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MH 38 9.68% (mh38-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: MH 38 9.68% (mh38-il)
Reynolds number: 100,000
Max Cl/Cd: 61.64 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-mh38-il-100000-n5.txt
Download as CSV file: xf-mh38-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 38  9.68%                                    
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3295   0.09191   0.08722  -0.0411   1.0000   0.0200
  -8.500  -0.3302   0.08845   0.08385  -0.0421   1.0000   0.0198
  -8.250  -0.3336   0.08503   0.08052  -0.0428   1.0000   0.0198
  -8.000  -0.3398   0.08214   0.07775  -0.0428   1.0000   0.0195
  -7.750  -0.3532   0.08003   0.07580  -0.0413   1.0000   0.0194
  -7.500  -0.3480   0.07528   0.07111  -0.0466   0.9849   0.0191
  -7.250  -0.3302   0.06779   0.06362  -0.0577   0.9701   0.0190
  -7.000  -0.3099   0.05921   0.05496  -0.0705   0.9564   0.0187
  -6.750  -0.2908   0.04803   0.04351  -0.0837   0.9427   0.0183
  -6.500  -0.2734   0.03874   0.03357  -0.0922   0.9299   0.0182
  -6.250  -0.2523   0.03261   0.02666  -0.0959   0.9191   0.0187
  -6.000  -0.2267   0.02832   0.02158  -0.0978   0.9108   0.0201
  -5.750  -0.2000   0.02560   0.01823  -0.0986   0.9024   0.0233
  -5.500  -0.1740   0.02397   0.01638  -0.0990   0.8942   0.0269
  -5.250  -0.1456   0.02207   0.01403  -0.0992   0.8872   0.0316
  -5.000  -0.1195   0.02098   0.01280  -0.0992   0.8789   0.0397
  -4.750  -0.0910   0.01973   0.01133  -0.0994   0.8728   0.0496
  -4.500  -0.0649   0.01897   0.01043  -0.0992   0.8644   0.0623
  -4.250  -0.0366   0.01832   0.00961  -0.0993   0.8584   0.0783
  -4.000  -0.0105   0.01773   0.00891  -0.0990   0.8504   0.0937
  -3.750   0.0174   0.01723   0.00833  -0.0990   0.8445   0.1132
  -3.500   0.0435   0.01684   0.00790  -0.0988   0.8368   0.1336
  -3.250   0.0713   0.01644   0.00747  -0.0987   0.8313   0.1581
  -3.000   0.0972   0.01613   0.00716  -0.0985   0.8237   0.1837
  -2.750   0.1247   0.01579   0.00679  -0.0984   0.8183   0.2162
  -2.500   0.1506   0.01552   0.00659  -0.0981   0.8110   0.2540
  -2.250   0.1777   0.01522   0.00636  -0.0980   0.8054   0.3038
  -2.000   0.2035   0.01495   0.00626  -0.0977   0.7987   0.3651
  -1.750   0.2295   0.01467   0.00614  -0.0973   0.7928   0.4396
  -1.500   0.2548   0.01441   0.00607  -0.0967   0.7867   0.5258
  -1.250   0.2788   0.01411   0.00605  -0.0956   0.7805   0.6245
  -1.000   0.3006   0.01379   0.00602  -0.0937   0.7750   0.7399
  -0.750   0.3333   0.01343   0.00590  -0.0937   0.7688   0.9178
  -0.500   0.3694   0.01340   0.00567  -0.0953   0.7638   1.0000
  -0.250   0.3955   0.01356   0.00570  -0.0952   0.7566   1.0000
   0.000   0.4228   0.01366   0.00564  -0.0950   0.7511   1.0000
   0.250   0.4491   0.01382   0.00569  -0.0948   0.7443   1.0000
   0.500   0.4762   0.01394   0.00569  -0.0946   0.7384   1.0000
   0.750   0.5027   0.01410   0.00577  -0.0944   0.7319   1.0000
   1.000   0.5295   0.01423   0.00582  -0.0942   0.7256   1.0000
   1.250   0.5562   0.01438   0.00592  -0.0940   0.7193   1.0000
   1.500   0.5828   0.01454   0.00603  -0.0938   0.7125   1.0000
   1.750   0.6097   0.01468   0.00612  -0.0936   0.7064   1.0000
   2.000   0.6360   0.01485   0.00628  -0.0933   0.6992   1.0000
