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AH 79-100 C AIRFOIL (ah79100c-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: AH 79-100 C AIRFOIL (ah79100c-il)
Reynolds number: 500,000
Max Cl/Cd: 147.56 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-ah79100c-il-500000.txt
Download as CSV file: xf-ah79100c-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.0099   0.08652   0.08406  -0.1127   0.9537   0.0197
  -8.000  -0.0128   0.08229   0.07986  -0.1168   0.9444   0.0204
  -7.750   0.0013   0.07764   0.07521  -0.1212   0.9424   0.0206
  -7.500   0.0218   0.07518   0.07274  -0.1224   0.9416   0.0212
  -7.250   0.0229   0.07284   0.07042  -0.1220   0.9331   0.0212
  -7.000   0.0421   0.07059   0.06816  -0.1244   0.9309   0.0226
  -6.750   0.0615   0.06643   0.06399  -0.1300   0.9289   0.0239
  -6.500   0.0726   0.06071   0.05828  -0.1387   0.9187   0.0252
  -6.250   0.1117   0.02077   0.01688  -0.1889   0.9067   0.0164
  -6.000   0.1511   0.01797   0.01374  -0.1937   0.9051   0.0177
  -5.750   0.1927   0.01608   0.01138  -0.1976   0.9038   0.0203
  -5.500   0.2334   0.01526   0.01047  -0.2010   0.9024   0.0233
  -5.250   0.2760   0.01411   0.00903  -0.2048   0.9011   0.0264
  -5.000   0.2979   0.01399   0.00890  -0.2037   0.8938   0.0280
  -4.750   0.3345   0.01391   0.00869  -0.2056   0.8906   0.0308
  -4.500   0.3737   0.01324   0.00796  -0.2086   0.8880   0.0339
  -4.250   0.4029   0.01291   0.00754  -0.2091   0.8823   0.0359
  -4.000   0.4345   0.01213   0.00659  -0.2100   0.8771   0.0367
  -3.750   0.4716   0.01157   0.00588  -0.2121   0.8735   0.0379
  -3.500   0.4998   0.01115   0.00535  -0.2122   0.8674   0.0384
  -3.250   0.5302   0.01029   0.00440  -0.2130   0.8618   0.0400
  -3.000   0.5662   0.00987   0.00392  -0.2149   0.8578   0.0421
  -2.750   0.5910   0.00965   0.00368  -0.2143   0.8509   0.0446
  -2.500   0.6219   0.00947   0.00341  -0.2150   0.8456   0.0478
  -2.250   0.6530   0.00916   0.00309  -0.2158   0.8403   0.0580
  -2.000   0.6796   0.00897   0.00290  -0.2156   0.8338   0.0711
  -1.750   0.7117   0.00879   0.00272  -0.2166   0.8288   0.0907
  -1.500   0.7378   0.00864   0.00267  -0.2164   0.8223   0.1263
  -1.250   0.7662   0.00849   0.00264  -0.2167   0.8163   0.1852
  -1.000   0.7960   0.00837   0.00265  -0.2173   0.8109   0.2480
  -0.750   0.8214   0.00826   0.00269  -0.2169   0.8042   0.3142
  -0.500   0.8516   0.00817   0.00270  -0.2175   0.7986   0.3851
  -0.250   0.8770   0.00805   0.00277  -0.2172   0.7921   0.4664
   0.000   0.9040   0.00784   0.00288  -0.2172   0.7862   0.6041
   0.250   0.9284   0.00757   0.00304  -0.2164   0.7808   0.7921
   0.500   0.9449   0.00729   0.00302  -0.2135   0.7739   1.0000
   0.750   0.9742   0.00739   0.00301  -0.2138   0.7681   1.0000
   1.000   0.9992   0.00748   0.00306  -0.2132   0.7616   1.0000
   1.250   1.0261   0.00757   0.00310  -0.2131   0.7556   1.0000
   1.500   1.0533   0.00768   0.00315  -0.2130   0.7494   1.0000
   1.750   1.0780   0.00777   0.00321  -0.2123   0.7423   1.0000
   2.000   1.1060   0.00789   0.00326  -0.2124   0.7360   1.0000
   2.250   1.1295   0.00798   0.00336  -0.2115   0.7289   1.0000
   2.500   1.1568   0.00810   0.00342  -0.2115   0.7226   1.0000
   2.750   1.1801   0.00820   0.00353  -0.2105   0.7148   1.0000
   3.000   1.2058   0.00833   0.00360  -0.2101   0.7069   1.0000
   3.250   1.2280   0.00843   0.00372  -0.2090   0.6983   1.0000
   3.500   1.2528   0.00857   0.00381  -0.2083   0.6899   1.0000
   3.750   1.2747   0.00868   0.00394  -0.2071   0.6804   1.0000
   4.000   1.2981   0.00881   0.00407  -0.2062   0.6719   1.0000
   4.250   1.3209   0.00896   0.00421  -0.2052   0.6630   1.0000
   4.500   1.3428   0.00910   0.00436  -0.2040   0.6534   1.0000
   4.750   1.3640   0.00926   0.00451  -0.2027   0.6427   1.0000
