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


Details Polar file
Airfoil: AH 79-100 B AIRFOIL (ah79100b-il)
Reynolds number: 100,000
Max Cl/Cd: 68.77 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-ah79100b-il-100000-n5.txt
Download as CSV file: xf-ah79100b-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.1454   0.10385   0.09901  -0.0757   0.9507   0.0455
  -8.000  -0.1352   0.10107   0.09623  -0.0808   0.9432   0.0458
  -7.750  -0.1300   0.09872   0.09391  -0.0848   0.9332   0.0461
  -7.500  -0.1095   0.09279   0.08797  -0.0839   0.9319   0.0473
  -7.250  -0.0898   0.08904   0.08420  -0.0856   0.9287   0.0487
  -7.000  -0.0795   0.08622   0.08138  -0.0868   0.9211   0.0501
  -6.750  -0.0657   0.08307   0.07823  -0.0897   0.9152   0.0514
  -6.500  -0.0560   0.08022   0.07539  -0.0919   0.9071   0.0521
  -6.250  -0.0384   0.07650   0.07165  -0.0967   0.9012   0.0535
  -5.750   0.0048   0.06391   0.05893  -0.1172   0.8858   0.0352
  -5.500   0.0216   0.06025   0.05524  -0.1207   0.8789   0.0347
  -5.250   0.0603   0.05283   0.04764  -0.1347   0.8732   0.0351
  -5.000   0.1132   0.04454   0.03887  -0.1503   0.8703   0.0356
  -4.750   0.1477   0.03938   0.03333  -0.1575   0.8642   0.0355
  -4.500   0.1835   0.03591   0.02968  -0.1629   0.8601   0.0373
  -4.250   0.2275   0.03304   0.02647  -0.1689   0.8575   0.0408
  -4.000   0.2821   0.02875   0.02144  -0.1769   0.8558   0.0419
  -3.750   0.3232   0.02649   0.01849  -0.1808   0.8512   0.0453
  -3.500   0.3607   0.02461   0.01611  -0.1834   0.8463   0.0465
  -3.250   0.3997   0.02292   0.01418  -0.1862   0.8429   0.0482
  -3.000   0.4387   0.02186   0.01292  -0.1886   0.8402   0.0520
  -2.750   0.4653   0.02127   0.01217  -0.1886   0.8336   0.0553
  -2.500   0.4990   0.02047   0.01119  -0.1897   0.8294   0.0576
  -2.250   0.5355   0.01959   0.01027  -0.1915   0.8262   0.0611
  -2.000   0.5639   0.01926   0.00994  -0.1919   0.8205   0.0677
  -1.750   0.5957   0.01885   0.00947  -0.1929   0.8155   0.0761
  -1.500   0.6323   0.01836   0.00893  -0.1947   0.8118   0.0913
  -1.250   0.6641   0.01796   0.00864  -0.1958   0.8060   0.1314
  -1.000   0.7005   0.01707   0.00869  -0.1984   0.8005   0.4243
  -0.750   0.7330   0.01688   0.00870  -0.1990   0.7962   0.5605
  -0.500   0.7556   0.01697   0.00894  -0.1977   0.7893   0.6378
  -0.250   0.7796   0.01692   0.00901  -0.1965   0.7839   0.7086
   0.000   0.8063   0.01681   0.00891  -0.1957   0.7795   0.7572
   0.250   0.8260   0.01691   0.00904  -0.1940   0.7719   0.7913
   0.500   0.8513   0.01671   0.00883  -0.1930   0.7666   0.8341
   0.750   0.8639   0.01658   0.00877  -0.1896   0.7585   0.9720
   1.000   0.8988   0.01664   0.00868  -0.1911   0.7528   1.0000
   1.250   0.9287   0.01684   0.00878  -0.1917   0.7466   1.0000
   1.500   0.9571   0.01705   0.00891  -0.1920   0.7400   1.0000
   1.750   0.9907   0.01711   0.00886  -0.1931   0.7354   1.0000
   2.000   1.0140   0.01746   0.00920  -0.1925   0.7272   1.0000
   2.250   1.0455   0.01753   0.00920  -0.1932   0.7215   1.0000
