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MH 115 11.06% (mh115-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: MH 115 11.06% (mh115-il)
Reynolds number: 200,000
Max Cl/Cd: 91.54 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-mh115-il-200000.txt
Download as CSV file: xf-mh115-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 115  11.06%                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.2204   0.10544   0.10220  -0.0518   0.9847   0.0368
  -8.250  -0.2136   0.10156   0.09835  -0.0608   0.9769   0.0378
  -8.000  -0.1985   0.09703   0.09382  -0.0697   0.9723   0.0380
  -7.750  -0.1780   0.09277   0.08956  -0.0666   0.9700   0.0391
  -7.500  -0.1607   0.08964   0.08643  -0.0686   0.9644   0.0402
  -7.250  -0.1402   0.08588   0.08266  -0.0733   0.9607   0.0418
  -7.000  -0.1301   0.08262   0.07941  -0.0766   0.9522   0.0432
  -6.750  -0.1194   0.07721   0.07403  -0.0901   0.9395   0.0460
  -6.500  -0.0979   0.07056   0.06737  -0.0997   0.9341   0.0468
  -6.250  -0.0749   0.06811   0.06491  -0.0984   0.9326   0.0483
  -6.000  -0.0613   0.06528   0.06208  -0.1004   0.9236   0.0498
  -5.750  -0.0277   0.05965   0.05639  -0.1113   0.9195   0.0534
  -5.250   0.0452   0.03376   0.02928  -0.1437   0.9053   0.0321
  -5.000   0.0927   0.02551   0.01977  -0.1509   0.9035   0.0249
  -4.750   0.1250   0.02278   0.01646  -0.1525   0.8979   0.0251
  -4.500   0.1585   0.02092   0.01441  -0.1542   0.8929   0.0274
  -4.250   0.1983   0.01939   0.01255  -0.1565   0.8901   0.0320
  -4.000   0.2389   0.01795   0.01096  -0.1588   0.8878   0.0368
  -3.750   0.2648   0.01720   0.01015  -0.1584   0.8798   0.0455
  -3.500   0.3008   0.01603   0.00899  -0.1600   0.8756   0.0604
  -3.250   0.3395   0.01529   0.00817  -0.1619   0.8724   0.0801
  -3.000   0.3652   0.01468   0.00766  -0.1616   0.8640   0.1003
  -2.750   0.4004   0.01400   0.00702  -0.1630   0.8592   0.1392
  -2.500   0.4316   0.01347   0.00668  -0.1637   0.8530   0.1933
  -2.250   0.4615   0.01307   0.00646  -0.1642   0.8459   0.2598
  -2.000   0.4968   0.01261   0.00618  -0.1656   0.8414   0.3418
  -1.750   0.5213   0.01243   0.00620  -0.1650   0.8323   0.4162
  -1.500   0.5539   0.01208   0.00603  -0.1657   0.8269   0.5030
  -1.250   0.5783   0.01195   0.00609  -0.1649   0.8182   0.5798
  -1.000   0.6076   0.01170   0.00598  -0.1647   0.8121   0.6608
  -0.750   0.6292   0.01160   0.00604  -0.1630   0.8035   0.7342
  -0.500   0.6522   0.01137   0.00592  -0.1612   0.7969   0.8123
  -0.250   0.6661   0.01118   0.00585  -0.1575   0.7882   0.9102
   0.000   0.7020   0.01105   0.00558  -0.1589   0.7815   1.0000
   0.250   0.7295   0.01118   0.00559  -0.1589   0.7727   1.0000
   0.500   0.7615   0.01121   0.00546  -0.1595   0.7658   1.0000
   0.750   0.7878   0.01134   0.00551  -0.1593   0.7566   1.0000
   1.000   0.8195   0.01139   0.00541  -0.1599   0.7497   1.0000
   1.250   0.8449   0.01153   0.00551  -0.1594   0.7400   1.0000
   1.500   0.8746   0.01162   0.00548  -0.1596   0.7324   1.0000
   1.750   0.9012   0.01174   0.00555  -0.1593   0.7229   1.0000
   2.000   0.9288   0.01186   0.00560  -0.1592   0.7142   1.0000
   2.250   0.9570   0.01196   0.00562  -0.1591   0.7054   1.0000
   2.500   0.9829   0.01210   0.00574  -0.1587   0.6955   1.0000
   2.750   1.0116   0.01221   0.00577  -0.1587   0.6870   1.0000
   3.000   1.0369   0.01235   0.00589  -0.1582   0.6764   1.0000
