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SELIG 3002-099-83 (s3002-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: SELIG 3002-099-83 (s3002-il)
Reynolds number: 50,000
Max Cl/Cd: 35.29 at α=6.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s3002-il-50000.txt
Download as CSV file: xf-s3002-il-50000.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 =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3553   0.10544   0.09862  -0.0233   1.0000   0.2301
  -8.250  -0.3432   0.10152   0.09475  -0.0224   1.0000   0.2401
  -8.000  -0.3712   0.10203   0.09547  -0.0235   1.0000   0.2476
  -7.750  -0.3513   0.09743   0.09088  -0.0217   1.0000   0.2617
  -7.500  -0.3393   0.09371   0.08721  -0.0203   1.0000   0.2734
  -7.250  -0.3406   0.09125   0.08486  -0.0192   1.0000   0.2845
  -7.000  -0.3744   0.09189   0.08575  -0.0171   1.0000   0.2946
  -6.750  -0.3681   0.08888   0.08282  -0.0148   1.0000   0.3098
  -6.500  -0.3669   0.08636   0.08040  -0.0122   1.0000   0.3251
  -6.250  -0.3708   0.08428   0.07842  -0.0091   1.0000   0.3407
  -6.000  -0.3818   0.08276   0.07704  -0.0060   1.0000   0.3571
  -5.750  -0.3606   0.07914   0.07343  -0.0024   1.0000   0.3830
  -5.500  -0.3806   0.07847   0.07292   0.0019   1.0000   0.4036
  -5.250  -0.3775   0.07635   0.07088   0.0065   1.0000   0.4346
  -5.000  -0.3769   0.07449   0.06910   0.0112   1.0000   0.4662
  -4.250  -0.3619   0.05079   0.04433  -0.0390   1.0000   0.1974
  -4.000  -0.3209   0.04350   0.03608  -0.0461   1.0000   0.1487
  -3.750  -0.2888   0.03928   0.03112  -0.0486   1.0000   0.1347
  -3.500  -0.2592   0.03595   0.02721  -0.0500   1.0000   0.1285
  -3.250  -0.2315   0.03363   0.02445  -0.0506   1.0000   0.1297
  -3.000  -0.2038   0.03168   0.02209  -0.0509   1.0000   0.1330
  -2.750  -0.1762   0.02993   0.01990  -0.0508   1.0000   0.1354
  -2.500  -0.1510   0.02848   0.01823  -0.0505   1.0000   0.1430
  -2.250  -0.1265   0.02741   0.01693  -0.0498   1.0000   0.1533
  -2.000  -0.1046   0.02636   0.01591  -0.0486   1.0000   0.1673
  -1.750  -0.0819   0.02537   0.01503  -0.0477   1.0000   0.1917
  -1.500  -0.0540   0.02385   0.01398  -0.0478   1.0000   0.2676
  -1.250  -0.0664   0.02118   0.01425  -0.0360   1.0000   0.8591
  -1.000  -0.0498   0.02080   0.01351  -0.0342   1.0000   1.0000
  -0.750  -0.0257   0.02123   0.01346  -0.0349   1.0000   1.0000
  -0.500  -0.0023   0.02172   0.01359  -0.0357   1.0000   1.0000
  -0.250   0.0204   0.02227   0.01383  -0.0364   1.0000   1.0000
   0.000   0.0424   0.02288   0.01418  -0.0370   1.0000   1.0000
   0.250   0.0638   0.02356   0.01463  -0.0376   1.0000   1.0000
   0.500   0.1036   0.02468   0.01550  -0.0416   0.9907   1.0000
   0.750   0.1573   0.02606   0.01663  -0.0479   0.9738   1.0000
   1.000   0.2094   0.02731   0.01767  -0.0536   0.9566   1.0000
   1.250   0.2533   0.02828   0.01851  -0.0577   0.9380   1.0000
