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EPPLER STE 871-514 AIRFOIL (ste87151-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: EPPLER STE 871-514 AIRFOIL (ste87151-il)
Reynolds number: 200,000
Max Cl/Cd: 55.18 at α=6.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-ste87151-il-200000.txt
Download as CSV file: xf-ste87151-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER STE 871-514 AIRFOIL                      
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.5299   0.09681   0.09378  -0.0403   1.0020   0.0429
  -9.000  -0.5542   0.09194   0.08888  -0.0408   1.0020   0.0429
  -8.750  -0.5767   0.08813   0.08504  -0.0397   1.0020   0.0429
  -8.500  -0.6020   0.08498   0.08186  -0.0372   1.0020   0.0429
  -8.250  -0.6255   0.08235   0.07922  -0.0338   1.0020   0.0429
  -8.000  -0.6532   0.07854   0.07527  -0.0313   1.0020   0.0429
  -7.750  -0.6472   0.07546   0.07228  -0.0297   1.0020   0.0434
  -7.500  -0.6513   0.07267   0.06949  -0.0277   1.0020   0.0440
  -7.250  -0.6589   0.06944   0.06620  -0.0258   1.0020   0.0448
  -7.000  -0.6684   0.06544   0.06202  -0.0241   1.0020   0.0464
  -6.750  -0.7105   0.06292   0.05863  -0.0233   1.0020   0.0479
  -6.500  -0.7001   0.06041   0.05621  -0.0224   1.0020   0.0488
  -6.250  -0.6933   0.05682   0.05222  -0.0215   1.0020   0.0532
  -6.000  -0.6804   0.05483   0.05031  -0.0208   1.0020   0.0555
  -5.750  -0.6680   0.05180   0.04703  -0.0202   1.0020   0.0601
  -5.500  -0.6468   0.04892   0.04386  -0.0210   1.0006   0.0657
  -5.250  -0.6202   0.04633   0.04099  -0.0227   0.9984   0.0721
  -5.000  -0.5932   0.04414   0.03857  -0.0242   0.9966   0.0793
  -4.750  -0.5664   0.04208   0.03631  -0.0254   0.9935   0.0875
  -4.500  -0.5351   0.04039   0.03446  -0.0275   0.9910   0.0979
  -4.250  -0.4856   0.03160   0.02366  -0.0239   0.9913   0.0347
  -4.000  -0.4522   0.03038   0.02228  -0.0248   0.9901   0.0333
  -3.750  -0.4259   0.02905   0.02079  -0.0245   0.9867   0.0328
  -3.500  -0.3927   0.02828   0.01986  -0.0255   0.9844   0.0332
  -3.250  -0.3576   0.02788   0.01938  -0.0270   0.9828   0.0350
  -3.000  -0.3305   0.02741   0.01890  -0.0274   0.9776   0.0383
  -2.750  -0.2912   0.02715   0.01873  -0.0301   0.9750   0.0411
  -2.250  -0.2179   0.02636   0.01803  -0.0347   0.9604   0.0531
  -2.000  -0.1435   0.02443   0.01926  -0.0434   0.9404   0.7681
  -1.750  -0.1229   0.02587   0.02068  -0.0396   0.9337   0.8051
  -1.500  -0.1173   0.02635   0.02118  -0.0331   0.9227   0.8274
  -1.250  -0.1161   0.02682   0.02166  -0.0252   0.9118   0.8568
  -1.000  -0.1183   0.02727   0.02214  -0.0153   0.9061   0.8914
  -0.750  -0.1280   0.02681   0.02168  -0.0058   0.8945   0.9154
  -0.500  -0.1009   0.02694   0.02172  -0.0045   0.8910   0.9306
  -0.250  -0.0847   0.02666   0.02136  -0.0030   0.8812   0.9339
   0.000  -0.0480   0.02674   0.02132  -0.0053   0.8772   0.9353
   0.250  -0.0059   0.02694   0.02143  -0.0085   0.8748   0.9361
   0.500   0.0085   0.02664   0.02109  -0.0067   0.8645   0.9380
   0.750   0.0460   0.02664   0.02102  -0.0090   0.8609   0.9388
   1.000   0.0878   0.02672   0.02104  -0.0120   0.8586   0.9393
   1.250   0.1029   0.02651   0.02081  -0.0104   0.8480   0.9412
   1.500   0.1418   0.02646   0.02072  -0.0129   0.8446   0.9414
   1.750   0.1837   0.02642   0.02064  -0.0158   0.8425   0.9418
   2.000   0.1999   0.02628   0.02051  -0.0144   0.8318   0.9434
   2.250   0.2401   0.02610   0.02032  -0.0170   0.8286   0.9435
   2.500   0.2837   0.02586   0.02008  -0.0200   0.8265   0.9433
   2.750   0.3015   0.02571   0.01995  -0.0189   0.8155   0.9447
   3.000   0.3435   0.02529   0.01954  -0.0214   0.8125   0.9451
   3.250   0.3891   0.02473   0.01901  -0.0245   0.8106   0.9451
