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MH 200 12.97% (mh200-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: MH 200 12.97% (mh200-il)
Reynolds number: 100,000
Max Cl/Cd: 50.96 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-mh200-il-100000-n5.txt
Download as CSV file: xf-mh200-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 200  12.97%                                  
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.4242   0.09524   0.09023  -0.0529   1.0000   0.0188
 -10.500  -0.4355   0.08860   0.08367  -0.0557   1.0000   0.0182
 -10.000  -0.5025   0.06764   0.06256  -0.0684   1.0000   0.0164
  -9.750  -0.5246   0.06437   0.05926  -0.0678   1.0000   0.0163
  -9.500  -0.5480   0.06229   0.05721  -0.0651   1.0000   0.0163
  -9.250  -0.5780   0.06136   0.05631  -0.0600   1.0000   0.0163
  -9.000  -0.5821   0.05709   0.05180  -0.0628   0.9893   0.0161
  -8.750  -0.5795   0.05250   0.04687  -0.0652   0.9788   0.0160
  -8.500  -0.5714   0.04839   0.04234  -0.0671   0.9705   0.0160
  -8.250  -0.5632   0.04483   0.03838  -0.0674   0.9612   0.0159
  -8.000  -0.5474   0.04121   0.03428  -0.0684   0.9553   0.0159
  -7.750  -0.5326   0.03834   0.03099  -0.0681   0.9479   0.0159
  -7.500  -0.5093   0.03541   0.02758  -0.0689   0.9439   0.0160
  -7.250  -0.4883   0.03315   0.02493  -0.0686   0.9381   0.0162
  -7.000  -0.4633   0.03095   0.02241  -0.0688   0.9335   0.0165
  -6.750  -0.4352   0.02890   0.02020  -0.0698   0.9303   0.0173
  -6.500  -0.4094   0.02763   0.01878  -0.0702   0.9261   0.0190
  -6.250  -0.3863   0.02652   0.01750  -0.0697   0.9208   0.0210
  -6.000  -0.3582   0.02529   0.01609  -0.0700   0.9173   0.0225
  -5.750  -0.3310   0.02376   0.01451  -0.0705   0.9144   0.0243
  -5.500  -0.3131   0.02290   0.01357  -0.0692   0.9078   0.0266
  -5.250  -0.2879   0.02204   0.01257  -0.0691   0.9036   0.0319
  -5.000  -0.2606   0.02100   0.01144  -0.0695   0.9006   0.0419
  -4.750  -0.2427   0.01993   0.01060  -0.0683   0.8950   0.0745
  -4.500  -0.2251   0.01848   0.00998  -0.0676   0.8901   0.2155
  -4.250  -0.2045   0.01716   0.00959  -0.0673   0.8867   0.3955
  -4.000  -0.1878   0.01663   0.00974  -0.0650   0.8821   0.5402
  -3.750  -0.1686   0.01679   0.01010  -0.0625   0.8771   0.6184
  -3.500  -0.1419   0.01700   0.01024  -0.0616   0.8737   0.6635
  -3.250  -0.1123   0.01717   0.01025  -0.0615   0.8711   0.6955
  -3.000  -0.0936   0.01745   0.01041  -0.0595   0.8654   0.7173
  -2.750  -0.0691   0.01766   0.01047  -0.0585   0.8611   0.7361
  -2.500  -0.0408   0.01780   0.01047  -0.0582   0.8581   0.7527
  -2.250  -0.0144   0.01795   0.01050  -0.0575   0.8547   0.7667
  -2.000   0.0032   0.01817   0.01065  -0.0554   0.8487   0.7791
  -1.750   0.0295   0.01827   0.01063  -0.0548   0.8451   0.7912
  -1.500   0.0587   0.01832   0.01057  -0.0547   0.8423   0.8032
  -1.250   0.0752   0.01852   0.01071  -0.0526   0.8361   0.8151
  -1.000   0.0989   0.01861   0.01075  -0.0514   0.8317   0.8241
  -0.750   0.1281   0.01859   0.01064  -0.0515   0.8286   0.8330
  -0.500   0.1484   0.01870   0.01070  -0.0501   0.8231   0.8416
  -0.250   0.1711   0.01875   0.01072  -0.0491   0.8179   0.8489
   0.000   0.2009   0.01869   0.01059  -0.0494   0.8145   0.8562
   0.250   0.2228   0.01876   0.01063  -0.0483   0.8089   0.8631
   0.500   0.2457   0.01879   0.01064  -0.0474   0.8031   0.8707
   0.750   0.2771   0.01868   0.01050  -0.0479   0.7996   0.8765
   1.000   0.2961   0.01877   0.01059  -0.0464   0.7923   0.8840
   1.250   0.3244   0.01868   0.01050  -0.0464   0.7871   0.8900
   1.500   0.3595   0.01850   0.01030  -0.0476   0.7837   0.8948
   1.750   0.3749   0.01862   0.01046  -0.0455   0.7744   0.9025
   2.000   0.4098   0.01840   0.01025  -0.0466   0.7701   0.9067
   2.250   0.4286   0.01847   0.01036  -0.0451   0.7611   0.9139
