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MH 200 12.97% (mh200-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: MH 200 12.97% (mh200-il)
Reynolds number: 50,000
Max Cl/Cd: 32.35 at α=7.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-mh200-il-50000-n5.txt
Download as CSV file: xf-mh200-il-50000-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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.4167   0.10324   0.09615  -0.0519   1.0000   0.0381
 -10.500  -0.4215   0.09861   0.09161  -0.0535   1.0000   0.0375
 -10.250  -0.4290   0.09349   0.08658  -0.0554   1.0000   0.0368
 -10.000  -0.4395   0.08769   0.08088  -0.0580   1.0000   0.0361
  -9.750  -0.4567   0.08165   0.07490  -0.0611   1.0000   0.0354
  -9.500  -0.4787   0.07670   0.07002  -0.0628   1.0000   0.0348
  -9.250  -0.5048   0.07300   0.06636  -0.0625   1.0000   0.0344
  -9.000  -0.5354   0.07051   0.06390  -0.0598   1.0000   0.0339
  -8.750  -0.5666   0.06876   0.06217  -0.0555   1.0000   0.0336
  -8.500  -0.5936   0.06656   0.05991  -0.0515   1.0000   0.0332
  -8.250  -0.6168   0.06410   0.05730  -0.0477   1.0000   0.0329
  -8.000  -0.6338   0.06149   0.05449  -0.0443   1.0000   0.0327
  -7.750  -0.6463   0.05866   0.05138  -0.0412   1.0000   0.0324
  -7.500  -0.6530   0.05575   0.04816  -0.0384   1.0000   0.0323
  -7.250  -0.6458   0.05235   0.04435  -0.0379   0.9971   0.0322
  -7.000  -0.6286   0.04874   0.04028  -0.0387   0.9921   0.0325
  -6.750  -0.6090   0.04559   0.03670  -0.0392   0.9873   0.0328
  -6.500  -0.5857   0.04271   0.03339  -0.0399   0.9833   0.0334
  -6.250  -0.5635   0.04031   0.03063  -0.0398   0.9789   0.0344
  -6.000  -0.5384   0.03829   0.02829  -0.0400   0.9748   0.0365
  -5.750  -0.5100   0.03651   0.02605  -0.0404   0.9713   0.0398
  -5.500  -0.4842   0.03478   0.02413  -0.0401   0.9678   0.0429
  -5.250  -0.4602   0.03339   0.02264  -0.0396   0.9638   0.0462
  -5.000  -0.4332   0.03225   0.02123  -0.0394   0.9601   0.0526
  -4.750  -0.4062   0.03098   0.01992  -0.0398   0.9567   0.0628
  -4.500  -0.3866   0.02973   0.01867  -0.0388   0.9519   0.0799
  -4.250  -0.3659   0.02791   0.01730  -0.0387   0.9476   0.1353
  -4.000  -0.3487   0.02545   0.01640  -0.0390   0.9438   0.3631
  -3.750  -0.3403   0.02503   0.01723  -0.0338   0.9389   0.5730
  -3.500  -0.3261   0.02582   0.01813  -0.0289   0.9337   0.6784
  -3.250  -0.3032   0.02649   0.01852  -0.0267   0.9293   0.7316
  -3.000  -0.2871   0.02692   0.01873  -0.0235   0.9239   0.7645
  -2.750  -0.2669   0.02729   0.01882  -0.0211   0.9189   0.7928
  -2.500  -0.2408   0.02762   0.01888  -0.0199   0.9149   0.8184
  -2.250  -0.2221   0.02780   0.01886  -0.0177   0.9096   0.8402
  -2.000  -0.1978   0.02796   0.01880  -0.0166   0.9047   0.8612
  -1.750  -0.1634   0.02817   0.01874  -0.0175   0.9011   0.8807
  -1.500  -0.1339   0.02829   0.01866  -0.0178   0.8964   0.8994
  -1.250  -0.1007   0.02840   0.01857  -0.0191   0.8916   0.9158
  -1.000  -0.0556   0.02855   0.01848  -0.0228   0.8880   0.9284
  -0.750  -0.0042   0.02870   0.01842  -0.0278   0.8852   0.9380
  -0.500   0.0305   0.02880   0.01838  -0.0301   0.8793   0.9485
  -0.250   0.0742   0.02892   0.01835  -0.0340   0.8748   0.9576
   0.000   0.1276   0.02903   0.01832  -0.0397   0.8715   0.9640
   0.250   0.1639   0.02916   0.01837  -0.0425   0.8652   0.9728
   0.500   0.2077   0.02926   0.01841  -0.0465   0.8599   0.9803
   0.750   0.2574   0.02931   0.01840  -0.0514   0.8561   0.9862
   1.000   0.2869   0.02949   0.01857  -0.0530   0.8475   0.9957
   1.250   0.3286   0.02954   0.01860  -0.0563   0.8425   1.0000