   3.500   0.4092   0.02446   0.01878  -0.0236   0.7987   0.9458
   3.750   0.4552   0.02363   0.01800  -0.0265   0.7961   0.9457
   4.000   0.4801   0.02317   0.01759  -0.0262   0.7846   0.9462
   4.250   0.5271   0.02193   0.01640  -0.0288   0.7810   0.9464
   4.500   0.5547   0.02115   0.01568  -0.0284   0.7685   0.9475
   4.750   0.5886   0.02014   0.01476  -0.0289   0.7581   0.9481
   5.000   0.6261   0.01897   0.01366  -0.0299   0.7500   0.9484
   5.250   0.6542   0.01835   0.01310  -0.0298   0.7350   0.9489
   5.500   0.6882   0.01752   0.01235  -0.0304   0.7178   0.9493
   5.750   0.7273   0.01651   0.01136  -0.0317   0.6924   0.9496
   6.000   0.7884   0.01483   0.00945  -0.0361   0.6392   0.9491
   6.250   0.8183   0.01483   0.00908  -0.0361   0.5580   0.9495
   6.500   0.8263   0.01564   0.00942  -0.0330   0.4746   0.9505
   6.750   0.8289   0.01672   0.01006  -0.0294   0.3945   0.9521
   7.000   0.8309   0.01788   0.01079  -0.0258   0.3158   0.9540
   7.250   0.8353   0.01914   0.01161  -0.0229   0.2396   0.9554
   7.500   0.8432   0.02040   0.01248  -0.0207   0.1817   0.9567
   7.750   0.8558   0.02146   0.01332  -0.0191   0.1497   0.9580
   8.000   0.8706   0.02240   0.01414  -0.0178   0.1320   0.9593
   8.250   0.8870   0.02329   0.01495  -0.0168   0.1205   0.9608
   8.500   0.9050   0.02411   0.01577  -0.0160   0.1120   0.9623
   8.750   0.9234   0.02496   0.01660  -0.0153   0.1054   0.9639
   9.000   0.9424   0.02586   0.01742  -0.0147   0.1000   0.9656
   9.250   0.9640   0.02659   0.01824  -0.0144   0.0953   0.9675
   9.500   0.9872   0.02751   0.01904  -0.0144   0.0914   0.9692
   9.750   1.0102   0.02823   0.01991  -0.0143   0.0876   0.9717
  10.000   1.0375   0.02909   0.02069  -0.0149   0.0842   0.9743
  10.250   1.0649   0.02997   0.02169  -0.0154   0.0814   0.9780
  10.500   1.0917   0.03082   0.02259  -0.0160   0.0785   0.9832
  10.750   1.1247   0.03184   0.02360  -0.0174   0.0759   0.9948
  11.000   1.1525   0.03297   0.02494  -0.0181   0.0736   0.9980
  11.250   1.1826   0.03411   0.02611  -0.0193   0.0712   0.9980
  11.500   1.2153   0.03566   0.02780  -0.0208   0.0691   0.9980
  11.750   1.2366   0.03712   0.02951  -0.0207   0.0671   0.9980
  12.000   1.2653   0.03842   0.03085  -0.0218   0.0649   0.9980
  12.250   1.2875   0.04033   0.03296  -0.0220   0.0631   0.9980
  12.500   1.2958   0.04203   0.03500  -0.0202   0.0613   0.9980
  12.750   1.3193   0.04326   0.03622  -0.0207   0.0592   0.9980
  13.000   1.3287   0.04529   0.03850  -0.0194   0.0576   0.9980
  13.250   1.3254   0.04738   0.04095  -0.0164   0.0561   0.9980
  13.500   1.3386   0.04874   0.04238  -0.0157   0.0543   0.9980
  13.750   1.3502   0.05068   0.04442  -0.0150   0.0526   0.9980
  14.000   1.3335   0.05345   0.04763  -0.0111   0.0516   0.9980
  14.250   1.3250   0.05603   0.05049  -0.0084   0.0504   0.9980
  14.500   1.3610   0.05642   0.05059  -0.0105   0.0482   0.9980
  14.750   1.3332   0.05995   0.05458  -0.0063   0.0477   0.9980
  15.000   1.3076   0.06391   0.05894  -0.0032   0.0471   0.9980
  15.250   1.2840   0.06809   0.06345  -0.0010   0.0464   0.9980
  15.500   1.2626   0.07241   0.06804   0.0004   0.0459   0.9980
  15.750   1.2486   0.07625   0.07206   0.0008   0.0451   0.9980
  16.000   1.2728   0.07651   0.07217   0.0004   0.0434   0.9980
  16.250   1.2407   0.08252   0.07849   0.0004   0.0432   0.9980
  16.500   1.2093   0.08926   0.08551  -0.0010   0.0432   0.9980
  16.750   1.1777   0.09684   0.09335  -0.0037   0.0432   0.9980
  17.000   1.1474   0.10511   0.10182  -0.0077   0.0434   0.9980
  17.250   1.1179   0.11418   0.11107  -0.0129   0.0435   0.9980
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