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MH 200 12.97% (mh200-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: MH 200 12.97% (mh200-il)
Reynolds number: 200,000
Max Cl/Cd: 76.08 at α=6°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-mh200-il-200000.txt
Download as CSV file: xf-mh200-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.3457   0.09147   0.08846  -0.0486   1.0000   0.0557
 -10.000  -0.3687   0.09123   0.08833  -0.0437   1.0000   0.0559
  -9.750  -0.3681   0.08797   0.08508  -0.0443   0.9984   0.0574
  -9.500  -0.3647   0.08241   0.07953  -0.0481   0.9958   0.0595
  -9.250  -0.3695   0.07526   0.07239  -0.0537   0.9931   0.0618
  -9.000  -0.3893   0.06528   0.06240  -0.0628   0.9888   0.0627
  -8.750  -0.4141   0.05651   0.05353  -0.0713   0.9838   0.0628
  -8.500  -0.4374   0.05119   0.04804  -0.0753   0.9739   0.0634
  -7.000  -0.4535   0.03305   0.02711  -0.0768   0.9444   0.0344
  -6.750  -0.4207   0.02864   0.02203  -0.0775   0.9427   0.0266
  -6.500  -0.4046   0.02629   0.01911  -0.0747   0.9356   0.0240
  -6.250  -0.3719   0.02475   0.01729  -0.0756   0.9330   0.0233
  -6.000  -0.3370   0.02304   0.01541  -0.0770   0.9312   0.0232
  -5.750  -0.3034   0.02099   0.01331  -0.0782   0.9296   0.0237
  -5.500  -0.2829   0.01980   0.01213  -0.0772   0.9245   0.0251
  -5.250  -0.2600   0.01892   0.01121  -0.0766   0.9199   0.0269
  -5.000  -0.2299   0.01809   0.01032  -0.0773   0.9171   0.0316
  -4.750  -0.2005   0.01680   0.00900  -0.0781   0.9147   0.0449
  -4.500  -0.1976   0.01482   0.00816  -0.0750   0.9071   0.2404
  -4.250  -0.1765   0.01356   0.00778  -0.0749   0.9033   0.4362
  -4.000  -0.1516   0.01294   0.00792  -0.0741   0.9008   0.6056
  -3.750  -0.1318   0.01326   0.00835  -0.0720   0.8960   0.6725
  -3.500  -0.1089   0.01364   0.00869  -0.0705   0.8913   0.7082
  -3.250  -0.0799   0.01392   0.00888  -0.0701   0.8884   0.7317
  -3.000  -0.0489   0.01416   0.00903  -0.0700   0.8862   0.7490
  -2.750  -0.0301   0.01453   0.00934  -0.0680   0.8810   0.7631
  -2.500  -0.0068   0.01479   0.00953  -0.0667   0.8765   0.7762
  -2.250   0.0218   0.01494   0.00960  -0.0663   0.8735   0.7887
  -2.000   0.0525   0.01504   0.00961  -0.0664   0.8712   0.8002
  -1.750   0.0660   0.01540   0.00996  -0.0633   0.8647   0.8088
  -1.500   0.0913   0.01550   0.01001  -0.0625   0.8608   0.8188
  -1.250   0.1209   0.01553   0.00997  -0.0625   0.8580   0.8287
  -1.000   0.1429   0.01567   0.01009  -0.0609   0.8538   0.8365
  -0.750   0.1610   0.01583   0.01022  -0.0590   0.8477   0.8464
  -0.500   0.1883   0.01582   0.01018  -0.0583   0.8443   0.8549
  -0.250   0.2193   0.01572   0.01003  -0.0584   0.8418   0.8624
   0.000   0.2321   0.01592   0.01023  -0.0557   0.8336   0.8712
   0.250   0.2614   0.01577   0.01005  -0.0555   0.8299   0.8769
   0.500   0.2945   0.01559   0.00983  -0.0561   0.8271   0.8827
   0.750   0.3085   0.01570   0.00996  -0.0537   0.8185   0.8901
   1.000   0.3396   0.01550   0.00973  -0.0539   0.8146   0.8954
   1.250   0.3616   0.01549   0.00972  -0.0529   0.8081   0.9023
   1.500   0.3881   0.01532   0.00957  -0.0522   0.8022   0.9076
   1.750   0.4225   0.01504   0.00925  -0.0531   0.7985   0.9129
   2.000   0.4406   0.01500   0.00926  -0.0512   0.7894   0.9192
   2.250   0.4757   0.01466   0.00890  -0.0521   0.7847   0.9235
   2.500   0.4957   0.01458   0.00886  -0.0507   0.7754   0.9302
   2.750   0.5321   0.01422   0.00849  -0.0519   0.7701   0.9335
   3.000   0.5547   0.01411   0.00843  -0.0508   0.7604   0.9394
   3.250   0.5889   0.01379   0.00811  -0.0517   0.7546   0.9437
