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MH 84 13.69% (mh84-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: MH 84 13.69% (mh84-il)
Reynolds number: 500,000
Max Cl/Cd: 92.34 at α=7°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-mh84-il-500000.txt
Download as CSV file: xf-mh84-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 84  13.69%                                   
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.2667   0.08674   0.08398  -0.0196   0.7538   0.0282
  -8.250  -0.2598   0.08402   0.08120  -0.0205   0.7400   0.0283
  -8.000  -0.4322   0.03226   0.02830  -0.0666   0.7481   0.0177
  -7.750  -0.4146   0.02880   0.02448  -0.0685   0.7364   0.0176
  -7.500  -0.3933   0.02597   0.02127  -0.0697   0.7244   0.0175
  -7.250  -0.3695   0.02370   0.01866  -0.0704   0.7131   0.0174
  -7.000  -0.3443   0.02188   0.01651  -0.0708   0.7015   0.0174
  -6.750  -0.3178   0.02038   0.01475  -0.0710   0.6900   0.0174
  -6.500  -0.2906   0.01928   0.01337  -0.0711   0.6789   0.0176
  -6.250  -0.2624   0.01845   0.01230  -0.0711   0.6672   0.0179
  -6.000  -0.2351   0.01724   0.01091  -0.0711   0.6565   0.0181
  -5.750  -0.2075   0.01626   0.00984  -0.0710   0.6451   0.0184
  -5.500  -0.1793   0.01552   0.00900  -0.0709   0.6344   0.0187
  -5.250  -0.1510   0.01488   0.00826  -0.0708   0.6233   0.0189
  -5.000  -0.1223   0.01430   0.00760  -0.0707   0.6126   0.0193
  -4.750  -0.0936   0.01380   0.00699  -0.0706   0.6017   0.0198
  -4.500  -0.0646   0.01331   0.00642  -0.0705   0.5911   0.0204
  -4.000  -0.0065   0.01236   0.00534  -0.0704   0.5700   0.0223
  -3.750   0.0227   0.01206   0.00494  -0.0703   0.5597   0.0238
  -3.500   0.0521   0.01166   0.00451  -0.0703   0.5491   0.0259
  -3.250   0.0815   0.01135   0.00412  -0.0702   0.5391   0.0296
  -3.000   0.1110   0.01100   0.00376  -0.0702   0.5285   0.0370
  -2.750   0.1403   0.01061   0.00344  -0.0702   0.5188   0.0597
  -2.500   0.1695   0.01035   0.00327  -0.0702   0.5085   0.0906
  -2.250   0.1988   0.01020   0.00316  -0.0702   0.4989   0.1144
  -2.000   0.2280   0.01009   0.00308  -0.0702   0.4889   0.1364
  -1.750   0.2573   0.01001   0.00302  -0.0701   0.4794   0.1581
  -1.500   0.2865   0.00997   0.00298  -0.0700   0.4694   0.1795
  -1.250   0.3158   0.00992   0.00296  -0.0700   0.4603   0.2017
  -1.000   0.3450   0.00990   0.00293  -0.0699   0.4506   0.2219
  -0.750   0.3742   0.00988   0.00292  -0.0699   0.4415   0.2420
  -0.500   0.4034   0.00988   0.00290  -0.0698   0.4324   0.2608
  -0.250   0.4326   0.00986   0.00290  -0.0697   0.4238   0.2802
   0.000   0.4617   0.00986   0.00290  -0.0697   0.4145   0.3016
   0.250   0.4908   0.00985   0.00291  -0.0696   0.4061   0.3268
   0.500   0.5198   0.00984   0.00294  -0.0696   0.3975   0.3576
   0.750   0.5487   0.00982   0.00299  -0.0695   0.3895   0.3981
   1.000   0.5776   0.00976   0.00305  -0.0695   0.3809   0.4515
   1.250   0.6060   0.00972   0.00314  -0.0694   0.3729   0.5205
   1.500   0.6343   0.00958   0.00324  -0.0693   0.3650   0.6084
   1.750   0.6610   0.00949   0.00337  -0.0688   0.3572   0.7142
   2.000   0.6868   0.00896   0.00339  -0.0676   0.3502   1.0000
   2.250   0.7157   0.00915   0.00346  -0.0676   0.3423   1.0000
   2.500   0.7447   0.00930   0.00355  -0.0676   0.3352   1.0000
   2.750   0.7734   0.00948   0.00364  -0.0675   0.3279   1.0000
   3.000   0.8020   0.00969   0.00376  -0.0675   0.3210   1.0000
   3.250   0.8307   0.00984   0.00387  -0.0674   0.3141   1.0000
   3.500   0.8589   0.01008   0.00401  -0.0674   0.3070   1.0000
   3.750   0.8875   0.01025   0.00415  -0.0673   0.3011   1.0000
   4.000   0.9158   0.01045   0.00429  -0.0672   0.2946   1.0000
   4.250   0.9436   0.01072   0.00447  -0.0671   0.2883   1.0000
   4.500   0.9720   0.01088   0.00462  -0.0671   0.2825   1.0000
