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S8025 (8%) (s8025-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: S8025 (8%) (s8025-il)
Reynolds number: 50,000
Max Cl/Cd: 26.62 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s8025-il-50000-n5.txt
Download as CSV file: xf-s8025-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S8025 (8%)                                      
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.6850   0.09662   0.08985   0.0113   1.0000   0.0362
  -9.500  -0.6888   0.09055   0.08383   0.0078   1.0000   0.0360
  -9.250  -0.6947   0.08406   0.07739   0.0034   1.0000   0.0357
  -9.000  -0.7032   0.07776   0.07110  -0.0015   1.0000   0.0354
  -8.750  -0.7157   0.07223   0.06555  -0.0052   1.0000   0.0351
  -8.500  -0.7265   0.06656   0.05974  -0.0083   1.0000   0.0349
  -8.250  -0.7329   0.06119   0.05414  -0.0104   1.0000   0.0348
  -8.000  -0.7353   0.05583   0.04842  -0.0118   1.0000   0.0350
  -7.750  -0.7320   0.05079   0.04289  -0.0125   1.0000   0.0354
  -7.500  -0.7232   0.04615   0.03769  -0.0126   1.0000   0.0358
  -7.250  -0.7100   0.04200   0.03309  -0.0124   1.0000   0.0367
  -7.000  -0.6930   0.03896   0.02981  -0.0120   1.0000   0.0385
  -6.750  -0.6737   0.03643   0.02696  -0.0115   1.0000   0.0423
  -6.500  -0.6521   0.03358   0.02343  -0.0107   1.0000   0.0470
  -6.250  -0.6309   0.03120   0.02101  -0.0100   1.0000   0.0519
  -6.000  -0.6081   0.02912   0.01866  -0.0091   1.0000   0.0616
  -5.750  -0.5854   0.02728   0.01673  -0.0083   1.0000   0.0752
  -5.500  -0.5624   0.02565   0.01501  -0.0076   1.0000   0.0965
  -5.250  -0.5393   0.02424   0.01359  -0.0069   1.0000   0.1249
  -5.000  -0.5160   0.02300   0.01243  -0.0063   1.0000   0.1565
  -4.750  -0.4920   0.02186   0.01129  -0.0057   1.0000   0.1899
  -4.500  -0.4675   0.02083   0.01031  -0.0052   1.0000   0.2274
  -4.250  -0.4429   0.01989   0.00949  -0.0047   1.0000   0.2717
  -4.000  -0.4194   0.01907   0.00880  -0.0040   1.0000   0.3239
  -3.750  -0.3963   0.01831   0.00820  -0.0030   1.0000   0.3815
  -3.500  -0.3737   0.01763   0.00775  -0.0018   1.0000   0.4435
  -3.250  -0.3514   0.01706   0.00738  -0.0003   1.0000   0.5100
  -3.000  -0.3297   0.01656   0.00710   0.0015   1.0000   0.5769
  -2.750  -0.3081   0.01613   0.00685   0.0036   1.0000   0.6425
  -2.500  -0.2864   0.01576   0.00661   0.0059   1.0000   0.7062
  -2.250  -0.2631   0.01545   0.00641   0.0079   1.0000   0.7688
  -2.000  -0.2334   0.01521   0.00621   0.0088   1.0000   0.8313
  -1.750  -0.1912   0.01503   0.00594   0.0070   1.0000   0.8934
  -1.500  -0.1367   0.01487   0.00561   0.0023   1.0000   0.9477
  -1.250  -0.0776   0.01465   0.00518  -0.0041   1.0000   0.9939
  -1.000  -0.0543   0.01449   0.00492  -0.0042   1.0000   1.0000
  -0.750  -0.0354   0.01438   0.00474  -0.0031   1.0000   1.0000
  -0.500  -0.0162   0.01433   0.00464  -0.0021   1.0000   1.0000
