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E392 (10.15%) (e392-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: E392 (10.15%) (e392-il)
Reynolds number: 100,000
Max Cl/Cd: 61.79 at α=7°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e392-il-100000-n5.txt
Download as CSV file: xf-e392-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E392  (10.15%)                                  
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3259   0.08729   0.08269  -0.0412   1.0000   0.0355
  -7.500  -0.3552   0.08001   0.07571  -0.0417   1.0000   0.0280
  -7.250  -0.3577   0.07749   0.07326  -0.0414   0.9979   0.0274
  -7.000  -0.3350   0.07163   0.06738  -0.0500   0.9853   0.0263
  -6.750  -0.3112   0.06409   0.05977  -0.0616   0.9716   0.0250
  -6.250  -0.2635   0.04320   0.03794  -0.0853   0.9413   0.0216
  -6.000  -0.2367   0.03812   0.03236  -0.0897   0.9299   0.0215
  -5.750  -0.2097   0.03365   0.02731  -0.0926   0.9179   0.0214
  -5.500  -0.1806   0.03001   0.02305  -0.0947   0.9069   0.0215
  -5.250  -0.1494   0.02699   0.01940  -0.0963   0.8973   0.0218
  -5.000  -0.1195   0.02487   0.01701  -0.0975   0.8871   0.0230
  -4.750  -0.0904   0.02352   0.01540  -0.0981   0.8760   0.0251
  -4.500  -0.0603   0.02198   0.01347  -0.0985   0.8659   0.0273
  -4.250  -0.0300   0.02045   0.01165  -0.0987   0.8566   0.0288
  -4.000  -0.0029   0.01924   0.01035  -0.0987   0.8456   0.0310
  -3.750   0.0252   0.01832   0.00929  -0.0986   0.8355   0.0352
  -3.500   0.0538   0.01750   0.00834  -0.0987   0.8266   0.0445
  -3.250   0.0810   0.01668   0.00747  -0.0986   0.8162   0.0636
  -3.000   0.1084   0.01595   0.00693  -0.0987   0.8070   0.1113
  -2.750   0.1360   0.01526   0.00645  -0.0989   0.7986   0.1807
  -2.500   0.1622   0.01467   0.00614  -0.0989   0.7891   0.2794
  -2.250   0.1885   0.01413   0.00597  -0.0987   0.7814   0.4105
  -2.000   0.2132   0.01380   0.00592  -0.0979   0.7725   0.5243
  -1.750   0.2380   0.01359   0.00585  -0.0969   0.7649   0.6136
  -1.500   0.2617   0.01342   0.00578  -0.0955   0.7570   0.6897
  -1.250   0.2839   0.01328   0.00572  -0.0937   0.7496   0.7612
  -1.000   0.3058   0.01313   0.00563  -0.0916   0.7423   0.8350
  -0.750   0.3376   0.01296   0.00542  -0.0917   0.7354   0.9270
  -0.500   0.3757   0.01294   0.00522  -0.0939   0.7281   1.0000
  -0.250   0.4035   0.01308   0.00516  -0.0940   0.7214   1.0000
   0.000   0.4309   0.01322   0.00514  -0.0941   0.7142   1.0000
   0.250   0.4588   0.01336   0.00512  -0.0942   0.7080   1.0000
   0.500   0.4859   0.01353   0.00518  -0.0942   0.7008   1.0000
   0.750   0.5140   0.01368   0.00518  -0.0942   0.6953   1.0000
   1.000   0.5406   0.01387   0.00532  -0.0942   0.6878   1.0000
   1.250   0.5684   0.01404   0.00538  -0.0942   0.6820   1.0000
   1.500   0.5953   0.01424   0.00553  -0.0941   0.6753   1.0000
   1.750   0.6227   0.01443   0.00567  -0.0941   0.6690   1.0000
   2.000   0.6499   0.01463   0.00583  -0.0940   0.6631   1.0000
   2.250   0.6767   0.01485   0.00603  -0.0939   0.6563   1.0000
   2.500   0.7045   0.01503   0.00615  -0.0939   0.6511   1.0000
   2.750   0.7305   0.01529   0.00647  -0.0937   0.6437   1.0000
   3.000   0.7580   0.01548   0.00664  -0.0937   0.6380   1.0000
   3.250   0.7841   0.01574   0.00695  -0.0935   0.6308   1.0000
   3.500   0.8111   0.01595   0.00720  -0.0933   0.6245   1.0000
   3.750   0.8372   0.01620   0.00750  -0.0931   0.6172   1.0000
