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MH 117 9.8% (mh117-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: MH 117 9.8% (mh117-il)
Reynolds number: 500,000
Max Cl/Cd: 102.92 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-mh117-il-500000.txt
Download as CSV file: xf-mh117-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 117  9.8%                                    
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.5145   0.06801   0.06583  -0.0403   1.0000   0.0084
  -9.000  -0.5692   0.04767   0.04545  -0.0559   1.0000   0.0080
  -8.750  -0.5941   0.04046   0.03792  -0.0598   1.0000   0.0080
  -8.500  -0.6053   0.03621   0.03341  -0.0591   1.0000   0.0078
  -8.250  -0.6153   0.03204   0.02889  -0.0570   1.0000   0.0075
  -8.000  -0.6053   0.02680   0.02303  -0.0582   0.9976   0.0074
  -7.750  -0.5747   0.02284   0.01851  -0.0613   0.9940   0.0074
  -7.500  -0.5436   0.02050   0.01579  -0.0631   0.9898   0.0077
  -7.250  -0.5099   0.01873   0.01373  -0.0651   0.9860   0.0081
  -7.000  -0.4741   0.01739   0.01214  -0.0672   0.9832   0.0084
  -6.750  -0.4425   0.01578   0.01031  -0.0685   0.9782   0.0087
  -6.500  -0.4099   0.01414   0.00851  -0.0701   0.9734   0.0095
  -6.250  -0.3733   0.01338   0.00769  -0.0722   0.9704   0.0105
  -6.000  -0.3407   0.01278   0.00702  -0.0733   0.9641   0.0119
  -5.750  -0.3077   0.01179   0.00588  -0.0744   0.9577   0.0133
  -5.500  -0.2763   0.01098   0.00497  -0.0751   0.9496   0.0177
  -5.250  -0.2447   0.01003   0.00414  -0.0759   0.9417   0.0471
  -5.000  -0.2157   0.00969   0.00386  -0.0762   0.9307   0.0651
  -4.750  -0.1869   0.00945   0.00362  -0.0763   0.9194   0.0797
  -4.500  -0.1590   0.00924   0.00339  -0.0762   0.9078   0.0940
  -4.250  -0.1317   0.00904   0.00316  -0.0760   0.8961   0.1093
  -3.750  -0.0783   0.00861   0.00272  -0.0753   0.8723   0.1443
  -3.500  -0.0515   0.00843   0.00255  -0.0750   0.8607   0.1667
  -3.250  -0.0247   0.00823   0.00238  -0.0747   0.8497   0.1924
  -3.000   0.0022   0.00807   0.00224  -0.0744   0.8392   0.2215
  -2.750   0.0291   0.00790   0.00212  -0.0742   0.8287   0.2535
  -2.500   0.0561   0.00774   0.00202  -0.0740   0.8181   0.2864
  -2.250   0.0831   0.00759   0.00193  -0.0738   0.8081   0.3245
  -2.000   0.1100   0.00745   0.00185  -0.0735   0.7987   0.3675
  -1.750   0.1369   0.00728   0.00179  -0.0733   0.7883   0.4125
  -1.500   0.1638   0.00711   0.00175  -0.0731   0.7785   0.4666
  -1.250   0.1904   0.00696   0.00171  -0.0727   0.7690   0.5228
  -1.000   0.2168   0.00678   0.00170  -0.0724   0.7588   0.5861
  -0.750   0.2428   0.00660   0.00170  -0.0719   0.7487   0.6550
  -0.500   0.2682   0.00644   0.00171  -0.0712   0.7392   0.7238
  -0.250   0.2927   0.00629   0.00174  -0.0701   0.7296   0.7918
   0.000   0.3160   0.00616   0.00178  -0.0688   0.7196   0.8582
   0.250   0.3403   0.00609   0.00179  -0.0674   0.7103   0.9191
   0.500   0.3774   0.00609   0.00176  -0.0691   0.7005   0.9674
   0.750   0.4216   0.00609   0.00172  -0.0726   0.6895   0.9958
   1.000   0.4507   0.00615   0.00172  -0.0728   0.6791   1.0000
   1.250   0.4763   0.00624   0.00173  -0.0723   0.6689   1.0000
   1.500   0.5021   0.00632   0.00175  -0.0718   0.6583   1.0000
   1.750   0.5284   0.00640   0.00179  -0.0714   0.6470   1.0000
   2.000   0.5547   0.00648   0.00184  -0.0710   0.6356   1.0000
   2.250   0.5811   0.00658   0.00189  -0.0706   0.6241   1.0000
   2.500   0.6075   0.00668   0.00195  -0.0703   0.6120   1.0000
   2.750   0.6340   0.00679   0.00201  -0.0699   0.5992   1.0000
   3.000   0.6604   0.00690   0.00209  -0.0696   0.5857   1.0000