  -0.250   0.0031   0.01431   0.00459  -0.0011   1.0000   1.0000
   0.000   0.0221   0.01433   0.00461   0.0000   1.0000   1.0000
   0.250   0.0403   0.01441   0.00471   0.0011   1.0000   1.0000
   0.500   0.0898   0.01457   0.00489  -0.0038   0.9498   1.0000
   0.750   0.1427   0.01474   0.00504  -0.0085   0.8870   1.0000
   1.000   0.1835   0.01494   0.00513  -0.0103   0.8241   1.0000
   1.250   0.2118   0.01522   0.00522  -0.0095   0.7680   1.0000
   1.500   0.2352   0.01554   0.00536  -0.0079   0.7182   1.0000
   1.750   0.2579   0.01588   0.00550  -0.0062   0.6733   1.0000
   2.000   0.2807   0.01623   0.00568  -0.0047   0.6318   1.0000
   2.250   0.3040   0.01660   0.00588  -0.0034   0.5934   1.0000
   2.500   0.3276   0.01698   0.00615  -0.0022   0.5568   1.0000
   2.750   0.3516   0.01737   0.00641  -0.0012   0.5229   1.0000
   3.000   0.3759   0.01778   0.00673  -0.0003   0.4899   1.0000
   3.250   0.4004   0.01821   0.00708   0.0006   0.4584   1.0000
   3.500   0.4249   0.01866   0.00749   0.0014   0.4284   1.0000
   3.750   0.4496   0.01914   0.00792   0.0021   0.3998   1.0000
   4.000   0.4745   0.01965   0.00840   0.0027   0.3727   1.0000
   4.250   0.4997   0.02020   0.00897   0.0033   0.3468   1.0000
   4.500   0.5248   0.02078   0.00952   0.0038   0.3229   1.0000
   4.750   0.5498   0.02140   0.01019   0.0043   0.2987   1.0000
   5.000   0.5746   0.02206   0.01088   0.0049   0.2755   1.0000
   5.250   0.5989   0.02276   0.01162   0.0054   0.2541   1.0000
   5.500   0.6233   0.02351   0.01246   0.0060   0.2322   1.0000
   5.750   0.6472   0.02431   0.01329   0.0065   0.2125   1.0000
   6.000   0.6711   0.02522   0.01427   0.0071   0.1944   1.0000
   6.250   0.6948   0.02620   0.01539   0.0076   0.1761   1.0000
   6.500   0.7180   0.02728   0.01663   0.0082   0.1599   1.0000
   6.750   0.7408   0.02849   0.01796   0.0088   0.1453   1.0000
   7.000   0.7631   0.02969   0.01929   0.0093   0.1310   1.0000
   7.250   0.7851   0.03122   0.02102   0.0099   0.1193   1.0000
   7.500   0.8060   0.03272   0.02271   0.0105   0.1076   1.0000
   7.750   0.8268   0.03440   0.02446   0.0111   0.0997   1.0000
   8.000   0.8462   0.03657   0.02709   0.0116   0.0913   1.0000
   8.250   0.8639   0.03872   0.02951   0.0121   0.0838   1.0000
   8.500   0.8805   0.04124   0.03236   0.0126   0.0783   1.0000
   8.750   0.8970   0.04373   0.03494   0.0131   0.0746   1.0000
   9.000   0.9026   0.04819   0.04014   0.0132   0.0709   1.0000
   9.250   0.9081   0.05173   0.04406   0.0131   0.0669   1.0000
   9.500   0.9217   0.05353   0.04585   0.0136   0.0631   1.0000
   9.750   0.9162   0.05852   0.05121   0.0129   0.0620   1.0000
  10.000   0.8997   0.06429   0.05733   0.0111   0.0617   1.0000
  10.250   0.8771   0.07010   0.06330   0.0084   0.0618   1.0000
  10.500   0.8537   0.07730   0.07055   0.0029   0.0622   1.0000
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