   2.500   0.4632   0.01823   0.01014  -0.0461   0.7560   0.9182
   2.750   0.4850   0.01824   0.01022  -0.0451   0.7464   0.9247
   3.000   0.5205   0.01793   0.00993  -0.0462   0.7406   0.9295
   3.250   0.5445   0.01789   0.00997  -0.0456   0.7296   0.9354
   3.500   0.5711   0.01776   0.00993  -0.0454   0.7194   0.9419
   3.750   0.6060   0.01748   0.00971  -0.0464   0.7105   0.9464
   4.000   0.6352   0.01735   0.00966  -0.0467   0.6987   0.9525
   4.250   0.6636   0.01725   0.00968  -0.0469   0.6854   0.9592
   4.500   0.6947   0.01714   0.00967  -0.0476   0.6711   0.9657
   4.750   0.7265   0.01700   0.00964  -0.0484   0.6550   0.9725
   5.000   0.7563   0.01698   0.00976  -0.0491   0.6343   0.9813
   5.250   0.7892   0.01681   0.00967  -0.0501   0.6114   0.9911
   5.500   0.8117   0.01674   0.00960  -0.0492   0.5850   1.0000
   5.750   0.8321   0.01670   0.00951  -0.0477   0.5552   1.0000
   6.000   0.8526   0.01683   0.00956  -0.0464   0.5195   1.0000
   6.250   0.8725   0.01712   0.00970  -0.0451   0.4807   1.0000
   6.500   0.8903   0.01759   0.00999  -0.0436   0.4403   1.0000
   6.750   0.9067   0.01818   0.01042  -0.0420   0.4010   1.0000
   7.000   0.9220   0.01885   0.01094  -0.0403   0.3641   1.0000
   7.250   0.9364   0.01957   0.01154  -0.0386   0.3297   1.0000
   7.500   0.9494   0.02033   0.01217  -0.0366   0.2982   1.0000
   7.750   0.9624   0.02114   0.01287  -0.0348   0.2690   1.0000
   8.000   0.9758   0.02197   0.01362  -0.0331   0.2425   1.0000
   8.250   0.9891   0.02285   0.01443  -0.0315   0.2180   1.0000
   8.500   1.0016   0.02380   0.01531  -0.0298   0.1953   1.0000
   8.750   1.0149   0.02475   0.01623  -0.0283   0.1733   1.0000
   9.000   1.0266   0.02580   0.01726  -0.0268   0.1540   1.0000
   9.250   1.0393   0.02685   0.01831  -0.0254   0.1350   1.0000
   9.500   1.0506   0.02801   0.01945  -0.0239   0.1181   1.0000
   9.750   1.0611   0.02927   0.02069  -0.0224   0.1031   1.0000
  10.000   1.0711   0.03059   0.02203  -0.0210   0.0906   1.0000
  10.250   1.0808   0.03199   0.02346  -0.0196   0.0799   1.0000
  10.500   1.0890   0.03352   0.02501  -0.0181   0.0711   1.0000
  10.750   1.0963   0.03516   0.02670  -0.0167   0.0644   1.0000
  11.000   1.1043   0.03683   0.02851  -0.0154   0.0585   1.0000
  11.250   1.1107   0.03859   0.03034  -0.0141   0.0532   1.0000
  11.500   1.1167   0.04053   0.03238  -0.0129   0.0491   1.0000
  11.750   1.1239   0.04242   0.03442  -0.0118   0.0452   1.0000
  12.000   1.1281   0.04452   0.03659  -0.0108   0.0420   1.0000
  12.250   1.1326   0.04679   0.03898  -0.0098   0.0391   1.0000
  12.500   1.1385   0.04899   0.04140  -0.0089   0.0361   1.0000
  12.750   1.1418   0.05136   0.04390  -0.0083   0.0337   1.0000
  13.000   1.1418   0.05406   0.04666  -0.0078   0.0316   1.0000
  13.250   1.1437   0.05690   0.04970  -0.0072   0.0297   1.0000
  13.500   1.1448   0.05992   0.05298  -0.0068   0.0278   1.0000
  13.750   1.1436   0.06312   0.05638  -0.0068   0.0262   1.0000
  14.000   1.1401   0.06648   0.05993  -0.0071   0.0248   1.0000
  14.250   1.1355   0.07013   0.06367  -0.0077   0.0236   1.0000
  14.500   1.1292   0.07436   0.06802  -0.0084   0.0226   1.0000
  14.750   1.1213   0.07909   0.07306  -0.0097   0.0219   1.0000
  15.000   1.1107   0.08446   0.07872  -0.0114   0.0212   1.0000
  15.250   1.0990   0.09025   0.08476  -0.0137   0.0208   1.0000
  15.500   1.0851   0.09669   0.09145  -0.0167   0.0204   1.0000
  15.750   1.0690   0.10390   0.09889  -0.0206   0.0200   1.0000
  16.000   1.0516   0.11183   0.10705  -0.0251   0.0200   1.0000
  16.250   1.0315   0.12090   0.11632  -0.0306   0.0202   1.0000
  16.500   1.0090   0.13112   0.12673  -0.0371   0.0206   1.0000
  16.750   0.9825   0.14323   0.13894  -0.0447   0.0212   1.0000
  17.000   0.9558   0.15641   0.15220  -0.0528   0.0218   1.0000
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