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AH 79-100 B AIRFOIL (ah79100b-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: AH 79-100 B AIRFOIL (ah79100b-il)
Reynolds number: 1,000,000
Max Cl/Cd: 153.73 at α=2°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-ah79100b-il-1000000-n5.txt
Download as CSV file: xf-ah79100b-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: AH 79-100 B AIRFOIL                             
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.250  -0.2314   0.14510   0.14329  -0.0603   0.9923   0.0068
 -13.000  -0.2208   0.14135   0.13954  -0.0629   0.9911   0.0069
  -9.500  -0.1813   0.01870   0.01537  -0.1941   0.8528   0.0061
  -9.250  -0.1555   0.01659   0.01294  -0.1964   0.8414   0.0063
  -9.000  -0.1284   0.01521   0.01129  -0.1978   0.8316   0.0065
  -8.750  -0.1009   0.01417   0.01002  -0.1989   0.8231   0.0067
  -8.500  -0.0729   0.01334   0.00899  -0.1998   0.8157   0.0069
  -8.250  -0.0446   0.01259   0.00806  -0.2006   0.8095   0.0071
  -8.000  -0.0159   0.01195   0.00729  -0.2014   0.8036   0.0076
  -7.750   0.0124   0.01149   0.00673  -0.2019   0.7978   0.0080
  -7.500   0.0411   0.01108   0.00622  -0.2024   0.7926   0.0085
  -7.250   0.0699   0.01069   0.00573  -0.2029   0.7871   0.0092
  -7.000   0.0983   0.01037   0.00531  -0.2033   0.7813   0.0099
  -6.750   0.1267   0.01020   0.00511  -0.2036   0.7757   0.0108
  -6.500   0.1550   0.01001   0.00484  -0.2038   0.7696   0.0118
  -6.250   0.1834   0.00981   0.00455  -0.2041   0.7644   0.0125
  -6.000   0.2122   0.00963   0.00432  -0.2044   0.7596   0.0134
  -5.750   0.2404   0.00957   0.00424  -0.2046   0.7548   0.0143
  -5.250   0.2974   0.00934   0.00391  -0.2050   0.7465   0.0160
  -5.000   0.3261   0.00922   0.00372  -0.2053   0.7418   0.0164
  -4.750   0.3555   0.00888   0.00331  -0.2058   0.7369   0.0173
  -4.500   0.3843   0.00876   0.00317  -0.2061   0.7324   0.0182
  -4.250   0.4130   0.00866   0.00304  -0.2064   0.7276   0.0192
  -4.000   0.4418   0.00852   0.00285  -0.2067   0.7227   0.0200
  -3.750   0.4709   0.00835   0.00262  -0.2070   0.7176   0.0205
  -3.500   0.4997   0.00824   0.00245  -0.2073   0.7112   0.0211
  -3.250   0.5284   0.00810   0.00224  -0.2076   0.7053   0.0217
  -3.000   0.5581   0.00791   0.00202  -0.2081   0.7005   0.0227
  -2.750   0.5872   0.00781   0.00189  -0.2084   0.6960   0.0237
  -2.500   0.6159   0.00774   0.00178  -0.2086   0.6918   0.0248
  -2.250   0.6448   0.00767   0.00168  -0.2089   0.6875   0.0261
  -2.000   0.6735   0.00762   0.00160  -0.2091   0.6822   0.0274
  -1.750   0.7020   0.00756   0.00153  -0.2093   0.6765   0.0314
  -1.500   0.7307   0.00752   0.00148  -0.2095   0.6711   0.0355
  -1.250   0.7590   0.00749   0.00145  -0.2097   0.6640   0.0437
  -1.000   0.7874   0.00746   0.00142  -0.2098   0.6576   0.0558
  -0.750   0.8160   0.00742   0.00142  -0.2101   0.6514   0.0777
  -0.500   0.8444   0.00737   0.00142  -0.2103   0.6460   0.1126
  -0.250   0.8744   0.00720   0.00144  -0.2110   0.6407   0.2003
   0.000   0.9047   0.00696   0.00151  -0.2119   0.6345   0.3438
   0.250   0.9334   0.00691   0.00157  -0.2122   0.6290   0.4112
   0.500   0.9620   0.00688   0.00164  -0.2125   0.6226   0.4638
   0.750   0.9897   0.00691   0.00173  -0.2126   0.6151   0.5123
   1.000   1.0175   0.00694   0.00181  -0.2126   0.6059   0.5491
   1.250   1.0448   0.00701   0.00189  -0.2126   0.5967   0.5706
   1.750   1.0986   0.00721   0.00206  -0.2123   0.5767   0.5984
   2.000   1.1253   0.00732   0.00216  -0.2121   0.5658   0.6140
   2.250   1.1510   0.00749   0.00228  -0.2118   0.5483   0.6275
   2.500   1.1759   0.00772   0.00244  -0.2113   0.5257   0.6438
