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AH 79-100 C AIRFOIL (ah79100c-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: AH 79-100 C AIRFOIL (ah79100c-il)
Reynolds number: 200,000
Max Cl/Cd: 97.57 at α=6.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-ah79100c-il-200000.txt
Download as CSV file: xf-ah79100c-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: AH 79-100 C AIRFOIL                             
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.1622   0.10821   0.10476  -0.0708   0.9567   0.0354
  -8.000  -0.1585   0.10628   0.10284  -0.0776   0.9507   0.0381
  -7.750  -0.1563   0.10402   0.10061  -0.0815   0.9436   0.0384
  -7.500  -0.1426   0.09890   0.09550  -0.0850   0.9414   0.0389
  -7.250  -0.1357   0.09596   0.09256  -0.0824   0.9349   0.0394
  -7.000  -0.1177   0.09260   0.08919  -0.0834   0.9319   0.0405
  -6.750  -0.1009   0.08940   0.08598  -0.0864   0.9293   0.0419
  -6.500  -0.1054   0.08775   0.08436  -0.0848   0.9201   0.0425
  -6.250  -0.0887   0.08418   0.08077  -0.0894   0.9165   0.0444
  -6.000  -0.0869   0.08164   0.07826  -0.0915   0.9067   0.0461
  -5.750  -0.0413   0.07472   0.07124  -0.1142   0.9018   0.0478
  -5.500  -0.0493   0.07150   0.06807  -0.1107   0.8926   0.0484
  -5.250  -0.0361   0.06893   0.06550  -0.1082   0.8902   0.0496
  -5.000  -0.0096   0.06569   0.06223  -0.1114   0.8884   0.0517
  -4.750  -0.0017   0.06332   0.05985  -0.1126   0.8799   0.0539
  -4.500   0.0617   0.05333   0.04955  -0.1351   0.8763   0.0601
  -4.250   0.0818   0.05186   0.04814  -0.1338   0.8745   0.0627
  -4.000   0.1375   0.04556   0.04154  -0.1465   0.8735   0.0748
  -3.750   0.1454   0.04457   0.04055  -0.1444   0.8651   0.0780
  -3.500   0.1899   0.04063   0.03637  -0.1514   0.8629   0.0921
  -3.250   0.2818   0.02846   0.02268  -0.1693   0.8651   0.0641
  -3.000   0.3286   0.02544   0.01896  -0.1736   0.8639   0.0627
  -2.750   0.3705   0.02358   0.01664  -0.1764   0.8626   0.0621
  -2.500   0.4103   0.02232   0.01516  -0.1787   0.8613   0.0639
  -2.250   0.4501   0.02131   0.01400  -0.1810   0.8602   0.0675
  -2.000   0.4907   0.02044   0.01295  -0.1831   0.8592   0.0719
  -1.750   0.5325   0.01920   0.01175  -0.1859   0.8586   0.0803
  -1.500   0.5757   0.01829   0.01085  -0.1889   0.8579   0.0969
  -1.250   0.5860   0.01858   0.01118  -0.1858   0.8483   0.1116
  -1.000   0.6269   0.01783   0.01060  -0.1884   0.8468   0.1608
  -0.750   0.6705   0.01694   0.01015  -0.1918   0.8457   0.2842
  -0.500   0.7147   0.01620   0.00977  -0.1951   0.8446   0.4179
  -0.250   0.7559   0.01523   0.00954  -0.1977   0.8436   0.6718
   0.500   0.8405   0.01451   0.00895  -0.1968   0.8298   1.0000
   0.750   0.8862   0.01416   0.00848  -0.2003   0.8280   1.0000
   1.000   0.8980   0.01460   0.00887  -0.1971   0.8187   1.0000
   1.250   0.9391   0.01435   0.00853  -0.1997   0.8157   1.0000
   1.500   0.9830   0.01408   0.00817  -0.2028   0.8131   1.0000
   1.750   0.9980   0.01441   0.00849  -0.2002   0.8041   1.0000
   2.000   1.0382   0.01417   0.00818  -0.2025   0.8000   1.0000
   2.250   1.0659   0.01425   0.00824  -0.2025   0.7937   1.0000
   2.500   1.0943   0.01430   0.00828  -0.2026   0.7872   1.0000
   2.750   1.1364   0.01407   0.00798  -0.2053   0.7829   1.0000
   3.000   1.1534   0.01431   0.00825  -0.2030   0.7735   1.0000
   3.250   1.1930   0.01412   0.00802  -0.2052   0.7680   1.0000
   3.500   1.2111   0.01436   0.00830  -0.2032   0.7590   1.0000
   3.750   1.2484   0.01424   0.00814  -0.2050   0.7529   1.0000
   4.000   1.2667   0.01442   0.00837  -0.2030   0.7430   1.0000