   1.500   0.2983   0.02922   0.01934  -0.0618   0.9192   1.0000
   1.750   0.3449   0.03009   0.02013  -0.0658   0.9003   1.0000
   2.000   0.3939   0.03085   0.02084  -0.0698   0.8818   1.0000
   2.250   0.4310   0.03151   0.02147  -0.0719   0.8613   1.0000
   2.500   0.4708   0.03207   0.02203  -0.0741   0.8409   1.0000
   2.750   0.5174   0.03241   0.02240  -0.0768   0.8215   1.0000
   3.000   0.5698   0.03242   0.02247  -0.0799   0.8032   1.0000
   3.250   0.5980   0.03286   0.02295  -0.0798   0.7803   1.0000
   3.500   0.6446   0.03261   0.02280  -0.0814   0.7609   1.0000
   3.750   0.6918   0.03202   0.02229  -0.0824   0.7426   1.0000
   4.000   0.7226   0.03200   0.02234  -0.0817   0.7203   1.0000
   4.250   0.7622   0.03138   0.02182  -0.0814   0.6999   1.0000
   4.500   0.8062   0.03032   0.02084  -0.0811   0.6809   1.0000
   4.750   0.8333   0.03026   0.02087  -0.0796   0.6563   1.0000
   5.000   0.8738   0.02923   0.01986  -0.0787   0.6352   1.0000
   5.250   0.9005   0.02919   0.01988  -0.0772   0.6093   1.0000
   5.500   0.9322   0.02885   0.01955  -0.0758   0.5843   1.0000
   5.750   0.9645   0.02852   0.01916  -0.0745   0.5588   1.0000
   6.000   0.9893   0.02884   0.01947  -0.0730   0.5310   1.0000
   6.250   1.0146   0.02924   0.01987  -0.0715   0.5034   1.0000
   6.500   1.0402   0.02971   0.02028  -0.0702   0.4764   1.0000
   6.750   1.0667   0.03023   0.02066  -0.0689   0.4496   1.0000
   7.000   1.0892   0.03111   0.02152  -0.0675   0.4229   1.0000
   7.250   1.1101   0.03217   0.02262  -0.0661   0.3969   1.0000
   7.500   1.1341   0.03316   0.02350  -0.0650   0.3724   1.0000
   7.750   1.1541   0.03439   0.02477  -0.0636   0.3481   1.0000
   8.000   1.1753   0.03573   0.02611  -0.0624   0.3256   1.0000
   8.250   1.1940   0.03721   0.02765  -0.0610   0.3039   1.0000
   8.500   1.2184   0.03851   0.02876  -0.0601   0.2836   1.0000
   8.750   1.2328   0.04047   0.03097  -0.0585   0.2656   1.0000
   9.000   1.2485   0.04244   0.03309  -0.0570   0.2488   1.0000
   9.250   1.2641   0.04454   0.03536  -0.0556   0.2337   1.0000
   9.500   1.2798   0.04681   0.03775  -0.0542   0.2205   1.0000
   9.750   1.2970   0.04897   0.03997  -0.0531   0.2079   1.0000
  10.000   1.3026   0.05207   0.04345  -0.0511   0.1988   1.0000
  10.250   1.3068   0.05546   0.04713  -0.0493   0.1912   1.0000
  10.500   1.3314   0.05749   0.04905  -0.0489   0.1805   1.0000
  10.750   1.3107   0.06229   0.05448  -0.0458   0.1780   1.0000
  11.000   1.2869   0.06741   0.06002  -0.0432   0.1766   1.0000
  11.250   1.2549   0.07277   0.06566  -0.0408   0.1765   1.0000
  11.500   1.2152   0.07901   0.07206  -0.0397   0.1776   1.0000
  11.750   1.1728   0.08699   0.08014  -0.0412   0.1792   1.0000
  12.000   1.1354   0.09642   0.08961  -0.0447   0.1806   1.0000
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