   2.750   1.2012   0.00793   0.00260  -0.2108   0.5070   0.6620
   3.000   1.2271   0.00809   0.00276  -0.2106   0.4938   0.6814
   3.250   1.2530   0.00826   0.00292  -0.2103   0.4811   0.7028
   3.500   1.2788   0.00842   0.00310  -0.2100   0.4682   0.7272
   3.750   1.3043   0.00860   0.00329  -0.2096   0.4546   0.7559
   4.250   1.3516   0.00906   0.00378  -0.2082   0.4141   0.8458
   4.500   1.3679   0.00922   0.00399  -0.2058   0.3905   1.0000
   4.750   1.3918   0.00954   0.00423  -0.2052   0.3735   1.0000
   5.000   1.4156   0.00985   0.00449  -0.2045   0.3564   1.0000
   5.250   1.4354   0.01045   0.00488  -0.2032   0.3197   1.0000
   5.500   1.4536   0.01117   0.00535  -0.2016   0.2753   1.0000
   5.750   1.4727   0.01179   0.00580  -0.2002   0.2428   1.0000
   6.000   1.4895   0.01255   0.00634  -0.1984   0.2046   1.0000
   6.250   1.5050   0.01338   0.00695  -0.1963   0.1642   1.0000
   6.500   1.5176   0.01437   0.00768  -0.1938   0.1197   1.0000
   6.750   1.5267   0.01543   0.00849  -0.1906   0.0760   1.0000
   7.000   1.5395   0.01617   0.00911  -0.1879   0.0562   1.0000
   7.250   1.5554   0.01671   0.00963  -0.1859   0.0482   1.0000
   7.500   1.5723   0.01719   0.01011  -0.1841   0.0435   1.0000
   7.750   1.5880   0.01775   0.01067  -0.1821   0.0386   1.0000
   8.000   1.6050   0.01824   0.01118  -0.1804   0.0351   1.0000
   8.250   1.6177   0.01899   0.01189  -0.1780   0.0259   1.0000
   8.500   1.6296   0.01982   0.01268  -0.1755   0.0186   1.0000
   8.750   1.6426   0.02060   0.01346  -0.1733   0.0143   1.0000
   9.000   1.6547   0.02144   0.01432  -0.1710   0.0109   1.0000
   9.250   1.6666   0.02233   0.01523  -0.1688   0.0089   1.0000
   9.500   1.6794   0.02318   0.01612  -0.1668   0.0080   1.0000
   9.750   1.6913   0.02412   0.01710  -0.1647   0.0074   1.0000
  10.000   1.7021   0.02517   0.01819  -0.1626   0.0067   1.0000
  10.250   1.7131   0.02623   0.01930  -0.1605   0.0063   1.0000
  10.500   1.7243   0.02731   0.02046  -0.1587   0.0060   1.0000
  10.750   1.7349   0.02848   0.02169  -0.1568   0.0057   1.0000
  11.000   1.7445   0.02976   0.02303  -0.1549   0.0055   1.0000
  11.250   1.7536   0.03113   0.02446  -0.1530   0.0052   1.0000
  11.500   1.7617   0.03264   0.02603  -0.1512   0.0050   1.0000
  11.750   1.7689   0.03427   0.02773  -0.1494   0.0048   1.0000
  12.000   1.7743   0.03613   0.02967  -0.1475   0.0046   1.0000
  12.250   1.7788   0.03815   0.03178  -0.1457   0.0044   1.0000
  12.500   1.7862   0.03991   0.03362  -0.1442   0.0043   1.0000
  12.750   1.7922   0.04187   0.03567  -0.1428   0.0042   1.0000
  13.000   1.7978   0.04391   0.03779  -0.1414   0.0041   1.0000
  13.250   1.8029   0.04608   0.04004  -0.1401   0.0040   1.0000
  13.500   1.8070   0.04843   0.04248  -0.1389   0.0039   1.0000
  13.750   1.8108   0.05086   0.04500  -0.1378   0.0038   1.0000
  14.000   1.8147   0.05334   0.04757  -0.1368   0.0037   1.0000
  14.250   1.8169   0.05610   0.05043  -0.1359   0.0036   1.0000
  14.500   1.8198   0.05884   0.05325  -0.1351   0.0035   1.0000
  14.750   1.8228   0.06160   0.05610  -0.1344   0.0033   1.0000
  15.000   1.8235   0.06479   0.05939  -0.1338   0.0033   1.0000
  15.250   1.8237   0.06810   0.06278  -0.1334   0.0032   1.0000
  15.500   1.8230   0.07159   0.06637  -0.1331   0.0031   1.0000
  15.750   1.8188   0.07573   0.07062  -0.1329   0.0030   1.0000
  16.000   1.8158   0.07979   0.07479  -0.1330   0.0029   1.0000
  16.250   1.8077   0.08476   0.07989  -0.1332   0.0028   1.0000
  16.500   1.8047   0.08898   0.08422  -0.1336   0.0028   1.0000
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