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MH 92 15.49% (mh92-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: MH 92 15.49% (mh92-il)
Reynolds number: 100,000
Max Cl/Cd: 39.98 at α=7.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-mh92-il-100000-n5.txt
Download as CSV file: xf-mh92-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 92  15.49%                                   
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -13.000  -0.6826   0.09644   0.09127  -0.0050   1.0000   0.0232
 -12.750  -0.7488   0.07978   0.07421  -0.0173   1.0000   0.0224
 -12.500  -0.7990   0.06983   0.06377  -0.0233   1.0000   0.0219
 -12.250  -0.8231   0.06445   0.05810  -0.0250   1.0000   0.0218
 -11.750  -0.8515   0.05683   0.04998  -0.0249   1.0000   0.0218
 -11.500  -0.8588   0.05381   0.04676  -0.0239   1.0000   0.0218
 -11.250  -0.8631   0.05104   0.04378  -0.0226   1.0000   0.0219
 -11.000  -0.8642   0.04856   0.04111  -0.0210   1.0000   0.0220
 -10.750  -0.8619   0.04630   0.03868  -0.0193   1.0000   0.0222
 -10.500  -0.8570   0.04415   0.03637  -0.0176   1.0000   0.0224
 -10.250  -0.8492   0.04217   0.03422  -0.0160   1.0000   0.0227
 -10.000  -0.8390   0.04020   0.03207  -0.0144   1.0000   0.0230
  -9.750  -0.8258   0.03832   0.03002  -0.0131   1.0000   0.0234
  -9.500  -0.8095   0.03650   0.02802  -0.0121   1.0000   0.0238
  -9.250  -0.7910   0.03475   0.02610  -0.0112   1.0000   0.0244
  -9.000  -0.7707   0.03308   0.02424  -0.0104   1.0000   0.0251
  -8.750  -0.7507   0.03162   0.02273  -0.0097   1.0000   0.0259
  -8.500  -0.7325   0.03047   0.02161  -0.0089   1.0000   0.0271
  -8.250  -0.7129   0.02935   0.02043  -0.0081   1.0000   0.0285
  -8.000  -0.6937   0.02819   0.01922  -0.0073   1.0000   0.0301
  -7.750  -0.6762   0.02716   0.01824  -0.0063   1.0000   0.0317
  -7.500  -0.6541   0.02610   0.01712  -0.0061   0.9729   0.0336
  -7.250  -0.6245   0.02495   0.01593  -0.0073   0.9389   0.0358
  -7.000  -0.6007   0.02406   0.01494  -0.0070   0.9124   0.0402
  -6.750  -0.5830   0.02330   0.01412  -0.0055   0.8889   0.0442
  -6.500  -0.5674   0.02255   0.01331  -0.0034   0.8685   0.0493
  -6.250  -0.5520   0.02181   0.01253  -0.0012   0.8505   0.0581
  -6.000  -0.5368   0.02099   0.01175   0.0010   0.8339   0.0726
  -5.750  -0.5220   0.02005   0.01100   0.0032   0.8185   0.1039
  -5.500  -0.5089   0.01896   0.01031   0.0055   0.8041   0.1716
  -5.000  -0.4806   0.01726   0.00942   0.0099   0.7764   0.3407
  -4.750  -0.4638   0.01671   0.00914   0.0121   0.7629   0.4089
  -4.500  -0.4456   0.01629   0.00894   0.0142   0.7505   0.4700
  -4.250  -0.4257   0.01599   0.00879   0.0162   0.7380   0.5248
  -4.000  -0.4039   0.01579   0.00871   0.0179   0.7248   0.5739
  -3.750  -0.3799   0.01569   0.00868   0.0194   0.7127   0.6135
  -3.500  -0.3549   0.01566   0.00860   0.0207   0.7007   0.6448
  -3.250  -0.3278   0.01569   0.00861   0.0215   0.6875   0.6705
  -3.000  -0.3018   0.01573   0.00857   0.0225   0.6755   0.6945
  -2.750  -0.2750   0.01582   0.00854   0.0235   0.6638   0.7155
  -2.500  -0.2472   0.01593   0.00857   0.0241   0.6506   0.7342
  -2.250  -0.2202   0.01602   0.00855   0.0249   0.6387   0.7511
  -2.000  -0.1942   0.01611   0.00848   0.0258   0.6272   0.7669
  -1.750  -0.1647   0.01626   0.00854   0.0261   0.6142   0.7795
  -1.500  -0.1362   0.01640   0.00855   0.0266   0.6023   0.7915
  -1.250  -0.1101   0.01648   0.00850   0.0274   0.5911   0.8044
  -1.000  -0.0811   0.01663   0.00855   0.0276   0.5784   0.8152
  -0.750  -0.0521   0.01677   0.00857   0.0279   0.5667   0.8251
  -0.500  -0.0282   0.01684   0.00851   0.0290   0.5558   0.8376
  -0.250   0.0062   0.01704   0.00863   0.0283   0.5430   0.8445
   0.000   0.0304   0.01713   0.00860   0.0292   0.5323   0.8562
   0.250   0.0655   0.01732   0.00868   0.0283   0.5203   0.8626
   0.500   0.0897   0.01741   0.00870   0.0292   0.5090   0.8739