   4.250   1.3001   0.01436   0.00830  -0.2039   0.7353   1.0000
   4.500   1.3217   0.01447   0.00845  -0.2025   0.7252   1.0000
   4.750   1.3447   0.01455   0.00856  -0.2014   0.7147   1.0000
   5.000   1.3744   0.01453   0.00854  -0.2016   0.7049   1.0000
   5.250   1.3950   0.01465   0.00872  -0.2000   0.6937   1.0000
   5.500   1.4154   0.01481   0.00893  -0.1984   0.6826   1.0000
   5.750   1.4383   0.01492   0.00907  -0.1973   0.6709   1.0000
   6.000   1.4602   0.01502   0.00921  -0.1959   0.6579   1.0000
   6.250   1.4791   0.01516   0.00938  -0.1940   0.6432   1.0000
   6.500   1.4946   0.01533   0.00959  -0.1913   0.6265   1.0000
   6.750   1.5072   0.01553   0.00980  -0.1881   0.6072   1.0000
   7.000   1.5196   0.01577   0.01001  -0.1848   0.5861   1.0000
   7.250   1.5269   0.01613   0.01034  -0.1806   0.5610   1.0000
   7.500   1.5333   0.01661   0.01071  -0.1763   0.5316   1.0000
   7.750   1.5376   0.01726   0.01122  -0.1718   0.4987   1.0000
   8.000   1.5412   0.01807   0.01186  -0.1674   0.4658   1.0000
   8.250   1.5421   0.01907   0.01268  -0.1626   0.4307   1.0000
   8.500   1.5432   0.02015   0.01362  -0.1581   0.3964   1.0000
   8.750   1.5448   0.02132   0.01466  -0.1539   0.3647   1.0000
   9.000   1.5466   0.02258   0.01579  -0.1500   0.3342   1.0000
   9.250   1.5479   0.02395   0.01705  -0.1462   0.3041   1.0000
   9.500   1.5477   0.02551   0.01848  -0.1423   0.2706   1.0000
   9.750   1.5462   0.02728   0.02008  -0.1385   0.2367   1.0000
  10.000   1.5424   0.02936   0.02196  -0.1347   0.1956   1.0000
  10.250   1.5330   0.03205   0.02430  -0.1306   0.1427   1.0000
  10.500   1.5136   0.03587   0.02754  -0.1259   0.0725   1.0000
  10.750   1.5021   0.03927   0.03067  -0.1222   0.0429   1.0000
  11.000   1.5020   0.04176   0.03322  -0.1197   0.0359   1.0000
  11.250   1.4999   0.04451   0.03603  -0.1173   0.0323   1.0000
  11.500   1.5034   0.04676   0.03842  -0.1154   0.0303   1.0000
  11.750   1.5055   0.04921   0.04099  -0.1137   0.0284   1.0000
  12.000   1.5047   0.05205   0.04393  -0.1120   0.0271   1.0000
  12.250   1.5002   0.05538   0.04737  -0.1103   0.0262   1.0000
  12.500   1.4980   0.05858   0.05068  -0.1087   0.0257   1.0000
  12.750   1.4993   0.06146   0.05368  -0.1075   0.0252   1.0000
  13.000   1.5012   0.06434   0.05668  -0.1063   0.0247   1.0000
  13.250   1.5039   0.06715   0.05961  -0.1052   0.0242   1.0000
  13.500   1.5081   0.06986   0.06242  -0.1041   0.0237   1.0000
  13.750   1.5144   0.07236   0.06502  -0.1031   0.0233   1.0000
  14.000   1.5227   0.07466   0.06743  -0.1021   0.0229   1.0000
  14.250   1.5334   0.07675   0.06962  -0.1010   0.0226   1.0000
  14.500   1.5460   0.07874   0.07173  -0.0999   0.0224   1.0000
  14.750   1.5582   0.08086   0.07398  -0.0990   0.0221   1.0000
  15.000   1.5688   0.08320   0.07643  -0.0983   0.0216   1.0000
  15.250   1.5829   0.08544   0.07876  -0.0975   0.0210   1.0000
  15.500   1.5981   0.08817   0.08169  -0.0967   0.0207   1.0000
  15.750   1.6020   0.09164   0.08541  -0.0962   0.0207   1.0000
  16.000   1.6012   0.09550   0.08952  -0.0959   0.0207   1.0000
  16.250   1.5960   0.09964   0.09392  -0.0959   0.0209   1.0000
  16.500   1.5881   0.10418   0.09874  -0.0963   0.0210   1.0000
  16.750   1.5764   0.10926   0.10412  -0.0972   0.0211   1.0000
  17.000   1.5618   0.11501   0.11019  -0.0986   0.0214   1.0000
  17.250   1.5389   0.12232   0.11789  -0.1012   0.0218   1.0000
  17.500   1.5106   0.13106   0.12702  -0.1053   0.0224   1.0000
  17.750   1.4868   0.13960   0.13587  -0.1098   0.0228   1.0000
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