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SA7026 (sa7026-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: SA7026 (sa7026-il)
Reynolds number: 100,000
Max Cl/Cd: 61.83 at α=6.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sa7026-il-100000.txt
Download as CSV file: xf-sa7026-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: SA7026                                          
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3617   0.10601   0.10151  -0.0378   1.0000   0.0748
  -8.250  -0.3813   0.10553   0.10116  -0.0362   1.0000   0.0750
  -8.000  -0.4014   0.10499   0.10073  -0.0340   1.0000   0.0751
  -7.750  -0.3661   0.09710   0.09274  -0.0310   1.0000   0.0783
  -7.500  -0.3717   0.09529   0.09099  -0.0284   1.0000   0.0800
  -7.250  -0.3829   0.09386   0.08965  -0.0258   1.0000   0.0814
  -7.000  -0.3975   0.09264   0.08851  -0.0231   1.0000   0.0825
  -6.750  -0.4106   0.09104   0.08699  -0.0216   1.0000   0.0843
  -6.500  -0.4215   0.08908   0.08510  -0.0221   1.0000   0.0862
  -6.000  -0.4347   0.08254   0.07858  -0.0326   1.0000   0.0895
  -5.750  -0.4328   0.07993   0.07606  -0.0258   1.0000   0.0914
  -5.500  -0.4301   0.07754   0.07369  -0.0239   1.0000   0.0944
  -5.250  -0.4158   0.07310   0.06890  -0.0387   1.0000   0.1029
  -5.000  -0.4143   0.06944   0.06545  -0.0334   1.0000   0.1044
  -4.750  -0.4090   0.06712   0.06318  -0.0305   1.0000   0.1076
  -4.500  -0.3893   0.06254   0.05836  -0.0377   1.0000   0.1181
  -4.250  -0.3815   0.06020   0.05611  -0.0351   1.0000   0.1215
  -4.000  -0.3464   0.05614   0.05190  -0.0410   0.9952   0.1363
  -3.750  -0.3090   0.05225   0.04778  -0.0476   0.9895   0.1612
  -3.500  -0.2712   0.04917   0.04449  -0.0527   0.9842   0.1886
  -3.250  -0.2435   0.04629   0.04162  -0.0540   0.9784   0.2060
  -3.000  -0.1572   0.03299   0.02603  -0.0657   0.9778   0.0699
  -2.750  -0.1129   0.02987   0.02198  -0.0679   0.9735   0.0599
  -2.500  -0.0731   0.02774   0.01940  -0.0700   0.9689   0.0576
  -2.250  -0.0380   0.02620   0.01751  -0.0711   0.9627   0.0574
  -2.000   0.0041   0.02503   0.01607  -0.0733   0.9580   0.0598
  -1.750   0.0348   0.02409   0.01512  -0.0740   0.9508   0.0671
  -1.500   0.0746   0.02325   0.01431  -0.0762   0.9451   0.0826
  -1.250   0.1071   0.02062   0.01374  -0.0773   0.9404   0.5282
  -1.000   0.1459   0.01965   0.01362  -0.0783   0.9336   1.0000
  -0.750   0.1827   0.02001   0.01358  -0.0803   0.9258   1.0000
  -0.500   0.2209   0.02033   0.01360  -0.0826   0.9179   1.0000
  -0.250   0.2521   0.02063   0.01367  -0.0835   0.9084   1.0000
   0.000   0.2967   0.02091   0.01370  -0.0868   0.9023   1.0000
   0.250   0.3238   0.02117   0.01382  -0.0869   0.8917   1.0000
   0.500   0.3576   0.02142   0.01393  -0.0882   0.8829   1.0000
   0.750   0.3984   0.02155   0.01392  -0.0905   0.8756   1.0000
   1.000   0.4270   0.02176   0.01405  -0.0908   0.8650   1.0000
   1.250   0.4657   0.02182   0.01403  -0.0927   0.8571   1.0000
   1.500   0.5046   0.02177   0.01394  -0.0944   0.8485   1.0000
   1.750   0.5354   0.02185   0.01397  -0.0949   0.8379   1.0000
   2.000   0.5852   0.02144   0.01356  -0.0981   0.8330   1.0000
   2.250   0.6128   0.02146   0.01357  -0.0978   0.8214   1.0000
   2.500   0.6431   0.02140   0.01353  -0.0978   0.8108   1.0000
   2.750   0.6879   0.02078   0.01295  -0.0998   0.8054   1.0000
