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AH 79-100 C AIRFOIL (ah79100c-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: AH 79-100 C AIRFOIL (ah79100c-il)
Reynolds number: 100,000
Max Cl/Cd: 61.47 at α=7°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-ah79100c-il-100000-n5.txt
Download as CSV file: xf-ah79100c-il-100000-n5.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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.1481   0.10415   0.09920  -0.0794   0.9356   0.0473
  -7.500  -0.1434   0.10137   0.09644  -0.0827   0.9298   0.0475
  -7.250  -0.1437   0.09908   0.09418  -0.0827   0.9218   0.0475
  -7.000  -0.1339   0.09559   0.09070  -0.0860   0.9166   0.0476
  -6.250  -0.1030   0.08351   0.07863  -0.0900   0.9018   0.0397
  -6.000  -0.1013   0.08113   0.07625  -0.0888   0.8932   0.0366
  -5.750  -0.0844   0.07700   0.07210  -0.0934   0.8888   0.0360
  -5.500  -0.0768   0.07364   0.06874  -0.0961   0.8811   0.0359
  -5.250  -0.0585   0.06912   0.06418  -0.1015   0.8758   0.0350
  -5.000  -0.0269   0.06290   0.05786  -0.1112   0.8729   0.0339
  -4.750  -0.0104   0.05819   0.05306  -0.1164   0.8644   0.0336
  -4.500   0.0326   0.05140   0.04604  -0.1279   0.8612   0.0359
  -4.250   0.1043   0.03909   0.03280  -0.1480   0.8604   0.0394
  -4.000   0.1401   0.03738   0.03095  -0.1513   0.8587   0.0425
  -3.750   0.1932   0.03251   0.02520  -0.1593   0.8580   0.0456
  -3.500   0.2236   0.03027   0.02223  -0.1613   0.8522   0.0475
  -3.250   0.2588   0.02843   0.02001  -0.1636   0.8491   0.0489
  -3.000   0.2939   0.02729   0.01865  -0.1655   0.8468   0.0514
  -2.750   0.3306   0.02625   0.01734  -0.1674   0.8450   0.0554
  -2.500   0.3685   0.02511   0.01587  -0.1693   0.8435   0.0583
  -2.250   0.3905   0.02470   0.01540  -0.1687   0.8372   0.0609
  -2.000   0.4209   0.02417   0.01484  -0.1694   0.8336   0.0659
  -1.750   0.4553   0.02354   0.01410  -0.1707   0.8312   0.0742
  -1.500   0.4916   0.02294   0.01343  -0.1723   0.8294   0.0859
  -1.250   0.5288   0.02231   0.01286  -0.1742   0.8279   0.1054
  -1.000   0.5443   0.02255   0.01316  -0.1723   0.8193   0.1241
  -0.750   0.5786   0.02209   0.01282  -0.1736   0.8166   0.1690
  -0.500   0.6155   0.02158   0.01248  -0.1755   0.8146   0.2442
  -0.250   0.6543   0.02103   0.01217  -0.1776   0.8130   0.3466
   0.000   0.6693   0.02131   0.01273  -0.1757   0.8043   0.4446
   0.250   0.6979   0.02052   0.01267  -0.1753   0.8014   0.7008
   0.500   0.7240   0.01977   0.01210  -0.1740   0.7986   1.0000
   1.000   0.7744   0.02022   0.01227  -0.1732   0.7865   1.0000
   1.250   0.8127   0.02001   0.01192  -0.1750   0.7840   1.0000
   1.750   0.8640   0.02037   0.01211  -0.1743   0.7715   1.0000
   2.000   0.9034   0.02010   0.01176  -0.1763   0.7686   1.0000
   2.250   0.9203   0.02055   0.01219  -0.1744   0.7602   1.0000
   2.500   0.9543   0.02045   0.01203  -0.1754   0.7556   1.0000
   2.750   0.9958   0.02014   0.01167  -0.1778   0.7525   1.0000
   3.000   1.0087   0.02065   0.01221  -0.1751   0.7426   1.0000
   3.250   1.0483   0.02036   0.01189  -0.1771   0.7383   1.0000
