.08023  -0.1657   0.8628   0.0277
  -9.750   0.2800   0.08140   0.07814  -0.1665   0.8557   0.0282
  -9.500   0.2587   0.07518   0.07192  -0.1702   0.8461   0.0306
  -9.250   0.2708   0.07324   0.06992  -0.1704   0.8399   0.0308
  -9.000   0.2829   0.07215   0.06884  -0.1696   0.8337   0.0311
  -8.750   0.2915   0.07037   0.06705  -0.1697   0.8272   0.0314
  -8.500   0.3017   0.06860   0.06522  -0.1701   0.8211   0.0320
  -8.250   0.3062   0.06646   0.06310  -0.1703   0.8148   0.0328
  -8.000   0.1452   0.03745   0.03381  -0.1899   0.7997   0.0268
  -7.750   0.1476   0.03491   0.03127  -0.1909   0.7937   0.0273
  -7.500   0.1588   0.03328   0.02958  -0.1918   0.7881   0.0275
  -7.250   0.1778   0.03246   0.02871  -0.1923   0.7833   0.0280
  -7.000   0.2958   0.05158   0.04820  -0.1736   0.7835   0.0364
  -6.750   0.1770   0.01841   0.01259  -0.1972   0.7718   0.0199
  -6.500   0.2026   0.01740   0.01139  -0.1973   0.7675   0.0200
  -6.250   0.2299   0.01642   0.01023  -0.1977   0.7632   0.0201
  -6.000   0.2543   0.01550   0.00925  -0.1975   0.7588   0.0203
  -5.750   0.2802   0.01477   0.00850  -0.1974   0.7541   0.0206
  -5.500   0.3073   0.01423   0.00790  -0.1975   0.7498   0.0209
  -5.250   0.3360   0.01379   0.00737  -0.1978   0.7455   0.0215
  -5.000   0.3631   0.01337   0.00690  -0.1978   0.7411   0.0222
  -4.750   0.3903   0.01298   0.00647  -0.1977   0.7363   0.0231
  -4.500   0.4181   0.01249   0.00595  -0.1979   0.7319   0.0243
  -4.250   0.4473   0.01220   0.00559  -0.1982   0.7276   0.0259
  -4.000   0.4758   0.01187   0.00524  -0.1984   0.7231   0.0281
  -3.750   0.5033   0.01158   0.00494  -0.1984   0.7182   0.0315
  -3.500   0.5317   0.01130   0.00466  -0.1985   0.7135   0.0379
  -3.250   0.5611   0.01104   0.00440  -0.1989   0.7092   0.0511
  -3.000   0.5897   0.01084   0.00425  -0.1991   0.7046   0.0701
  -2.750   0.6171   0.01065   0.00414  -0.1991   0.6995   0.0897
  -2.500   0.6452   0.01049   0.00404  -0.1992   0.6946   0.1122
  -2.250   0.6744   0.01038   0.00395  -0.1995   0.6900   0.1390
  -2.000   0.7023   0.01026   0.00391  -0.1996   0.6852   0.1695
  -1.750   0.7296   0.01013   0.00388  -0.1995   0.6798   0.2041
  -1.250   0.7871   0.01000   0.00383  -0.2000   0.6699   0.2788
  -1.000   0.8135   0.00991   0.00386  -0.1997   0.6647   0.3146
  -0.750   0.8407   0.00986   0.00387  -0.1996   0.6592   0.3508
  -0.500   0.8688   0.00984   0.00388  -0.1996   0.6540   0.3891
  -0.250   0.8961   0.00983   0.00394  -0.1995   0.6487   0.4270
   0.000   0.9222   0.00982   0.00399  -0.1992   0.6426   0.4621
   0.250   0.9491   0.00984   0.00403  -0.1989   0.6365   0.4961
   0.500   0.9755   0.00989   0.00410  -0.1986   0.6304   0.5266
   0.750   1.0009   0.00990   0.00417  -0.1981   0.6239   0.5553
   1.000   1.0271   0.00997   0.00423  -0.1977   0.6178   0.5825
   1.250   1.0529   0.01003   0.00432  -0.1973   0.6120   0.6096
   1.500   1.0779   0.01006   0.00442  -0.1967   0.6058   0.6359
   1.750   1.1033   0.01015   0.00450  -0.1962   0.5998   0.6638
   2.000   1.1281   0.01022   0.00462  -0.1956   0.5941   0.6933
   2.250   1.1520   0.01026   0.00474  -0.1948   0.5879   0.7265
   2.500   1.1755   0.01033   0.00486  -0.1939   0.5819   0.7661
   2.750   1.1969   0.01035   0.00500  -0.1925   0.5761   0.8174
   3.000   1.2094   0.01017   0.00505  -0.1891   0.5701   0.9603
   3.250   1.2344   0.01034   0.00514  -0.1886   0.5640   1.0000
   3.500   1.2582   0.01052   0.00527  -0.1879   0.5581   1.0000
   3.750   1.2801   0.01067   0.00540  -0.1869   0.5516   1.0000
   4.000   1.3019   0.01088   0.00553  -0.1858   0.5454   1.0000
   4.250   1.3230   0.01107   0.00570  -0.1846   0.5393   1.0000
   4.500   1.3435   0.01126   0.00587  -0.1832   0.5327   1.0000
   4.750   1.3640   0.01153   0.00606  -0.1820   0.5265   1.0000