   3.250   1.0631   0.01250   0.00600  -0.1578   0.6664   1.0000
   3.500   1.0912   0.01262   0.00604  -0.1577   0.6570   1.0000
   3.750   1.1154   0.01277   0.00623  -0.1570   0.6455   1.0000
   4.000   1.1407   0.01294   0.00637  -0.1564   0.6344   1.0000
   4.250   1.1667   0.01309   0.00649  -0.1560   0.6235   1.0000
   4.500   1.1923   0.01326   0.00663  -0.1555   0.6120   1.0000
   4.750   1.2159   0.01344   0.00683  -0.1546   0.5992   1.0000
   5.000   1.2398   0.01364   0.00702  -0.1538   0.5862   1.0000
   5.250   1.2636   0.01385   0.00723  -0.1530   0.5730   1.0000
   5.500   1.2870   0.01407   0.00744  -0.1521   0.5592   1.0000
   5.750   1.3099   0.01431   0.00767  -0.1512   0.5449   1.0000
   6.000   1.3321   0.01458   0.00793  -0.1501   0.5297   1.0000
   6.250   1.3536   0.01487   0.00822  -0.1489   0.5139   1.0000
   6.500   1.3743   0.01518   0.00852  -0.1476   0.4973   1.0000
   6.750   1.3944   0.01553   0.00885  -0.1462   0.4802   1.0000
   7.000   1.4136   0.01592   0.00922  -0.1446   0.4628   1.0000
   7.250   1.4321   0.01635   0.00961  -0.1430   0.4453   1.0000
   7.500   1.4495   0.01683   0.01004  -0.1412   0.4277   1.0000
   7.750   1.4663   0.01731   0.01053  -0.1393   0.4101   1.0000
   8.000   1.4820   0.01784   0.01106  -0.1373   0.3926   1.0000
   8.250   1.4964   0.01841   0.01162  -0.1350   0.3755   1.0000
   8.500   1.5086   0.01900   0.01220  -0.1324   0.3589   1.0000
   8.750   1.5200   0.01965   0.01283  -0.1297   0.3426   1.0000
   9.000   1.5307   0.02035   0.01354  -0.1270   0.3266   1.0000
   9.250   1.5407   0.02111   0.01429  -0.1243   0.3109   1.0000
   9.500   1.5501   0.02194   0.01511  -0.1215   0.2955   1.0000
   9.750   1.5585   0.02284   0.01602  -0.1188   0.2802   1.0000
  10.000   1.5663   0.02382   0.01700  -0.1161   0.2652   1.0000
  10.250   1.5733   0.02489   0.01809  -0.1134   0.2504   1.0000
  10.500   1.5796   0.02606   0.01928  -0.1108   0.2358   1.0000
  10.750   1.5850   0.02734   0.02057  -0.1082   0.2214   1.0000
  11.000   1.5898   0.02874   0.02198  -0.1057   0.2074   1.0000
  11.250   1.5938   0.03026   0.02351  -0.1033   0.1936   1.0000
  11.500   1.5972   0.03189   0.02516  -0.1011   0.1802   1.0000
  11.750   1.6002   0.03365   0.02694  -0.0990   0.1676   1.0000
  12.000   1.6025   0.03554   0.02887  -0.0970   0.1558   1.0000
  12.250   1.6035   0.03763   0.03095  -0.0951   0.1452   1.0000
  12.500   1.6046   0.03979   0.03314  -0.0934   0.1350   1.0000
  12.750   1.6077   0.04189   0.03532  -0.0920   0.1252   1.0000
  13.000   1.6083   0.04429   0.03777  -0.0906   0.1169   1.0000
  13.250   1.6075   0.04691   0.04042  -0.0893   0.1090   1.0000
  13.500   1.6096   0.04936   0.04300  -0.0883   0.1010   1.0000
  13.750   1.6061   0.05248   0.04611  -0.0874   0.0943   1.0000
  14.000   1.6069   0.05526   0.04905  -0.0867   0.0865   1.0000
  14.250   1.6041   0.05856   0.05243  -0.0862   0.0796   1.0000
  14.500   1.5988   0.06228   0.05618  -0.0859   0.0728   1.0000
  14.750   1.5959   0.06587   0.05991  -0.0858   0.0650   1.0000
  15.000   1.5879   0.07025   0.06433  -0.0860   0.0585   1.0000
  15.250   1.5792   0.07490   0.06903  -0.0864   0.0522   1.0000
  15.500   1.5719   0.07953   0.07378  -0.0870   0.0458   1.0000
  15.750   1.5593   0.08504   0.07931  -0.0880   0.0416   1.0000
  16.000   1.5523   0.08995   0.08436  -0.0892   0.0369   1.0000
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