   3.500   1.0652   0.02075   0.01230  -0.1751   0.7291   1.0000
   3.750   1.1011   0.02058   0.01212  -0.1764   0.7237   1.0000
   4.000   1.1208   0.02088   0.01247  -0.1749   0.7148   1.0000
   4.250   1.1566   0.02066   0.01227  -0.1762   0.7080   1.0000
   4.500   1.1737   0.02099   0.01264  -0.1741   0.6976   1.0000
   4.750   1.2137   0.02068   0.01238  -0.1761   0.6911   1.0000
   5.000   1.2265   0.02112   0.01289  -0.1733   0.6796   1.0000
   5.250   1.2483   0.02131   0.01313  -0.1721   0.6690   1.0000
   5.500   1.2790   0.02122   0.01309  -0.1724   0.6591   1.0000
   5.750   1.2989   0.02144   0.01339  -0.1708   0.6468   1.0000
   6.000   1.3167   0.02173   0.01376  -0.1689   0.6336   1.0000
   6.250   1.3366   0.02195   0.01405  -0.1673   0.6195   1.0000
   6.500   1.3570   0.02216   0.01433  -0.1659   0.6045   1.0000
   6.750   1.3771   0.02242   0.01467  -0.1644   0.5892   1.0000
   7.000   1.3965   0.02272   0.01503  -0.1628   0.5733   1.0000
   7.250   1.4161   0.02304   0.01540  -0.1612   0.5566   1.0000
   7.500   1.4347   0.02338   0.01578  -0.1595   0.5377   1.0000
   7.750   1.4495   0.02389   0.01635  -0.1571   0.5165   1.0000
   8.000   1.4659   0.02439   0.01682  -0.1551   0.4941   1.0000
   8.250   1.4793   0.02505   0.01750  -0.1527   0.4719   1.0000
   8.500   1.4922   0.02579   0.01821  -0.1502   0.4494   1.0000
   8.750   1.5028   0.02665   0.01910  -0.1475   0.4264   1.0000
   9.000   1.5093   0.02772   0.02009  -0.1443   0.3992   1.0000
   9.250   1.5108   0.02907   0.02131  -0.1405   0.3670   1.0000
   9.500   1.5086   0.03071   0.02278  -0.1365   0.3308   1.0000
   9.750   1.5037   0.03266   0.02449  -0.1324   0.2919   1.0000
  10.000   1.4992   0.03476   0.02637  -0.1288   0.2535   1.0000
  10.250   1.4964   0.03693   0.02836  -0.1256   0.2187   1.0000
  10.500   1.4958   0.03909   0.03041  -0.1229   0.1878   1.0000
  10.750   1.4945   0.04141   0.03260  -0.1203   0.1562   1.0000
  11.000   1.4926   0.04394   0.03499  -0.1179   0.1232   1.0000
  11.250   1.4870   0.04695   0.03777  -0.1154   0.0875   1.0000
  11.500   1.4804   0.05023   0.04083  -0.1130   0.0585   1.0000
  11.750   1.4753   0.05348   0.04398  -0.1110   0.0425   1.0000
  12.000   1.4730   0.05655   0.04709  -0.1092   0.0348   1.0000
  12.250   1.4712   0.05964   0.05028  -0.1077   0.0311   1.0000
  12.500   1.4704   0.06271   0.05354  -0.1064   0.0287   1.0000
  12.750   1.4681   0.06604   0.05700  -0.1053   0.0270   1.0000
  13.000   1.4635   0.06973   0.06081  -0.1044   0.0259   1.0000
  13.250   1.4611   0.07327   0.06456  -0.1037   0.0250   1.0000
  13.500   1.4581   0.07697   0.06846  -0.1031   0.0242   1.0000
  13.750   1.4547   0.08082   0.07249  -0.1027   0.0236   1.0000
  14.000   1.4512   0.08474   0.07658  -0.1026   0.0230   1.0000
  14.250   1.4480   0.08869   0.08070  -0.1025   0.0224   1.0000
  14.500   1.4453   0.09264   0.08479  -0.1027   0.0219   1.0000
  14.750   1.4427   0.09659   0.08886  -0.1029   0.0213   1.0000
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