   3.250   0.6868   0.00701   0.00218  -0.0692   0.5704   1.0000
   3.500   0.7131   0.00714   0.00227  -0.0689   0.5540   1.0000
   3.750   0.7393   0.00729   0.00239  -0.0685   0.5355   1.0000
   4.000   0.7650   0.00747   0.00250  -0.0680   0.5141   1.0000
   4.250   0.7904   0.00768   0.00263  -0.0675   0.4891   1.0000
   4.500   0.8154   0.00793   0.00279  -0.0670   0.4598   1.0000
   4.750   0.8399   0.00824   0.00299  -0.0664   0.4245   1.0000
   5.000   0.8637   0.00862   0.00322  -0.0657   0.3877   1.0000
   5.250   0.8876   0.00902   0.00348  -0.0651   0.3527   1.0000
   5.500   0.9109   0.00947   0.00378  -0.0644   0.3165   1.0000
   5.750   0.9342   0.00994   0.00412  -0.0637   0.2814   1.0000
   6.000   0.9576   0.01040   0.00445  -0.0630   0.2511   1.0000
   6.500   1.0033   0.01140   0.00520  -0.0616   0.1923   1.0000
   6.750   1.0261   0.01190   0.00560  -0.0609   0.1670   1.0000
   7.000   1.0486   0.01242   0.00602  -0.0602   0.1430   1.0000
   7.250   1.0707   0.01297   0.00649  -0.0594   0.1218   1.0000
   7.500   1.0926   0.01352   0.00697  -0.0585   0.1030   1.0000
   7.750   1.1139   0.01412   0.00750  -0.0576   0.0874   1.0000
   8.000   1.1354   0.01468   0.00804  -0.0567   0.0760   1.0000
   8.250   1.1568   0.01524   0.00860  -0.0558   0.0668   1.0000
   8.500   1.1772   0.01586   0.00921  -0.0547   0.0585   1.0000
   8.750   1.1974   0.01648   0.00982  -0.0537   0.0509   1.0000
   9.000   1.2184   0.01699   0.01039  -0.0527   0.0452   1.0000
   9.250   1.2361   0.01776   0.01113  -0.0513   0.0384   1.0000
   9.500   1.2576   0.01817   0.01160  -0.0505   0.0343   1.0000
   9.750   1.2741   0.01897   0.01237  -0.0490   0.0286   1.0000
  10.000   1.2941   0.01944   0.01291  -0.0480   0.0252   1.0000
  10.250   1.3076   0.02038   0.01383  -0.0461   0.0201   1.0000
  10.500   1.3245   0.02095   0.01444  -0.0446   0.0164   1.0000
  10.750   1.3341   0.02190   0.01543  -0.0420   0.0123   1.0000
  11.000   1.3378   0.02325   0.01682  -0.0388   0.0089   1.0000
  11.250   1.3486   0.02413   0.01776  -0.0367   0.0074   1.0000
  11.500   1.3497   0.02573   0.01944  -0.0337   0.0063   1.0000
  11.750   1.3538   0.02717   0.02102  -0.0313   0.0058   1.0000
  12.000   1.3591   0.02859   0.02256  -0.0293   0.0053   1.0000
  12.250   1.3625   0.03024   0.02432  -0.0274   0.0049   1.0000
  12.500   1.3668   0.03189   0.02608  -0.0258   0.0046   1.0000
  12.750   1.3688   0.03385   0.02815  -0.0244   0.0045   1.0000
  13.000   1.3668   0.03629   0.03071  -0.0231   0.0042   1.0000
  13.250   1.3542   0.03999   0.03458  -0.0220   0.0040   1.0000
  13.500   1.3431   0.04380   0.03856  -0.0214   0.0039   1.0000
  13.750   1.3370   0.04730   0.04219  -0.0214   0.0038   1.0000
  14.000   1.3395   0.04995   0.04498  -0.0215   0.0037   1.0000
  14.250   1.3317   0.05398   0.04919  -0.0221   0.0037   1.0000
  14.500   1.3259   0.05797   0.05333  -0.0230   0.0036   1.0000
  14.750   1.3176   0.06253   0.05806  -0.0243   0.0035   1.0000
  15.000   1.3096   0.06727   0.06293  -0.0260   0.0035   1.0000
  15.250   1.2983   0.07283   0.06866  -0.0282   0.0034   1.0000
  15.500   1.2867   0.07872   0.07471  -0.0308   0.0034   1.0000
  15.750   1.2747   0.08497   0.08112  -0.0338   0.0034   1.0000
  16.000   1.2631   0.09149   0.08778  -0.0372   0.0033   1.0000
  16.250   1.2489   0.09876   0.09520  -0.0410   0.0032   1.0000
  16.500   1.2343   0.10631   0.10291  -0.0451   0.0033   1.0000
  16.750   1.2195   0.11423   0.11098  -0.0495   0.0032   1.0000
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