   2.500   0.6891   0.01517   0.00661  -0.0928   0.6854   1.0000
   2.750   0.7157   0.01533   0.00677  -0.0925   0.6784   1.0000
   3.000   0.7421   0.01549   0.00695  -0.0922   0.6709   1.0000
   3.250   0.7681   0.01567   0.00721  -0.0919   0.6630   1.0000
   3.500   0.7950   0.01578   0.00734  -0.0916   0.6556   1.0000
   3.750   0.8203   0.01599   0.00763  -0.0912   0.6464   1.0000
   4.000   0.8468   0.01612   0.00781  -0.0908   0.6381   1.0000
   4.250   0.8729   0.01626   0.00801  -0.0903   0.6289   1.0000
   4.500   0.8980   0.01645   0.00836  -0.0898   0.6184   1.0000
   4.750   0.9236   0.01661   0.00861  -0.0893   0.6079   1.0000
   5.000   0.9493   0.01674   0.00884  -0.0888   0.5972   1.0000
   5.250   0.9749   0.01688   0.00906  -0.0882   0.5857   1.0000
   5.500   0.9999   0.01703   0.00933  -0.0875   0.5729   1.0000
   5.750   1.0242   0.01722   0.00966  -0.0868   0.5581   1.0000
   6.000   1.0479   0.01742   0.01008  -0.0859   0.5413   1.0000
   6.250   1.0714   0.01761   0.01038  -0.0850   0.5222   1.0000
   6.500   1.0938   0.01782   0.01069  -0.0838   0.4985   1.0000
   6.750   1.1145   0.01808   0.01098  -0.0824   0.4668   1.0000
   7.000   1.1322   0.01852   0.01131  -0.0805   0.4222   1.0000
   7.250   1.1462   0.01928   0.01183  -0.0782   0.3644   1.0000
   7.500   1.1563   0.02039   0.01262  -0.0757   0.3003   1.0000
   7.750   1.1618   0.02189   0.01371  -0.0728   0.2282   1.0000
   8.000   1.1630   0.02379   0.01509  -0.0697   0.1521   1.0000
   8.250   1.1613   0.02596   0.01681  -0.0664   0.0853   1.0000
   8.500   1.1595   0.02795   0.01850  -0.0629   0.0528   1.0000
   8.750   1.1600   0.02985   0.02032  -0.0598   0.0370   1.0000
   9.000   1.1595   0.03191   0.02240  -0.0569   0.0296   1.0000
   9.250   1.1629   0.03374   0.02440  -0.0546   0.0247   1.0000
   9.500   1.1645   0.03581   0.02653  -0.0526   0.0206   1.0000
   9.750   1.1640   0.03818   0.02903  -0.0505   0.0187   1.0000
  10.000   1.1668   0.04041   0.03146  -0.0487   0.0173   1.0000
  10.250   1.1707   0.04269   0.03390  -0.0471   0.0163   1.0000
  10.500   1.1762   0.04497   0.03633  -0.0457   0.0152   1.0000
  10.750   1.1817   0.04725   0.03872  -0.0446   0.0137   1.0000
  11.000   1.1859   0.04975   0.04132  -0.0436   0.0126   1.0000
  11.250   1.1908   0.05284   0.04452  -0.0424   0.0115   1.0000
  11.500   1.1991   0.05532   0.04726  -0.0414   0.0109   1.0000
  11.750   1.2062   0.05823   0.05042  -0.0404   0.0106   1.0000
  12.000   1.2105   0.06152   0.05399  -0.0396   0.0104   1.0000
  12.250   1.2110   0.06515   0.05790  -0.0390   0.0102   1.0000
  12.500   1.2078   0.06920   0.06226  -0.0387   0.0100   1.0000
  12.750   1.2015   0.07357   0.06699  -0.0389   0.0099   1.0000
  13.000   1.1921   0.07837   0.07207  -0.0395   0.0099   1.0000
  13.250   1.1802   0.08363   0.07760  -0.0407   0.0098   1.0000
  13.500   1.1671   0.08918   0.08341  -0.0424   0.0099   1.0000
  13.750   1.1525   0.09525   0.08972  -0.0448   0.0099   1.0000
  14.000   1.1366   0.10196   0.09667  -0.0479   0.0099   1.0000
  14.250   1.1205   0.10916   0.10407  -0.0518   0.0100   1.0000
  14.500   1.1041   0.11698   0.11210  -0.0564   0.0101   1.0000
  14.750   1.0874   0.12554   0.12075  -0.0617   0.0102   1.0000
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