   2.500   1.0699   0.01781   0.00948  -0.1926   0.7133   1.0000
   2.750   1.1004   0.01788   0.00949  -0.1931   0.7068   1.0000
   3.000   1.1244   0.01816   0.00981  -0.1924   0.6982   1.0000
   3.250   1.1543   0.01826   0.00988  -0.1928   0.6919   1.0000
   3.500   1.1778   0.01858   0.01025  -0.1921   0.6835   1.0000
   3.750   1.2070   0.01870   0.01036  -0.1923   0.6769   1.0000
   4.000   1.2299   0.01902   0.01078  -0.1914   0.6679   1.0000
   4.250   1.2597   0.01910   0.01087  -0.1917   0.6611   1.0000
   4.500   1.2815   0.01943   0.01128  -0.1906   0.6508   1.0000
   4.750   1.3068   0.01963   0.01152  -0.1901   0.6413   1.0000
   5.000   1.3339   0.01977   0.01173  -0.1898   0.6322   1.0000
   5.250   1.3558   0.02011   0.01217  -0.1888   0.6215   1.0000
   5.500   1.3797   0.02035   0.01249  -0.1880   0.6108   1.0000
   5.750   1.4043   0.02054   0.01277  -0.1873   0.5993   1.0000
   6.000   1.4283   0.02077   0.01308  -0.1865   0.5876   1.0000
   6.250   1.4499   0.02112   0.01353  -0.1854   0.5753   1.0000
   6.500   1.4717   0.02144   0.01395  -0.1842   0.5621   1.0000
   6.750   1.4924   0.02174   0.01433  -0.1828   0.5455   1.0000
   7.000   1.5115   0.02206   0.01467  -0.1810   0.5262   1.0000
   7.250   1.5271   0.02250   0.01514  -0.1787   0.5040   1.0000
   7.500   1.5415   0.02302   0.01564  -0.1762   0.4798   1.0000
   7.750   1.5543   0.02363   0.01625  -0.1736   0.4558   1.0000
   8.000   1.5655   0.02432   0.01698  -0.1707   0.4338   1.0000
   8.250   1.5756   0.02510   0.01780  -0.1677   0.4121   1.0000
   8.500   1.5832   0.02602   0.01871  -0.1644   0.3882   1.0000
   8.750   1.5867   0.02717   0.01981  -0.1607   0.3592   1.0000
   9.000   1.5864   0.02860   0.02113  -0.1567   0.3243   1.0000
   9.250   1.5837   0.03033   0.02273  -0.1526   0.2859   1.0000
   9.500   1.5773   0.03250   0.02468  -0.1486   0.2454   1.0000
   9.750   1.5692   0.03506   0.02702  -0.1448   0.2034   1.0000
  10.000   1.5598   0.03799   0.02969  -0.1413   0.1595   1.0000
  10.250   1.5501   0.04120   0.03264  -0.1383   0.1203   1.0000
  10.500   1.5421   0.04446   0.03571  -0.1356   0.0931   1.0000
  10.750   1.5368   0.04761   0.03877  -0.1335   0.0749   1.0000
  11.000   1.5331   0.05071   0.04187  -0.1316   0.0635   1.0000
  11.250   1.5297   0.05388   0.04511  -0.1299   0.0555   1.0000
  11.500   1.5251   0.05730   0.04859  -0.1284   0.0487   1.0000
  11.750   1.5224   0.06064   0.05209  -0.1271   0.0435   1.0000
  12.000   1.5182   0.06427   0.05585  -0.1260   0.0393   1.0000
  12.250   1.5125   0.06820   0.05988  -0.1250   0.0362   1.0000
  12.500   1.5109   0.07171   0.06361  -0.1243   0.0328   1.0000
  12.750   1.5085   0.07542   0.06744  -0.1238   0.0302   1.0000
  13.000   1.5046   0.07942   0.07153  -0.1235   0.0283   1.0000
  13.250   1.5042   0.08301   0.07531  -0.1231   0.0264   1.0000
  13.500   1.5033   0.08670   0.07916  -0.1229   0.0250   1.0000
  13.750   1.5028   0.09039   0.08297  -0.1228   0.0238   1.0000
  14.000   1.5027   0.09404   0.08673  -0.1227   0.0230   1.0000
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