Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

SELIG 3002-099-83 (s3002-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: SELIG 3002-099-83 (s3002-il)
Reynolds number: 1,000,000
Max Cl/Cd: 100.08 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s3002-il-1000000-n5.txt
Download as CSV file: xf-s3002-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: SELIG 3002-099-83                               
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -12.250  -0.4183   0.13132   0.12951  -0.0181   1.0000   0.0045
 -10.250  -0.7034   0.02588   0.02302  -0.0809   0.9855   0.0047
 -10.000  -0.6814   0.02275   0.01952  -0.0830   0.9787   0.0049
  -9.750  -0.6550   0.02060   0.01708  -0.0848   0.9723   0.0050
  -9.500  -0.6295   0.01911   0.01538  -0.0855   0.9633   0.0052
  -9.250  -0.6035   0.01776   0.01381  -0.0862   0.9540   0.0053
  -9.000  -0.5782   0.01667   0.01253  -0.0864   0.9426   0.0054
  -8.750  -0.5538   0.01577   0.01145  -0.0862   0.9303   0.0055
  -8.500  -0.5289   0.01505   0.01057  -0.0859   0.9188   0.0056
  -8.250  -0.5038   0.01440   0.00977  -0.0857   0.9083   0.0057
  -8.000  -0.4785   0.01381   0.00904  -0.0854   0.8980   0.0058
  -7.750  -0.4535   0.01294   0.00801  -0.0852   0.8885   0.0060
  -7.500  -0.4276   0.01236   0.00731  -0.0850   0.8798   0.0062
  -7.250  -0.4011   0.01190   0.00677  -0.0848   0.8713   0.0064
  -7.000  -0.3743   0.01152   0.00630  -0.0847   0.8637   0.0066
  -6.750  -0.3472   0.01115   0.00585  -0.0846   0.8559   0.0069
  -6.500  -0.3201   0.01080   0.00542  -0.0845   0.8488   0.0071
  -6.250  -0.2927   0.01046   0.00501  -0.0844   0.8415   0.0074
  -5.750  -0.2375   0.00988   0.00429  -0.0843   0.8276   0.0081
  -5.500  -0.2099   0.00955   0.00391  -0.0843   0.8205   0.0088
  -5.250  -0.1819   0.00933   0.00367  -0.0843   0.8136   0.0094
  -5.000  -0.1540   0.00912   0.00340  -0.0842   0.8060   0.0101
  -4.750  -0.1259   0.00891   0.00314  -0.0842   0.7986   0.0107
  -4.500  -0.0979   0.00870   0.00289  -0.0842   0.7903   0.0117
  -4.250  -0.0697   0.00854   0.00270  -0.0842   0.7822   0.0128
  -4.000  -0.0416   0.00841   0.00251  -0.0842   0.7734   0.0139
  -3.750  -0.0134   0.00824   0.00233  -0.0842   0.7644   0.0155
  -3.500   0.0148   0.00814   0.00218  -0.0842   0.7546   0.0171
  -3.250   0.0430   0.00801   0.00201  -0.0842   0.7438   0.0185
  -3.000   0.0713   0.00787   0.00185  -0.0842   0.7334   0.0202
  -2.750   0.0995   0.00778   0.00170  -0.0841   0.7231   0.0218
  -2.500   0.1278   0.00768   0.00157  -0.0841   0.7121   0.0241
  -2.250   0.1561   0.00759   0.00145  -0.0842   0.7010   0.0272
  -2.000   0.1844   0.00750   0.00134  -0.0842   0.6893   0.0323
  -1.750   0.2126   0.00737   0.00124  -0.0842   0.6765   0.0529
  -1.500   0.2408   0.00723   0.00116  -0.0843   0.6630   0.0851
  -1.250   0.2690   0.00712   0.00110  -0.0843   0.6483   0.1204
  -1.000   0.2971   0.00700   0.00105  -0.0844   0.6324   0.1647
  -0.750   0.3252   0.00679   0.00101  -0.0846   0.6156   0.2459
  -0.500   0.3532   0.00657   0.00098  -0.0848   0.5973   0.3395
  -0.250   0.3811   0.00635   0.00097  -0.0850   0.5771   0.4430
   0.000   0.4087   0.00606   0.00100  -0.0852   0.5566   0.5850
   0.250   0.4360   0.00600   0.00109  -0.0851   0.5343   0.6712
   0.500   0.4635   0.00613   0.00115  -0.0850   0.5103   0.6936
   0.750   0.4910   0.00627   0.00122  -0.0848   0.4865   0.7093
   1.000   0.5184   0.00642   0.00130  -0.0847   0.4638   0.7273
   1.250   0.5458   0.00658   0.00139  -0.0845   0.4415   0.7421
   1.750   0.6005   0.00692   0.00157  -0.0842   0.3992   0.7618
   2.000   0.6278   0.00709   0.00166  -0.0841   0.3787   0.7678
   2.500   0.6824   0.00745   0.00186  -0.0839   0.3399   0.7765
   2.750   0.7096   0.00764   0.00196  -0.0838   0.3211   0.7801
   3.000   0.7368   0.00781   0.00208  -0.0836   0.3051   0.7835
   3.250   0.7639   0.00799   0.00220  -0.0835   0.2891   0.7871
   3.500   0.7910   0.00819   0.00233  -0.0834   0.2730   0.7908
   3.750   0.8180   0.00840   0.00247  -0.0832   0.2572   0.7944