   4.750   0.9998   0.01113   0.00480  -0.0670   0.2767   1.0000
   5.000   1.0274   0.01139   0.00502  -0.0668   0.2713   1.0000
   5.250   1.0554   0.01158   0.00520  -0.0668   0.2659   1.0000
   5.500   1.0828   0.01186   0.00541  -0.0666   0.2605   1.0000
   5.750   1.1099   0.01216   0.00567  -0.0665   0.2556   1.0000
   6.000   1.1376   0.01236   0.00588  -0.0664   0.2512   1.0000
   6.250   1.1646   0.01263   0.00612  -0.0662   0.2464   1.0000
   6.500   1.1907   0.01303   0.00643  -0.0660   0.2413   1.0000
   6.750   1.2181   0.01321   0.00666  -0.0659   0.2376   1.0000
   7.000   1.2448   0.01348   0.00692  -0.0657   0.2334   1.0000
   7.250   1.2707   0.01384   0.00723  -0.0654   0.2293   1.0000
   7.500   1.2963   0.01422   0.00759  -0.0652   0.2254   1.0000
   7.750   1.3229   0.01446   0.00787  -0.0650   0.2219   1.0000
   8.000   1.3488   0.01476   0.00817  -0.0648   0.2180   1.0000
   8.250   1.3736   0.01517   0.00853  -0.0644   0.2142   1.0000
   8.500   1.3980   0.01561   0.00896  -0.0641   0.2108   1.0000
   8.750   1.4236   0.01588   0.00929  -0.0638   0.2079   1.0000
   9.000   1.4484   0.01622   0.00965  -0.0635   0.2047   1.0000
   9.250   1.4722   0.01664   0.01006  -0.0630   0.2014   1.0000
   9.500   1.4938   0.01725   0.01061  -0.0624   0.1976   1.0000
   9.750   1.5181   0.01755   0.01099  -0.0620   0.1952   1.0000
  10.000   1.5415   0.01792   0.01141  -0.0616   0.1924   1.0000
  10.250   1.5638   0.01836   0.01186  -0.0610   0.1896   1.0000
  10.500   1.5843   0.01889   0.01239  -0.0602   0.1868   1.0000
  10.750   1.6021   0.01964   0.01311  -0.0592   0.1837   1.0000
  11.000   1.6233   0.02003   0.01359  -0.0586   0.1817   1.0000
  11.250   1.6429   0.02050   0.01412  -0.0577   0.1792   1.0000
  11.500   1.6604   0.02105   0.01471  -0.0567   0.1768   1.0000
  11.750   1.6725   0.02172   0.01540  -0.0549   0.1745   1.0000
  12.000   1.6811   0.02261   0.01629  -0.0530   0.1723   1.0000
  12.250   1.6902   0.02362   0.01733  -0.0514   0.1702   1.0000
  12.500   1.7028   0.02443   0.01824  -0.0503   0.1686   1.0000
  12.750   1.7145   0.02538   0.01927  -0.0492   0.1666   1.0000
  13.000   1.7254   0.02644   0.02040  -0.0483   0.1647   1.0000
  13.250   1.7350   0.02767   0.02167  -0.0475   0.1626   1.0000
  13.500   1.7426   0.02912   0.02313  -0.0467   0.1607   1.0000
  13.750   1.7485   0.03077   0.02477  -0.0458   0.1584   1.0000
  14.000   1.7577   0.03220   0.02631  -0.0453   0.1571   1.0000
  14.250   1.7663   0.03374   0.02795  -0.0449   0.1556   1.0000
  14.500   1.7738   0.03541   0.02971  -0.0446   0.1539   1.0000
  14.750   1.7804   0.03721   0.03158  -0.0443   0.1522   1.0000
  15.000   1.7858   0.03917   0.03361  -0.0442   0.1505   1.0000
  15.250   1.7897   0.04129   0.03575  -0.0441   0.1488   1.0000
  15.500   1.7938   0.04337   0.03784  -0.0438   0.1469   1.0000
  15.750   1.7980   0.04553   0.04008  -0.0437   0.1455   1.0000
  16.000   1.8006   0.04798   0.04265  -0.0440   0.1442   1.0000
  16.250   1.8027   0.05049   0.04527  -0.0443   0.1428   1.0000
  16.500   1.8046   0.05312   0.04800  -0.0447   0.1412   1.0000
  16.750   1.8061   0.05584   0.05079  -0.0452   0.1397   1.0000
  17.000   1.8069   0.05866   0.05367  -0.0458   0.1383   1.0000
  17.250   1.8089   0.06133   0.05636  -0.0462   0.1367   1.0000
  17.500   1.8143   0.06348   0.05851  -0.0463   0.1347   1.0000
  17.750   1.8113   0.06712   0.06230  -0.0475   0.1337   1.0000
  18.000   1.8082   0.07083   0.06615  -0.0488   0.1323   1.0000
  18.250   1.8052   0.07457   0.07000  -0.0501   0.1308   1.0000
  18.500   1.8031   0.07826   0.07378  -0.0515   0.1293   1.0000
  18.750   1.8015   0.08185   0.07744  -0.0528   0.1278   1.0000
  19.000   1.8012   0.08524   0.08086  -0.0541   0.1263   1.0000
  19.250   1.8089   0.08720   0.08280  -0.0544   0.1244   1.0000
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