   0.750   0.1262   0.01759   0.00876   0.0279   0.4977   0.8793
   1.000   0.1550   0.01771   0.00879   0.0279   0.4863   0.8879
   1.250   0.1863   0.01783   0.00884   0.0274   0.4752   0.8947
   1.500   0.2203   0.01796   0.00884   0.0263   0.4647   0.9005
   1.750   0.2446   0.01804   0.00890   0.0269   0.4538   0.9095
   2.000   0.2820   0.01818   0.00895   0.0251   0.4432   0.9135
   2.250   0.3155   0.01830   0.00899   0.0240   0.4327   0.9192
   2.500   0.3419   0.01842   0.00907   0.0242   0.4230   0.9268
   2.750   0.3795   0.01854   0.00908   0.0222   0.4133   0.9305
   3.000   0.4129   0.01868   0.00923   0.0209   0.4029   0.9359
   3.250   0.4402   0.01882   0.00927   0.0208   0.3949   0.9427
   3.500   0.4771   0.01896   0.00942   0.0188   0.3845   0.9466
   3.750   0.5096   0.01913   0.00952   0.0177   0.3763   0.9519
   4.000   0.5390   0.01930   0.00970   0.0170   0.3674   0.9578
   4.250   0.5745   0.01946   0.00981   0.0152   0.3595   0.9618
   4.500   0.6062   0.01965   0.01004   0.0141   0.3507   0.9671
   4.750   0.6374   0.01985   0.01016   0.0131   0.3439   0.9719
   5.000   0.6715   0.02006   0.01044   0.0114   0.3353   0.9761
   5.250   0.7022   0.02028   0.01061   0.0104   0.3286   0.9811
   5.500   0.7349   0.02053   0.01093   0.0089   0.3207   0.9851
   5.750   0.7675   0.02077   0.01117   0.0075   0.3138   0.9893
   6.000   0.7985   0.02107   0.01150   0.0063   0.3072   0.9937
   6.250   0.8309   0.02135   0.01183   0.0048   0.2999   0.9976
   6.500   0.8575   0.02165   0.01207   0.0045   0.2946   1.0000
   6.750   0.8750   0.02204   0.01259   0.0058   0.2885   1.0000
   7.000   0.8922   0.02240   0.01298   0.0072   0.2831   1.0000
   7.250   0.9095   0.02275   0.01329   0.0086   0.2786   1.0000
   7.500   0.9250   0.02320   0.01387   0.0102   0.2729   1.0000
   7.750   0.9405   0.02361   0.01434   0.0119   0.2678   1.0000
   8.000   0.9563   0.02400   0.01471   0.0136   0.2634   1.0000
   8.250   0.9700   0.02450   0.01530   0.0154   0.2585   1.0000
   8.500   0.9831   0.02498   0.01588   0.0174   0.2532   1.0000
   8.750   0.9968   0.02541   0.01631   0.0194   0.2489   1.0000
   9.000   1.0100   0.02590   0.01683   0.0214   0.2447   1.0000
   9.250   1.0202   0.02649   0.01756   0.0237   0.2395   1.0000
   9.500   1.0321   0.02698   0.01809   0.0258   0.2348   1.0000
   9.750   1.0464   0.02743   0.01848   0.0276   0.2309   1.0000
  10.000   1.0540   0.02816   0.01939   0.0300   0.2259   1.0000
  10.250   1.0640   0.02879   0.02009   0.0321   0.2211   1.0000
  10.500   1.0768   0.02931   0.02060   0.0338   0.2170   1.0000
  10.750   1.0856   0.03010   0.02149   0.0358   0.2126   1.0000
  11.000   1.0923   0.03096   0.02249   0.0378   0.2078   1.0000
  11.250   1.1001   0.03167   0.02323   0.0399   0.2038   1.0000
  11.500   1.1096   0.03238   0.02391   0.0416   0.2001   1.0000
  11.750   1.1080   0.03372   0.02545   0.0437   0.1959   1.0000
  12.000   1.1112   0.03496   0.02679   0.0451   0.1917   1.0000
  12.250   1.1193   0.03598   0.02783   0.0462   0.1879   1.0000
  12.500   1.1227   0.03746   0.02939   0.0471   0.1841   1.0000
  12.750   1.1191   0.03957   0.03168   0.0477   0.1799   1.0000
  13.000   1.1211   0.04134   0.03352   0.0481   0.1760   1.0000
  13.250   1.1311   0.04250   0.03466   0.0485   0.1724   1.0000
  13.500   1.1215   0.04557   0.03794   0.0483   0.1687   1.0000
  13.750   1.1120   0.04882   0.04135   0.0478   0.1647   1.0000
  14.000   1.1128   0.05110   0.04368   0.0474   0.1610   1.0000
  14.250   1.1199   0.05276   0.04533   0.0473   0.1577   1.0000
  14.500   1.0918   0.05869   0.05152   0.0451   0.1542   1.0000
  14.750   1.0703   0.06419   0.05719   0.0428   0.1506   1.0000
  15.000   1.0729   0.06664   0.05966   0.0420   0.1471   1.0000
  15.250   1.0699   0.06994   0.06300   0.0408   0.1439   1.0000
  15.500   0.9006   0.10071   0.09414   0.0247   0.1352   1.0000
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