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MH 83 13.29% (mh83-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: MH 83 13.29% (mh83-il)
Reynolds number: 200,000
Max Cl/Cd: 67.12 at α=7.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-mh83-il-200000-n5.txt
Download as CSV file: xf-mh83-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 83  13.29%                                   
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.2745   0.11327   0.10937  -0.0043   0.7339   0.0308
  -9.500  -0.2735   0.10958   0.10564  -0.0071   0.7219   0.0310
  -9.250  -0.2702   0.10589   0.10191  -0.0094   0.7096   0.0311
  -9.000  -0.2666   0.10218   0.09816  -0.0115   0.6982   0.0311
  -8.750  -0.2618   0.09855   0.09449  -0.0134   0.6865   0.0311
  -8.250  -0.2510   0.08932   0.08517  -0.0158   0.6663   0.0230
  -8.000  -0.2388   0.08756   0.08336  -0.0158   0.6530   0.0224
  -7.750  -0.2327   0.08450   0.08028  -0.0170   0.6423   0.0218
  -7.250  -0.2477   0.07292   0.06870  -0.0238   0.6294   0.0193
  -7.000  -0.2461   0.06902   0.06479  -0.0269   0.6204   0.0193
  -6.750  -0.2470   0.06167   0.05740  -0.0348   0.6146   0.0194
  -6.500  -0.2410   0.05259   0.04823  -0.0449   0.6087   0.0193
  -6.250  -0.2311   0.04173   0.03699  -0.0551   0.6029   0.0190
  -5.750  -0.1931   0.02914   0.02303  -0.0636   0.5870   0.0185
  -5.500  -0.1681   0.02602   0.01929  -0.0647   0.5777   0.0186
  -5.250  -0.1414   0.02378   0.01657  -0.0652   0.5674   0.0188
  -5.000  -0.1140   0.02208   0.01443  -0.0654   0.5579   0.0190
  -4.750  -0.0862   0.02076   0.01274  -0.0654   0.5476   0.0193
  -4.500  -0.0584   0.01969   0.01147  -0.0654   0.5380   0.0197
  -4.250  -0.0306   0.01889   0.01052  -0.0654   0.5282   0.0201
  -4.000  -0.0024   0.01818   0.00968  -0.0654   0.5185   0.0207
  -3.750   0.0258   0.01760   0.00893  -0.0653   0.5093   0.0216
  -3.500   0.0544   0.01707   0.00823  -0.0652   0.5001   0.0229
  -3.000   0.1110   0.01608   0.00712  -0.0651   0.4824   0.0250
  -2.750   0.1396   0.01569   0.00658  -0.0650   0.4740   0.0262
  -2.500   0.1684   0.01530   0.00613  -0.0650   0.4651   0.0276
  -2.000   0.2260   0.01473   0.00540  -0.0649   0.4497   0.0329
  -1.750   0.2547   0.01448   0.00509  -0.0649   0.4421   0.0402
  -1.500   0.2836   0.01414   0.00482  -0.0649   0.4345   0.0603
  -1.250   0.3122   0.01391   0.00465  -0.0649   0.4268   0.0975
  -1.000   0.3407   0.01372   0.00455  -0.0650   0.4198   0.1374
  -0.750   0.3690   0.01346   0.00454  -0.0651   0.4128   0.2118
  -0.250   0.4257   0.01319   0.00452  -0.0651   0.4004   0.3276
   0.000   0.4539   0.01310   0.00452  -0.0651   0.3941   0.3832
   0.250   0.4817   0.01300   0.00454  -0.0650   0.3884   0.4497
   0.500   0.5091   0.01285   0.00461  -0.0647   0.3821   0.5333
   0.750   0.5351   0.01267   0.00468  -0.0641   0.3766   0.6371
   1.000   0.5579   0.01241   0.00473  -0.0625   0.3721   0.7701
   1.250   0.5908   0.01217   0.00469  -0.0629   0.3667   1.0000
   1.500   0.6193   0.01235   0.00474  -0.0629   0.3617   1.0000
   2.000   0.6762   0.01275   0.00489  -0.0628   0.3523   1.0000
   2.250   0.7045   0.01294   0.00500  -0.0628   0.3474   1.0000
   2.500   0.7326   0.01316   0.00510  -0.0628   0.3433   1.0000
   2.750   0.7606   0.01340   0.00523  -0.0627   0.3397   1.0000
   3.000   0.7888   0.01361   0.00540  -0.0627   0.3357   1.0000
   3.250   0.8168   0.01383   0.00557  -0.0627   0.3317   1.0000
   3.500   0.8445   0.01407   0.00572  -0.0626   0.3279   1.0000
   3.750   0.8719   0.01436   0.00590  -0.0626   0.3245   1.0000
   4.000   0.8998   0.01458   0.00613  -0.0625   0.3208   1.0000
   4.250   0.9274   0.01483   0.00635  -0.0625   0.3173   1.0000
