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AIRFOIL 3024 9.84% (s3024-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: AIRFOIL 3024 9.84% (s3024-il)
Reynolds number: 100,000
Max Cl/Cd: 57.73 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s3024-il-100000-n5.txt
Download as CSV file: xf-s3024-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: AIRFOIL 3024    9.84%                           
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3345   0.09350   0.08882  -0.0397   1.0000   0.0522
  -8.250  -0.3431   0.09116   0.08658  -0.0390   1.0000   0.0520
  -8.000  -0.3575   0.08941   0.08494  -0.0371   1.0000   0.0515
  -7.500  -0.3732   0.07796   0.07356  -0.0454   0.9882   0.0289
  -7.250  -0.3574   0.07323   0.06881  -0.0509   0.9812   0.0280
  -7.000  -0.3396   0.06731   0.06281  -0.0588   0.9742   0.0268
  -6.500  -0.3107   0.04850   0.04328  -0.0765   0.9566   0.0232
  -6.250  -0.2919   0.04400   0.03845  -0.0793   0.9499   0.0230
  -6.000  -0.2699   0.03962   0.03362  -0.0818   0.9446   0.0228
  -5.750  -0.2520   0.03573   0.02914  -0.0824   0.9369   0.0231
  -5.500  -0.2256   0.03261   0.02556  -0.0839   0.9326   0.0241
  -5.250  -0.2043   0.03095   0.02368  -0.0837   0.9259   0.0251
  -5.000  -0.1778   0.02852   0.02078  -0.0840   0.9207   0.0255
  -4.750  -0.1470   0.02629   0.01808  -0.0848   0.9172   0.0259
  -4.500  -0.1252   0.02478   0.01624  -0.0837   0.9099   0.0264
  -4.250  -0.0958   0.02328   0.01445  -0.0839   0.9054   0.0273
  -4.000  -0.0650   0.02199   0.01293  -0.0843   0.9016   0.0285
  -3.750  -0.0430   0.02110   0.01194  -0.0832   0.8942   0.0305
  -3.500  -0.0138   0.02035   0.01113  -0.0835   0.8896   0.0346
  -3.250   0.0119   0.01962   0.01026  -0.0829   0.8839   0.0382
  -3.000   0.0370   0.01892   0.00951  -0.0824   0.8775   0.0441
  -2.750   0.0663   0.01807   0.00871  -0.0824   0.8732   0.0653
  -2.500   0.0883   0.01740   0.00834  -0.0815   0.8658   0.1313
  -2.250   0.1141   0.01657   0.00811  -0.0815   0.8603   0.2645
  -2.000   0.1402   0.01598   0.00789  -0.0812   0.8550   0.3814
  -1.750   0.1620   0.01541   0.00779  -0.0799   0.8478   0.5294
  -1.500   0.1860   0.01465   0.00770  -0.0779   0.8433   0.7349
  -1.250   0.2580   0.01416   0.00733  -0.0854   0.8423   0.9664
  -1.000   0.2984   0.01416   0.00713  -0.0882   0.8349   1.0000
  -0.750   0.3242   0.01413   0.00691  -0.0875   0.8286   1.0000
  -0.500   0.3457   0.01423   0.00685  -0.0863   0.8197   1.0000
  -0.250   0.3720   0.01419   0.00665  -0.0857   0.8134   1.0000
   0.000   0.3939   0.01429   0.00664  -0.0845   0.8041   1.0000
   0.250   0.4209   0.01424   0.00645  -0.0840   0.7978   1.0000
   0.500   0.4431   0.01434   0.00646  -0.0829   0.7878   1.0000
   0.750   0.4688   0.01433   0.00635  -0.0822   0.7801   1.0000
   1.000   0.4933   0.01436   0.00631  -0.0813   0.7707   1.0000
   1.250   0.5175   0.01441   0.00630  -0.0804   0.7609   1.0000
   1.500   0.5447   0.01434   0.00614  -0.0799   0.7529   1.0000
   1.750   0.5682   0.01442   0.00619  -0.0789   0.7413   1.0000
   2.000   0.5928   0.01447   0.00620  -0.0781   0.7302   1.0000
   2.250   0.6184   0.01448   0.00617  -0.0774   0.7195   1.0000
   2.500   0.6448   0.01446   0.00610  -0.0767   0.7088   1.0000
   2.750   0.6692   0.01453   0.00617  -0.0759   0.6958   1.0000
   3.000   0.6940   0.01460   0.00624  -0.0751   0.6824   1.0000
   3.250   0.7190   0.01467   0.00630  -0.0744   0.6685   1.0000
   3.500   0.7441   0.01475   0.00636  -0.0736   0.6540   1.0000
   3.750   0.7691   0.01484   0.00646  -0.0728   0.6386   1.0000
