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HAM-STD HS1-404 AIRFOIL (hs1404-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: HAM-STD HS1-404 AIRFOIL (hs1404-il)
Reynolds number: 1,000,000
Max Cl/Cd: 134.6 at α=1.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hs1404-il-1000000.txt
Download as CSV file: xf-hs1404-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HAM-STD HS1-404 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.4489   0.09689   0.09526  -0.0081   1.0000   0.0031
  -7.750  -0.4431   0.09354   0.09193  -0.0098   1.0000   0.0031
  -7.500  -0.4378   0.09027   0.08868  -0.0114   1.0000   0.0031
  -7.250  -0.4296   0.08671   0.08513  -0.0141   1.0000   0.0031
  -7.000  -0.4187   0.08291   0.08135  -0.0175   1.0000   0.0031
  -6.750  -0.4070   0.07907   0.07752  -0.0210   1.0000   0.0031
  -6.500  -0.3955   0.07528   0.07374  -0.0243   1.0000   0.0031
  -6.250  -0.3843   0.07141   0.06989  -0.0274   1.0000   0.0031
  -6.000  -0.3769   0.06644   0.06493  -0.0308   1.0000   0.0032
  -5.750  -0.3479   0.05975   0.05820  -0.0397   0.9984   0.0034
  -5.500  -0.3093   0.05314   0.05148  -0.0498   0.9964   0.0036
  -5.250  -0.2684   0.04702   0.04526  -0.0589   0.9948   0.0037
  -5.000  -0.2288   0.04151   0.03963  -0.0663   0.9926   0.0039
  -4.750  -0.1884   0.03605   0.03402  -0.0728   0.9902   0.0042
  -4.500  -0.1468   0.03026   0.02801  -0.0787   0.9882   0.0045
  -4.250  -0.1049   0.02379   0.02121  -0.0835   0.9865   0.0048
  -4.000  -0.0667   0.01926   0.01629  -0.0866   0.9845   0.0057
  -3.500   0.0038   0.01289   0.00903  -0.0897   0.9766   0.0066
  -2.750   0.0944   0.00987   0.00545  -0.0912   0.9571   0.0170
  -2.500   0.1234   0.00799   0.00327  -0.0908   0.9474   0.0122
  -2.250   0.1509   0.00732   0.00244  -0.0902   0.9358   0.0098
  -2.000   0.1776   0.00699   0.00201  -0.0896   0.9230   0.0089
  -1.750   0.2049   0.00667   0.00157  -0.0892   0.9111   0.0084
  -1.500   0.2325   0.00642   0.00114  -0.0888   0.9002   0.0084
  -1.250   0.2604   0.00615   0.00085  -0.0886   0.8896   0.0500
  -1.000   0.2879   0.00598   0.00073  -0.0885   0.8790   0.0962
  -0.750   0.3158   0.00578   0.00074  -0.0886   0.8701   0.1714
  -0.500   0.3435   0.00570   0.00076  -0.0886   0.8630   0.2163
  -0.250   0.3715   0.00559   0.00078  -0.0887   0.8553   0.2616
   0.000   0.3994   0.00550   0.00078  -0.0888   0.8481   0.3048
   0.250   0.4211   0.00386   0.00084  -0.0877   0.8402   1.0000
   0.500   0.4490   0.00391   0.00086  -0.0877   0.8318   1.0000
   0.750   0.4767   0.00397   0.00087  -0.0876   0.8233   1.0000
   1.000   0.5044   0.00403   0.00089  -0.0875   0.8127   1.0000
   1.250   0.5316   0.00411   0.00091  -0.0873   0.7942   1.0000
   1.500   0.5587   0.00421   0.00092  -0.0870   0.7705   1.0000
   1.750   0.5855   0.00435   0.00095  -0.0868   0.7358   1.0000
   2.000   0.6112   0.00466   0.00100  -0.0863   0.6611   1.0000
   2.250   0.6356   0.00531   0.00121  -0.0857   0.5450   1.0000
   2.500   0.6609   0.00589   0.00142  -0.0855   0.4501   1.0000
   2.750   0.6858   0.00656   0.00166  -0.0852   0.3465   1.0000
   3.000   0.7109   0.00720   0.00191  -0.0850   0.2538   1.0000
   3.250   0.7349   0.00807   0.00227  -0.0847   0.1346   1.0000
   3.500   0.7594   0.00886   0.00266  -0.0843   0.0511   1.0000
   3.750   0.7858   0.00922   0.00302  -0.0841   0.0339   1.0000
   4.000   0.8120   0.00958   0.00335  -0.0839   0.0226   1.0000
   4.250   0.8387   0.00980   0.00355  -0.0838   0.0176   1.0000
   4.500   0.8646   0.01029   0.00410  -0.0834   0.0119   1.0000
   4.750   0.8914   0.01039   0.00416  -0.0834   0.0093   1.0000
   5.000   0.9158   0.01135   0.00517  -0.0825   0.0020   1.0000
   5.250   0.9380   0.01292   0.00707  -0.0811   0.0018   1.0000
   5.500   0.9595   0.01470   0.00909  -0.0796   0.0018   1.0000
   5.750   0.9823   0.01625   0.01083  -0.0784   0.0018   1.0000
   6.000   1.0057   0.01781   0.01264  -0.0773   0.0020   1.0000
  13.250   0.7500   0.16298   0.16159  -0.0768   0.0048   1.0000
  13.500   0.7498   0.16638   0.16498  -0.0779   0.0048   1.0000
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