   4.500   0.9548   0.01510   0.00658  -0.0624   0.3141   1.0000
   4.750   0.9819   0.01539   0.00681  -0.0623   0.3111   1.0000
   5.000   1.0089   0.01570   0.00705  -0.0622   0.3082   1.0000
   5.250   1.0362   0.01597   0.00735  -0.0622   0.3048   1.0000
   5.500   1.0632   0.01625   0.00765  -0.0621   0.3016   1.0000
   5.750   1.0900   0.01655   0.00794  -0.0620   0.2987   1.0000
   6.000   1.1165   0.01687   0.00823  -0.0619   0.2961   1.0000
   6.250   1.1428   0.01724   0.00854  -0.0618   0.2935   1.0000
   6.500   1.1691   0.01756   0.00891  -0.0616   0.2907   1.0000
   6.750   1.1954   0.01789   0.00928  -0.0615   0.2876   1.0000
   7.000   1.2214   0.01823   0.00965  -0.0614   0.2848   1.0000
   7.250   1.2471   0.01859   0.01003  -0.0612   0.2823   1.0000
   7.500   1.2725   0.01896   0.01039  -0.0611   0.2799   1.0000
   7.750   1.2977   0.01939   0.01077  -0.0608   0.2775   1.0000
   8.000   1.3228   0.01977   0.01127  -0.0607   0.2747   1.0000
   8.250   1.3476   0.02017   0.01175  -0.0604   0.2720   1.0000
   8.500   1.3722   0.02058   0.01222  -0.0602   0.2695   1.0000
   8.750   1.3963   0.02100   0.01269  -0.0599   0.2670   1.0000
   9.000   1.4203   0.02143   0.01312  -0.0596   0.2646   1.0000
   9.250   1.4440   0.02192   0.01358  -0.0593   0.2622   1.0000
   9.500   1.4669   0.02241   0.01422  -0.0590   0.2598   1.0000
   9.750   1.4893   0.02292   0.01484  -0.0586   0.2573   1.0000
  10.000   1.5113   0.02342   0.01543  -0.0581   0.2546   1.0000
  10.250   1.5328   0.02392   0.01600  -0.0576   0.2520   1.0000
  10.500   1.5540   0.02444   0.01654  -0.0571   0.2497   1.0000
  10.750   1.5755   0.02501   0.01710  -0.0566   0.2476   1.0000
  11.000   1.5940   0.02566   0.01793  -0.0559   0.2451   1.0000
  11.250   1.6114   0.02633   0.01874  -0.0551   0.2423   1.0000
  11.500   1.6281   0.02700   0.01952  -0.0542   0.2396   1.0000
  11.750   1.6440   0.02768   0.02028  -0.0533   0.2372   1.0000
  12.000   1.6582   0.02835   0.02099  -0.0521   0.2349   1.0000
  12.250   1.6720   0.02909   0.02174  -0.0509   0.2327   1.0000
  12.500   1.6772   0.03020   0.02304  -0.0492   0.2302   1.0000
  12.750   1.6833   0.03140   0.02440  -0.0479   0.2275   1.0000
  13.000   1.6893   0.03268   0.02580  -0.0468   0.2248   1.0000
  13.250   1.6965   0.03398   0.02718  -0.0460   0.2222   1.0000
  13.500   1.7055   0.03521   0.02844  -0.0453   0.2199   1.0000
  13.750   1.7098   0.03692   0.03027  -0.0447   0.2174   1.0000
  14.000   1.7085   0.03922   0.03277  -0.0444   0.2143   1.0000
  14.250   1.7083   0.04153   0.03523  -0.0442   0.2114   1.0000
  14.500   1.7095   0.04379   0.03758  -0.0442   0.2086   1.0000
  14.750   1.7147   0.04567   0.03949  -0.0441   0.2060   1.0000
  15.000   1.7102   0.04873   0.04270  -0.0444   0.2032   1.0000
  15.250   1.6991   0.05271   0.04688  -0.0453   0.1999   1.0000
  15.500   1.6903   0.05654   0.05085  -0.0462   0.1967   1.0000
  15.750   1.6881   0.05959   0.05396  -0.0468   0.1937   1.0000
  16.000   1.6875   0.06252   0.05694  -0.0474   0.1910   1.0000
  16.250   1.6597   0.06950   0.06417  -0.0500   0.1873   1.0000
  16.500   1.6385   0.07582   0.07064  -0.0525   0.1834   1.0000
  16.750   1.6377   0.07914   0.07400  -0.0536   0.1802   1.0000
  17.000   1.6204   0.08518   0.08016  -0.0560   0.1767   1.0000
  17.250   1.5672   0.09739   0.09260  -0.0615   0.1715   1.0000
  17.500   1.5672   0.10091   0.09617  -0.0629   0.1680   1.0000
  17.750   1.5590   0.10579   0.10111  -0.0650   0.1645   1.0000
  18.000   1.4832   0.12313   0.11866  -0.0736   0.1570   1.0000
  18.250   1.5095   0.12199   0.11752  -0.0728   0.1548   1.0000
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