   4.000   0.8639   0.01641   0.00774  -0.0929   0.6099   1.0000
   4.250   0.8896   0.01664   0.00805  -0.0925   0.6016   1.0000
   4.500   0.9165   0.01680   0.00825  -0.0922   0.5937   1.0000
   4.750   0.9413   0.01704   0.00861  -0.0918   0.5837   1.0000
   5.000   0.9670   0.01722   0.00887  -0.0913   0.5741   1.0000
   5.250   0.9932   0.01735   0.00908  -0.0908   0.5643   1.0000
   5.500   1.0175   0.01755   0.00941  -0.0902   0.5521   1.0000
   5.750   1.0419   0.01773   0.00970  -0.0895   0.5393   1.0000
   6.000   1.0661   0.01790   0.00999  -0.0888   0.5255   1.0000
   6.250   1.0900   0.01807   0.01030  -0.0880   0.5103   1.0000
   6.500   1.1135   0.01825   0.01057  -0.0871   0.4935   1.0000
   6.750   1.1358   0.01848   0.01093  -0.0861   0.4731   1.0000
   7.000   1.1573   0.01873   0.01124  -0.0849   0.4494   1.0000
   7.250   1.1773   0.01909   0.01166  -0.0835   0.4196   1.0000
   7.500   1.1950   0.01958   0.01214  -0.0818   0.3796   1.0000
   7.750   1.2072   0.02045   0.01272  -0.0795   0.3194   1.0000
   8.000   1.2125   0.02189   0.01370  -0.0765   0.2513   1.0000
   8.250   1.2163   0.02355   0.01496  -0.0737   0.1923   1.0000
   8.500   1.2202   0.02520   0.01630  -0.0710   0.1451   1.0000
   8.750   1.2251   0.02668   0.01762  -0.0683   0.1140   1.0000
   9.000   1.2292   0.02813   0.01898  -0.0656   0.0901   1.0000
   9.250   1.2320   0.02976   0.02053  -0.0629   0.0686   1.0000
   9.500   1.2326   0.03165   0.02235  -0.0603   0.0526   1.0000
   9.750   1.2333   0.03365   0.02431  -0.0580   0.0429   1.0000
  10.000   1.2363   0.03557   0.02635  -0.0561   0.0368   1.0000
  10.250   1.2361   0.03787   0.02869  -0.0544   0.0336   1.0000
  10.500   1.2383   0.04007   0.03105  -0.0529   0.0315   1.0000
  10.750   1.2406   0.04236   0.03350  -0.0516   0.0297   1.0000
  11.000   1.2428   0.04474   0.03602  -0.0505   0.0283   1.0000
  11.250   1.2450   0.04722   0.03863  -0.0495   0.0272   1.0000
  11.500   1.2463   0.04986   0.04137  -0.0487   0.0261   1.0000
  11.750   1.2469   0.05270   0.04426  -0.0478   0.0252   1.0000
  12.000   1.2532   0.05504   0.04683  -0.0471   0.0242   1.0000
  12.250   1.2590   0.05750   0.04948  -0.0464   0.0230   1.0000
  12.500   1.2640   0.06008   0.05224  -0.0459   0.0220   1.0000
  12.750   1.2690   0.06279   0.05511  -0.0453   0.0213   1.0000
  13.000   1.2737   0.06563   0.05811  -0.0449   0.0208   1.0000
  13.250   1.2774   0.06864   0.06130  -0.0446   0.0203   1.0000
  13.500   1.2801   0.07186   0.06468  -0.0444   0.0199   1.0000
  13.750   1.2814   0.07535   0.06834  -0.0444   0.0195   1.0000
  14.000   1.2810   0.07916   0.07234  -0.0446   0.0193   1.0000
  14.250   1.2783   0.08341   0.07679  -0.0450   0.0190   1.0000
  14.500   1.2718   0.08821   0.08181  -0.0460   0.0188   1.0000
  14.750   1.2612   0.09357   0.08746  -0.0477   0.0187   1.0000
  15.000   1.2489   0.09939   0.09357  -0.0500   0.0186   1.0000
  15.250   1.2349   0.10578   0.10025  -0.0529   0.0185   1.0000
  15.500   1.2198   0.11269   0.10741  -0.0565   0.0185   1.0000
  15.750   1.2040   0.12013   0.11505  -0.0607   0.0185   1.0000
  16.000   1.1875   0.12819   0.12332  -0.0656   0.0185   1.0000
  16.250   1.1708   0.13683   0.13215  -0.0711   0.0186   1.0000
  16.500   1.1539   0.14614   0.14161  -0.0773   0.0187   1.0000
  16.750   1.1375   0.15600   0.15159  -0.0838   0.0189   1.0000
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