   3.500   0.6157   0.01364   0.00803  -0.0515   0.7442   0.9482
   3.750   0.6454   0.01344   0.00787  -0.0518   0.7350   0.9531
   4.000   0.6780   0.01314   0.00759  -0.0525   0.7264   0.9575
   4.250   0.7103   0.01295   0.00748  -0.0534   0.7143   0.9614
   4.500   0.7416   0.01274   0.00733  -0.0540   0.7013   0.9662
   4.750   0.7717   0.01253   0.00718  -0.0544   0.6871   0.9712
   5.000   0.8078   0.01231   0.00703  -0.0560   0.6701   0.9747
   5.250   0.8395   0.01217   0.00697  -0.0569   0.6477   0.9799
   5.500   0.8723   0.01205   0.00687  -0.0580   0.6197   0.9846
   5.750   0.9064   0.01205   0.00680  -0.0594   0.5813   0.9891
   6.000   0.9358   0.01230   0.00686  -0.0600   0.5314   0.9955
   6.250   0.9488   0.01272   0.00705  -0.0577   0.4845   1.0000
   6.500   0.9461   0.01307   0.00725  -0.0523   0.4484   1.0000
   6.750   0.9541   0.01364   0.00761  -0.0493   0.4069   1.0000
   7.000   0.9666   0.01433   0.00812  -0.0473   0.3645   1.0000
   7.250   0.9799   0.01509   0.00868  -0.0455   0.3249   1.0000
   7.500   0.9939   0.01582   0.00926  -0.0438   0.2894   1.0000
   7.750   1.0068   0.01658   0.00989  -0.0419   0.2584   1.0000
   8.000   1.0201   0.01738   0.01057  -0.0401   0.2308   1.0000
   8.250   1.0333   0.01821   0.01129  -0.0384   0.2050   1.0000
   8.500   1.0455   0.01910   0.01209  -0.0366   0.1811   1.0000
   8.750   1.0583   0.02000   0.01292  -0.0349   0.1573   1.0000
   9.000   1.0701   0.02099   0.01383  -0.0332   0.1354   1.0000
   9.250   1.0801   0.02213   0.01486  -0.0313   0.1158   1.0000
   9.500   1.0890   0.02340   0.01605  -0.0294   0.0989   1.0000
   9.750   1.0985   0.02468   0.01729  -0.0276   0.0847   1.0000
  10.000   1.1060   0.02615   0.01871  -0.0256   0.0742   1.0000
  10.250   1.1171   0.02741   0.02003  -0.0241   0.0660   1.0000
  10.500   1.1258   0.02896   0.02162  -0.0224   0.0593   1.0000
  10.750   1.1355   0.03038   0.02308  -0.0210   0.0536   1.0000
  11.000   1.1451   0.03211   0.02487  -0.0195   0.0491   1.0000
  11.250   1.1560   0.03347   0.02633  -0.0183   0.0447   1.0000
  11.500   1.1656   0.03570   0.02850  -0.0169   0.0405   1.0000
  11.750   1.1757   0.03706   0.03009  -0.0157   0.0375   1.0000
  12.000   1.1841   0.03867   0.03179  -0.0146   0.0343   1.0000
  12.250   1.1944   0.04139   0.03451  -0.0135   0.0308   1.0000
  12.500   1.1995   0.04308   0.03644  -0.0123   0.0286   1.0000
  12.750   1.2033   0.04496   0.03847  -0.0113   0.0261   1.0000
  13.000   1.2072   0.04723   0.04078  -0.0105   0.0241   1.0000
  13.250   1.2086   0.05067   0.04445  -0.0094   0.0222   1.0000
  13.500   1.2073   0.05312   0.04713  -0.0087   0.0204   1.0000
  13.750   1.2065   0.05574   0.04991  -0.0082   0.0190   1.0000
  14.000   1.2052   0.05850   0.05274  -0.0081   0.0178   1.0000
  14.250   1.2014   0.06240   0.05675  -0.0078   0.0168   1.0000
  14.500   1.1891   0.06769   0.06232  -0.0078   0.0163   1.0000
  14.750   1.1793   0.07209   0.06698  -0.0084   0.0161   1.0000
  15.000   1.1653   0.07722   0.07240  -0.0097   0.0157   1.0000
  15.250   1.1514   0.08279   0.07823  -0.0115   0.0156   1.0000
  15.500   1.1357   0.08899   0.08467  -0.0140   0.0154   1.0000
  15.750   1.1176   0.09600   0.09192  -0.0175   0.0153   1.0000
  16.000   1.0995   0.10347   0.09960  -0.0214   0.0154   1.0000
  16.250   1.0800   0.11171   0.10805  -0.0263   0.0154   1.0000
  16.500   1.0603   0.12049   0.11702  -0.0318   0.0157   1.0000
  16.750   1.0394   0.13006   0.12674  -0.0378   0.0160   1.0000
  17.000   1.0182   0.14022   0.13704  -0.0444   0.0162   1.0000
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