   3.000   0.7161   0.02064   0.01284  -0.0993   0.7935   1.0000
   3.250   0.7461   0.02040   0.01268  -0.0990   0.7821   1.0000
   3.500   0.7789   0.01999   0.01232  -0.0989   0.7713   1.0000
   3.750   0.8194   0.01920   0.01158  -0.0997   0.7635   1.0000
   4.000   0.8491   0.01885   0.01130  -0.0991   0.7503   1.0000
   4.250   0.8793   0.01847   0.01103  -0.0986   0.7366   1.0000
   4.500   0.9098   0.01810   0.01072  -0.0981   0.7222   1.0000
   4.750   0.9358   0.01795   0.01065  -0.0970   0.7045   1.0000
   5.000   0.9633   0.01773   0.01050  -0.0960   0.6858   1.0000
   5.250   0.9933   0.01743   0.01026  -0.0954   0.6669   1.0000
   5.500   1.0176   0.01740   0.01029  -0.0940   0.6432   1.0000
   5.750   1.0429   0.01739   0.01031  -0.0928   0.6186   1.0000
   6.000   1.0674   0.01749   0.01042  -0.0915   0.5922   1.0000
   6.250   1.0903   0.01769   0.01067  -0.0901   0.5636   1.0000
   6.500   1.1117   0.01798   0.01094  -0.0885   0.5325   1.0000
   6.750   1.1322   0.01835   0.01125  -0.0867   0.4997   1.0000
   7.000   1.1500   0.01884   0.01172  -0.0846   0.4643   1.0000
   7.250   1.1672   0.01942   0.01222  -0.0825   0.4292   1.0000
   7.500   1.1822   0.02009   0.01291  -0.0802   0.3921   1.0000
   7.750   1.1956   0.02085   0.01360  -0.0778   0.3544   1.0000
   8.000   1.2059   0.02171   0.01435  -0.0749   0.3137   1.0000
   8.250   1.2120   0.02268   0.01518  -0.0716   0.2668   1.0000
   8.500   1.2150   0.02387   0.01612  -0.0681   0.2150   1.0000
   8.750   1.2149   0.02539   0.01729  -0.0645   0.1585   1.0000
   9.000   1.2079   0.02773   0.01911  -0.0600   0.1018   1.0000
   9.250   1.1981   0.03065   0.02163  -0.0554   0.0651   1.0000
   9.500   1.1944   0.03318   0.02408  -0.0517   0.0525   1.0000
   9.750   1.1984   0.03549   0.02648  -0.0487   0.0459   1.0000
  10.000   1.2063   0.03792   0.02885  -0.0466   0.0414   1.0000
  10.250   1.2313   0.04081   0.03191  -0.0457   0.0383   1.0000
  10.500   1.2555   0.04341   0.03476  -0.0449   0.0358   1.0000
  10.750   1.2711   0.04590   0.03746  -0.0437   0.0334   1.0000
  11.000   1.2870   0.04900   0.04066  -0.0429   0.0312   1.0000
  11.250   1.3044   0.05342   0.04539  -0.0423   0.0306   1.0000
  11.500   1.3085   0.05714   0.04947  -0.0403   0.0305   1.0000
  11.750   1.3053   0.06049   0.05317  -0.0378   0.0306   1.0000
  12.000   1.2973   0.06390   0.05692  -0.0353   0.0308   1.0000
  12.250   1.2852   0.06736   0.06073  -0.0330   0.0311   1.0000
  12.500   1.2695   0.07123   0.06496  -0.0312   0.0315   1.0000
  12.750   1.2504   0.07571   0.06977  -0.0302   0.0319   1.0000
  13.000   1.2256   0.08094   0.07535  -0.0302   0.0324   1.0000
  13.250   1.1976   0.08703   0.08176  -0.0316   0.0330   1.0000
  13.500   1.1710   0.09376   0.08876  -0.0342   0.0333   1.0000
  13.750   1.1432   0.10148   0.09671  -0.0382   0.0338   1.0000
  14.000   1.1146   0.11036   0.10579  -0.0438   0.0344   1.0000
  14.250   1.0846   0.12103   0.11662  -0.0511   0.0351   1.0000
  14.500   1.0546   0.13372   0.12940  -0.0600   0.0361   1.0000
  14.750   1.0333   0.14578   0.14146  -0.0674   0.0378   1.0000
  15.000   1.0235   0.15484   0.15049  -0.0722   0.0390   1.0000
  15.250   1.0204   0.16163   0.15726  -0.0752   0.0398   1.0000
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