   5.000   1.3842   0.01172   0.00627  -0.1807   0.5202   1.0000
   5.250   1.4035   0.01197   0.00649  -0.1792   0.5133   1.0000
   5.500   1.4227   0.01227   0.00673  -0.1777   0.5068   1.0000
   5.750   1.4417   0.01251   0.00699  -0.1763   0.4999   1.0000
   6.000   1.4595   0.01283   0.00726  -0.1746   0.4930   1.0000
   6.250   1.4778   0.01315   0.00757  -0.1731   0.4862   1.0000
   6.500   1.4951   0.01348   0.00789  -0.1714   0.4787   1.0000
   6.750   1.5110   0.01390   0.00826  -0.1695   0.4715   1.0000
   7.000   1.5284   0.01424   0.00863  -0.1679   0.4641   1.0000
   7.250   1.5427   0.01474   0.00907  -0.1659   0.4562   1.0000
   7.500   1.5591   0.01515   0.00952  -0.1642   0.4485   1.0000
   7.750   1.5730   0.01569   0.01002  -0.1622   0.4403   1.0000
   8.000   1.5875   0.01623   0.01056  -0.1604   0.4322   1.0000
   8.250   1.6005   0.01685   0.01116  -0.1584   0.4235   1.0000
   8.500   1.6138   0.01749   0.01179  -0.1565   0.4150   1.0000
   8.750   1.6254   0.01822   0.01250  -0.1544   0.4059   1.0000
   9.000   1.6378   0.01895   0.01324  -0.1525   0.3969   1.0000
   9.250   1.6474   0.01985   0.01410  -0.1502   0.3874   1.0000
   9.500   1.6596   0.02066   0.01492  -0.1485   0.3782   1.0000
   9.750   1.6670   0.02176   0.01596  -0.1461   0.3689   1.0000
  10.000   1.6793   0.02263   0.01686  -0.1445   0.3597   1.0000
  10.250   1.6860   0.02385   0.01804  -0.1422   0.3509   1.0000
  10.500   1.6973   0.02485   0.01905  -0.1406   0.3420   1.0000
  10.750   1.7039   0.02617   0.02034  -0.1385   0.3338   1.0000
  11.000   1.7146   0.02728   0.02147  -0.1370   0.3255   1.0000
  11.250   1.7201   0.02876   0.02291  -0.1350   0.3177   1.0000
  11.500   1.7314   0.02989   0.02408  -0.1336   0.3103   1.0000
  11.750   1.7364   0.03150   0.02566  -0.1318   0.3029   1.0000
  12.000   1.7472   0.03273   0.02694  -0.1305   0.2961   1.0000
  12.250   1.7539   0.03431   0.02851  -0.1289   0.2892   1.0000
  12.500   1.7614   0.03585   0.03007  -0.1275   0.2827   1.0000
  12.750   1.7698   0.03737   0.03162  -0.1263   0.2760   1.0000
  13.000   1.7736   0.03930   0.03352  -0.1247   0.2695   1.0000
  13.250   1.7838   0.04075   0.03504  -0.1237   0.2636   1.0000
  13.500   1.7895   0.04261   0.03690  -0.1225   0.2570   1.0000
  13.750   1.7947   0.04454   0.03885  -0.1213   0.2512   1.0000
  14.000   1.8030   0.04624   0.04061  -0.1204   0.2450   1.0000
  14.250   1.8048   0.04860   0.04295  -0.1191   0.2387   1.0000
  14.500   1.8131   0.05036   0.04478  -0.1183   0.2332   1.0000
  14.750   1.8170   0.05262   0.04706  -0.1174   0.2269   1.0000
  15.000   1.8195   0.05502   0.04947  -0.1165   0.2211   1.0000
  15.250   1.8257   0.05712   0.05164  -0.1158   0.2153   1.0000
  15.500   1.8264   0.05982   0.05433  -0.1150   0.2093   1.0000
  15.750   1.8310   0.06216   0.05673  -0.1144   0.2038   1.0000
  16.000   1.8332   0.06479   0.05940  -0.1139   0.1977   1.0000
  16.250   1.8329   0.06776   0.06238  -0.1133   0.1922   1.0000
  16.500   1.8371   0.07024   0.06493  -0.1129   0.1867   1.0000
  16.750   1.8357   0.07343   0.06813  -0.1125   0.1812   1.0000
  17.000   1.8377   0.07626   0.07102  -0.1123   0.1763   1.0000
  17.250   1.8388   0.07922   0.07403  -0.1121   0.1709   1.0000
  17.500   1.8343   0.08293   0.07774  -0.1120   0.1657   1.0000
  17.750   1.8386   0.08554   0.08045  -0.1120   0.1610   1.0000
  18.000   1.8357   0.08914   0.08407  -0.1120   0.1561   1.0000
  18.250   1.8342   0.09256   0.08753  -0.1122   0.1515   1.0000
  18.500   1.8347   0.09577   0.09082  -0.1124   0.1469   1.0000
  18.750   1.8303   0.09966   0.09472  -0.1128   0.1423   1.0000
  19.000   1.8300   0.10299   0.09812  -0.1132   0.1382   1.0000
  19.250   1.8288   0.10645   0.10165  -0.1137   0.1339   1.0000
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