   4.000   0.7942   0.01494   0.00654  -0.0721   0.6224   1.0000
   4.250   0.8189   0.01506   0.00664  -0.0713   0.6050   1.0000
   4.500   0.8428   0.01524   0.00681  -0.0704   0.5860   1.0000
   4.750   0.8668   0.01543   0.00700  -0.0695   0.5663   1.0000
   5.000   0.8906   0.01566   0.00718  -0.0686   0.5457   1.0000
   5.250   0.9136   0.01593   0.00745  -0.0676   0.5236   1.0000
   5.500   0.9364   0.01624   0.00771  -0.0666   0.5015   1.0000
   5.750   0.9583   0.01660   0.00807  -0.0655   0.4776   1.0000
   6.000   0.9798   0.01699   0.00842  -0.0644   0.4535   1.0000
   6.250   1.0007   0.01743   0.00882  -0.0632   0.4292   1.0000
   6.500   1.0210   0.01790   0.00929  -0.0620   0.4044   1.0000
   6.750   1.0406   0.01843   0.00978  -0.0607   0.3802   1.0000
   7.000   1.0596   0.01899   0.01031  -0.0593   0.3564   1.0000
   7.250   1.0782   0.01959   0.01089  -0.0579   0.3328   1.0000
   7.500   1.0956   0.02024   0.01152  -0.0564   0.3104   1.0000
   7.750   1.1132   0.02090   0.01220  -0.0550   0.2884   1.0000
   8.000   1.1292   0.02163   0.01291  -0.0533   0.2676   1.0000
   8.250   1.1452   0.02237   0.01367  -0.0518   0.2469   1.0000
   8.500   1.1598   0.02317   0.01447  -0.0500   0.2269   1.0000
   8.750   1.1727   0.02403   0.01534  -0.0481   0.2051   1.0000
   9.000   1.1825   0.02498   0.01621  -0.0458   0.1819   1.0000
   9.250   1.1919   0.02595   0.01715  -0.0436   0.1587   1.0000
   9.500   1.2001   0.02705   0.01818  -0.0413   0.1367   1.0000
   9.750   1.2084   0.02824   0.01932  -0.0393   0.1163   1.0000
  10.000   1.2160   0.02954   0.02057  -0.0373   0.0955   1.0000
  10.250   1.2229   0.03096   0.02198  -0.0354   0.0784   1.0000
  10.500   1.2278   0.03259   0.02358  -0.0334   0.0605   1.0000
  10.750   1.2301   0.03451   0.02544  -0.0314   0.0460   1.0000
  11.000   1.2312   0.03659   0.02753  -0.0294   0.0370   1.0000
  11.250   1.2314   0.03881   0.02983  -0.0276   0.0318   1.0000
  11.500   1.2313   0.04111   0.03224  -0.0260   0.0290   1.0000
  11.750   1.2288   0.04373   0.03496  -0.0246   0.0271   1.0000
  12.000   1.2280   0.04628   0.03770  -0.0235   0.0257   1.0000
  12.250   1.2267   0.04898   0.04058  -0.0226   0.0247   1.0000
  12.500   1.2239   0.05196   0.04371  -0.0219   0.0236   1.0000
  12.750   1.2209   0.05507   0.04699  -0.0216   0.0230   1.0000
  13.000   1.2167   0.05846   0.05052  -0.0214   0.0223   1.0000
  13.250   1.2112   0.06210   0.05428  -0.0216   0.0217   1.0000
  13.500   1.2078   0.06570   0.05805  -0.0218   0.0210   1.0000
  13.750   1.2054   0.06929   0.06183  -0.0222   0.0205   1.0000
  14.000   1.2022   0.07312   0.06585  -0.0229   0.0198   1.0000
  14.250   1.1984   0.07718   0.07009  -0.0238   0.0192   1.0000
  14.500   1.1945   0.08136   0.07444  -0.0249   0.0188   1.0000
  14.750   1.1897   0.08582   0.07906  -0.0263   0.0184   1.0000
  15.000   1.1842   0.09054   0.08394  -0.0280   0.0180   1.0000
  15.250   1.1791   0.09532   0.08889  -0.0297   0.0179   1.0000
  15.500   1.1732   0.10037   0.09410  -0.0317   0.0177   1.0000
  15.750   1.1664   0.10570   0.09959  -0.0340   0.0175   1.0000
  16.000   1.1590   0.11138   0.10544  -0.0367   0.0174   1.0000
  16.250   1.1504   0.11745   0.11169  -0.0397   0.0173   1.0000
  16.500   1.1404   0.12409   0.11852  -0.0433   0.0173   1.0000
  16.750   1.1286   0.13140   0.12601  -0.0475   0.0173   1.0000
  17.000   1.1138   0.13989   0.13471  -0.0526   0.0173   1.0000
  17.250   1.0924   0.15083   0.14587  -0.0594   0.0176   1.0000
  17.500   1.0565   0.16748   0.16276  -0.0696   0.0182   1.0000
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