   1.500   0.3323   0.02974   0.01880  -0.0530   0.8316   1.0000
   1.750   0.3489   0.02985   0.01892  -0.0516   0.8231   1.0000
   2.250   0.3747   0.03010   0.01920  -0.0476   0.8036   1.0000
   2.500   0.3958   0.03016   0.01927  -0.0468   0.7951   1.0000
   2.750   0.4143   0.03021   0.01935  -0.0455   0.7857   1.0000
   3.000   0.4233   0.03039   0.01955  -0.0428   0.7740   1.0000
   3.250   0.4429   0.03050   0.01972  -0.0417   0.7637   1.0000
   3.500   0.4778   0.03036   0.01965  -0.0428   0.7559   1.0000
   4.000   0.5164   0.03062   0.02006  -0.0404   0.7313   1.0000
   4.250   0.5419   0.03060   0.02013  -0.0400   0.7193   1.0000
   4.500   0.5723   0.03039   0.02003  -0.0400   0.7080   1.0000
   4.750   0.6087   0.02994   0.01974  -0.0407   0.6976   1.0000
   5.000   0.6335   0.02978   0.01971  -0.0399   0.6834   1.0000
   5.250   0.6594   0.02955   0.01961  -0.0392   0.6689   1.0000
   5.500   0.6746   0.02969   0.01986  -0.0372   0.6505   1.0000
   5.750   0.6972   0.02952   0.01987  -0.0360   0.6330   1.0000
   6.000   0.7240   0.02913   0.01964  -0.0351   0.6154   1.0000
   6.250   0.7520   0.02865   0.01932  -0.0343   0.5966   1.0000
   6.500   0.7752   0.02842   0.01924  -0.0329   0.5734   1.0000
   6.750   0.8031   0.02801   0.01899  -0.0320   0.5484   1.0000
   7.000   0.8330   0.02757   0.01863  -0.0312   0.5188   1.0000
   7.250   0.8627   0.02728   0.01834  -0.0305   0.4847   1.0000
   7.500   0.8849   0.02751   0.01850  -0.0291   0.4478   1.0000
   7.750   0.9047   0.02797   0.01886  -0.0275   0.4110   1.0000
   8.000   0.9186   0.02879   0.01959  -0.0256   0.3759   1.0000
   8.250   0.9312   0.02975   0.02045  -0.0237   0.3433   1.0000
   8.500   0.9425   0.03085   0.02145  -0.0219   0.3133   1.0000
   8.750   0.9528   0.03206   0.02259  -0.0201   0.2852   1.0000
   9.000   0.9624   0.03336   0.02384  -0.0183   0.2588   1.0000
   9.250   0.9718   0.03475   0.02517  -0.0167   0.2348   1.0000
   9.500   0.9803   0.03623   0.02666  -0.0152   0.2120   1.0000
   9.750   0.9895   0.03779   0.02823  -0.0138   0.1908   1.0000
  10.000   0.9973   0.03946   0.02989  -0.0124   0.1711   1.0000
  10.250   1.0056   0.04120   0.03157  -0.0112   0.1542   1.0000
  10.500   1.0139   0.04304   0.03350  -0.0100   0.1374   1.0000
  10.750   1.0234   0.04494   0.03546  -0.0090   0.1234   1.0000
  11.000   1.0321   0.04692   0.03748  -0.0080   0.1113   1.0000
  11.250   1.0397   0.04897   0.03956  -0.0071   0.1009   1.0000
  11.500   1.0513   0.05113   0.04194  -0.0062   0.0913   1.0000
  11.750   1.0598   0.05344   0.04443  -0.0054   0.0835   1.0000
  12.000   1.0658   0.05580   0.04688  -0.0047   0.0769   1.0000
  12.250   1.0768   0.05850   0.04983  -0.0039   0.0716   1.0000
  12.500   1.0808   0.06137   0.05295  -0.0033   0.0668   1.0000
  12.750   1.0865   0.06394   0.05545  -0.0029   0.0626   1.0000
  13.000   1.0814   0.06792   0.05990  -0.0025   0.0596   1.0000
  13.250   1.0771   0.07203   0.06435  -0.0025   0.0573   1.0000
  13.500   1.0703   0.07627   0.06884  -0.0028   0.0553   1.0000
  13.750   1.0639   0.08041   0.07314  -0.0034   0.0535   1.0000
  14.000   1.0630   0.08399   0.07670  -0.0040   0.0512   1.0000
  14.250   1.0438   0.09013   0.08317  -0.0061   0.0507   1.0000
  14.500   1.0226   0.09704   0.09036  -0.0091   0.0505   1.0000
  14.750   1.0006   0.10473   0.09826  -0.0131   0.0506   1.0000
  15.000   0.9778   0.11335   0.10706  -0.0180   0.0508   1.0000
  15.250   0.9557   0.12274   0.11657  -0.0237   0.0512   1.0000
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