   5.000   1.3814   0.00944   0.00467  -0.2005   0.6287   1.0000
   5.250   1.3966   0.00965   0.00485  -0.1978   0.6115   1.0000
   5.500   1.4112   0.00991   0.00506  -0.1951   0.5918   1.0000
   5.750   1.4251   0.01024   0.00532  -0.1922   0.5704   1.0000
   6.000   1.4357   0.01067   0.00564  -0.1888   0.5412   1.0000
   6.250   1.4443   0.01124   0.00605  -0.1850   0.5085   1.0000
   6.500   1.4525   0.01189   0.00654  -0.1813   0.4727   1.0000
   6.750   1.4613   0.01261   0.00708  -0.1778   0.4383   1.0000
   7.000   1.4708   0.01333   0.00767  -0.1745   0.4071   1.0000
   7.250   1.4818   0.01405   0.00827  -0.1716   0.3789   1.0000
   7.500   1.4912   0.01487   0.00894  -0.1684   0.3478   1.0000
   7.750   1.4972   0.01590   0.00977  -0.1648   0.3099   1.0000
   8.000   1.5063   0.01682   0.01054  -0.1619   0.2796   1.0000
   8.250   1.5137   0.01788   0.01144  -0.1587   0.2459   1.0000
   8.500   1.5200   0.01904   0.01243  -0.1555   0.2112   1.0000
   8.750   1.5233   0.02046   0.01361  -0.1520   0.1710   1.0000
   9.000   1.5214   0.02230   0.01512  -0.1478   0.1207   1.0000
   9.250   1.5118   0.02480   0.01719  -0.1429   0.0609   1.0000
   9.500   1.5040   0.02734   0.01943  -0.1384   0.0222   1.0000
   9.750   1.5127   0.02869   0.02083  -0.1361   0.0183   1.0000
  10.000   1.5207   0.03012   0.02232  -0.1338   0.0165   1.0000
  10.250   1.5290   0.03155   0.02385  -0.1317   0.0156   1.0000
  10.500   1.5387   0.03290   0.02530  -0.1298   0.0149   1.0000
  10.750   1.5472   0.03438   0.02686  -0.1278   0.0144   1.0000
  11.000   1.5547   0.03599   0.02856  -0.1259   0.0139   1.0000
  11.250   1.5606   0.03778   0.03044  -0.1239   0.0134   1.0000
  11.500   1.5658   0.03970   0.03246  -0.1220   0.0132   1.0000
  11.750   1.5682   0.04195   0.03479  -0.1200   0.0128   1.0000
  12.000   1.5680   0.04453   0.03747  -0.1180   0.0126   1.0000
  12.250   1.5656   0.04744   0.04049  -0.1159   0.0124   1.0000
  12.500   1.5629   0.05049   0.04365  -0.1141   0.0122   1.0000
  12.750   1.5667   0.05291   0.04617  -0.1128   0.0121   1.0000
  13.000   1.5705   0.05535   0.04872  -0.1116   0.0119   1.0000
  13.250   1.5732   0.05802   0.05149  -0.1105   0.0117   1.0000
  13.500   1.5758   0.06075   0.05434  -0.1095   0.0115   1.0000
  13.750   1.5775   0.06366   0.05735  -0.1085   0.0113   1.0000
  14.000   1.5790   0.06664   0.06044  -0.1076   0.0112   1.0000
  14.250   1.5806   0.06968   0.06358  -0.1069   0.0111   1.0000
  14.500   1.5827   0.07270   0.06670  -0.1062   0.0110   1.0000
  14.750   1.5851   0.07572   0.06983  -0.1056   0.0109   1.0000
  15.000   1.5880   0.07873   0.07295  -0.1051   0.0108   1.0000
  15.250   1.5912   0.08171   0.07603  -0.1046   0.0107   1.0000
  15.500   1.5945   0.08471   0.07915  -0.1042   0.0106   1.0000
  15.750   1.5981   0.08770   0.08226  -0.1039   0.0105   1.0000
  16.000   1.6016   0.09075   0.08542  -0.1037   0.0104   1.0000
  16.250   1.6048   0.09387   0.08867  -0.1035   0.0104   1.0000
  16.500   1.6072   0.09711   0.09205  -0.1035   0.0103   1.0000
  16.750   1.6087   0.10053   0.09561  -0.1036   0.0102   1.0000
  17.000   1.6089   0.10416   0.09939  -0.1039   0.0101   1.0000
  17.250   1.6077   0.10802   0.10337  -0.1046   0.0100   1.0000
  17.500   1.6058   0.11200   0.10750  -0.1055   0.0099   1.0000
  17.750   1.6033   0.11609   0.11172  -0.1065   0.0098   1.0000
  18.000   1.5996   0.12045   0.11623  -0.1078   0.0097   1.0000
  18.250   1.5954   0.12489   0.12081  -0.1092   0.0096   1.0000
  18.500   1.5883   0.12997   0.12607  -0.1112   0.0096   1.0000
  18.750   1.5793   0.13557   0.13187  -0.1138   0.0096   1.0000
  19.000   1.5688   0.14158   0.13808  -0.1169   0.0097   1.0000
  19.250   1.5545   0.14860   0.14533  -0.1208   0.0098   1.0000
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