   4.000   0.8448   0.00859   0.00262  -0.0831   0.2421   0.7979
   4.250   0.8715   0.00879   0.00277  -0.0829   0.2281   0.8018
   4.500   0.8980   0.00903   0.00294  -0.0827   0.2121   0.8059
   5.000   0.9507   0.00950   0.00332  -0.0822   0.1833   0.8141
   5.250   0.9768   0.00976   0.00352  -0.0820   0.1693   0.8188
   5.500   1.0027   0.01003   0.00374  -0.0817   0.1551   0.8236
   5.750   1.0286   0.01028   0.00397  -0.0814   0.1435   0.8287
   6.000   1.0542   0.01054   0.00420  -0.0811   0.1323   0.8347
   6.500   1.1049   0.01111   0.00472  -0.0804   0.1114   0.8482
   6.750   1.1303   0.01135   0.00497  -0.0801   0.1036   0.8572
   7.000   1.1549   0.01163   0.00525  -0.0796   0.0950   0.8694
   7.250   1.1783   0.01192   0.00556  -0.0789   0.0859   0.8879
   7.500   1.2009   0.01202   0.00579  -0.0778   0.0801   0.9910
   7.750   1.2255   0.01239   0.00612  -0.0774   0.0728   1.0000
   8.000   1.2501   0.01275   0.00646  -0.0771   0.0662   1.0000
   8.250   1.2745   0.01312   0.00681  -0.0766   0.0607   1.0000
   8.500   1.2986   0.01350   0.00718  -0.0762   0.0555   1.0000
   8.750   1.3224   0.01390   0.00756  -0.0757   0.0506   1.0000
   9.000   1.3460   0.01429   0.00795  -0.0751   0.0467   1.0000
   9.250   1.3690   0.01473   0.00839  -0.0745   0.0428   1.0000
   9.500   1.3923   0.01511   0.00879  -0.0740   0.0403   1.0000
   9.750   1.4146   0.01557   0.00925  -0.0733   0.0373   1.0000
  10.000   1.4366   0.01603   0.00972  -0.0725   0.0348   1.0000
  10.250   1.4588   0.01645   0.01018  -0.0718   0.0331   1.0000
  10.500   1.4800   0.01692   0.01067  -0.0710   0.0311   1.0000
  10.750   1.5002   0.01746   0.01122  -0.0700   0.0291   1.0000
  11.000   1.5205   0.01795   0.01175  -0.0690   0.0277   1.0000
  11.250   1.5404   0.01844   0.01228  -0.0680   0.0265   1.0000
  11.500   1.5591   0.01897   0.01285  -0.0669   0.0252   1.0000
  11.750   1.5761   0.01958   0.01349  -0.0654   0.0239   1.0000
  12.000   1.5900   0.02022   0.01416  -0.0635   0.0225   1.0000
  12.250   1.6043   0.02076   0.01476  -0.0616   0.0217   1.0000
  12.500   1.6171   0.02139   0.01544  -0.0596   0.0204   1.0000
  12.750   1.6281   0.02216   0.01624  -0.0575   0.0189   1.0000
  13.000   1.6385   0.02300   0.01712  -0.0554   0.0178   1.0000
  13.250   1.6500   0.02381   0.01799  -0.0536   0.0171   1.0000
  13.500   1.6603   0.02472   0.01896  -0.0518   0.0164   1.0000
  13.750   1.6694   0.02576   0.02005  -0.0501   0.0154   1.0000
  14.000   1.6769   0.02696   0.02130  -0.0483   0.0145   1.0000
  14.250   1.6848   0.02820   0.02261  -0.0467   0.0138   1.0000
  14.500   1.6924   0.02950   0.02399  -0.0453   0.0131   1.0000
  14.750   1.6988   0.03098   0.02554  -0.0439   0.0125   1.0000
  15.000   1.7035   0.03266   0.02728  -0.0426   0.0117   1.0000
  15.250   1.7067   0.03455   0.02924  -0.0415   0.0110   1.0000
  15.500   1.7108   0.03644   0.03123  -0.0405   0.0106   1.0000
  15.750   1.7138   0.03854   0.03341  -0.0398   0.0102   1.0000
  16.000   1.7152   0.04089   0.03585  -0.0392   0.0096   1.0000
  16.250   1.7151   0.04351   0.03856  -0.0388   0.0092   1.0000
  16.500   1.7131   0.04649   0.04163  -0.0387   0.0087   1.0000
  16.750   1.7095   0.04979   0.04503  -0.0389   0.0084   1.0000
  17.000   1.7063   0.05321   0.04856  -0.0393   0.0081   1.0000
  17.250   1.7017   0.05700   0.05247  -0.0401   0.0078   1.0000
  17.500   1.6952   0.06123   0.05682  -0.0412   0.0075   1.0000
  17.750   1.6869   0.06594   0.06165  -0.0428   0.0073   1.0000
  18.000   1.6767   0.07119   0.06702  -0.0448   0.0071   1.0000
  18.250   1.6639   0.07703   0.07300  -0.0472   0.0069   1.0000
  18.500   1.6489   0.08351   0.07961  -0.0501   0.0067   1.0000
  18.750   1.6316   0.09061   0.08685  -0.0536   0.0065   1.0000
  19.000   1.6121   0.09832   0.09470  -0.0575   0.0064   1.0000
  19.250   1.5912   0.10654   0.10308  -0.0618   0.0063   1.0000
<< Back to SELIG 3002-099-83 (s3002-il)

Polar data table (+)

Polar graphs


<< Back to SELIG 3002-099-83 (s3002-il)