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EPPLER STF 863-615 AIRFOIL (stf86361-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: EPPLER STF 863-615 AIRFOIL (stf86361-il)
Reynolds number: 50,000
Max Cl/Cd: 23.75 at α=7.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-stf86361-il-50000-n5.txt
Download as CSV file: xf-stf86361-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER STF 863-615 AIRFOIL                      
  
 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  -0.5220   0.12950   0.12346  -0.0281   1.0019   0.1589
  -9.500  -0.5230   0.12623   0.12022  -0.0273   1.0019   0.1617
  -9.000  -0.4919   0.09855   0.09289  -0.0463   0.9960   0.0561
  -8.750  -0.5284   0.09421   0.08850  -0.0474   0.9939   0.0565
  -8.250  -0.6159   0.09436   0.08844  -0.0421   0.9983   0.0608
  -7.750  -0.6291   0.08382   0.07750  -0.0471   0.9937   0.0533
  -7.500  -0.6272   0.07902   0.07252  -0.0486   0.9915   0.0513
  -7.250  -0.6217   0.07392   0.06711  -0.0507   0.9893   0.0489
  -7.000  -0.6089   0.06791   0.06035  -0.0540   0.9870   0.0453
  -6.750  -0.5888   0.06418   0.05597  -0.0557   0.9846   0.0433
  -6.500  -0.5698   0.06025   0.05173  -0.0568   0.9825   0.0425
  -6.250  -0.5470   0.05664   0.04772  -0.0582   0.9805   0.0419
  -6.000  -0.5207   0.05342   0.04403  -0.0597   0.9785   0.0414
  -5.750  -0.4911   0.05079   0.04084  -0.0612   0.9765   0.0421
  -5.500  -0.4586   0.04890   0.03828  -0.0627   0.9746   0.0437
  -5.250  -0.4320   0.04652   0.03563  -0.0631   0.9725   0.0446
  -5.000  -0.4064   0.04477   0.03356  -0.0627   0.9701   0.0449
  -4.750  -0.3811   0.04336   0.03197  -0.0620   0.9678   0.0455
  -4.500  -0.3565   0.04240   0.03089  -0.0607   0.9656   0.0463
  -4.250  -0.3320   0.04180   0.03019  -0.0595   0.9634   0.0488
  -4.000  -0.3050   0.04147   0.02969  -0.0591   0.9613   0.0529
  -3.750  -0.2843   0.04088   0.02893  -0.0577   0.9579   0.0551
  -3.500  -0.2593   0.04034   0.02819  -0.0575   0.9548   0.0568
  -3.250  -0.2299   0.03969   0.02741  -0.0589   0.9521   0.0602
  -3.000  -0.1967   0.03934   0.02689  -0.0610   0.9495   0.0654
  -2.750  -0.1627   0.03894   0.02644  -0.0635   0.9466   0.0787
  -2.250  -0.1222   0.03920   0.02926  -0.0599   0.9390   0.6905
  -2.000  -0.1076   0.04031   0.03022  -0.0554   0.9351   0.7305
  -1.750  -0.1016   0.04054   0.03036  -0.0500   0.9294   0.7512
  -1.500  -0.0779   0.04087   0.03044  -0.0494   0.9251   0.7628
  -1.250  -0.0596   0.04135   0.03077  -0.0467   0.9212   0.7864
  -1.000  -0.0545   0.04128   0.03062  -0.0416   0.9152   0.8058
  -0.750  -0.0373   0.04144   0.03066  -0.0393   0.9109   0.8226
  -0.500  -0.0215   0.04154   0.03064  -0.0368   0.9064   0.8398
  -0.250  -0.0022   0.04160   0.03058  -0.0359   0.9010   0.8481
   0.000   0.0298   0.04196   0.03075  -0.0379   0.8970   0.8499
   0.250   0.0575   0.04227   0.03093  -0.0392   0.8924   0.8517
   0.500   0.0836   0.04255   0.03112  -0.0403   0.8871   0.8535
   0.750   0.1172   0.04302   0.03148  -0.0427   0.8830   0.8549
   1.000   0.1434   0.04338   0.03176  -0.0438   0.8776   0.8565
   1.250   0.1717   0.04381   0.03213  -0.0454   0.8723   0.8581
   1.500   0.2056   0.04431   0.03260  -0.0477   0.8683   0.8595
   1.750   0.2264   0.04460   0.03289  -0.0478   0.8611   0.8607
   2.000   0.2595   0.04503   0.03331  -0.0499   0.8555   0.8621
   2.250   0.2845   0.04528   0.03357  -0.0505   0.8470   0.8637
   2.500   0.3202   0.04566   0.03398  -0.0530   0.8409   0.8654
   2.750   0.3431   0.04596   0.03434  -0.0533   0.8321   0.8670
   3.000   0.3786   0.04640   0.03484  -0.0558   0.8269   0.8683
   3.250   0.3999   0.04679   0.03531  -0.0560   0.8183   0.8696
   3.500   0.4349   0.04725   0.03586  -0.0584   0.8132   0.8712
   3.750   0.4550   0.04767   0.03642  -0.0585   0.8042   0.8730
   4.000   0.4892   0.04803   0.03691  -0.0605   0.7992   0.8749
   4.250   0.5074   0.04845   0.03747  -0.0601   0.7895   0.8768
   4.500   0.5349   0.04884   0.03807  -0.0612   0.7823   0.8787
   4.750   0.5625   0.04923   0.03863  -0.0622   0.7745   0.8804
   5.000   0.5849   0.04966   0.03924  -0.0626   0.7648   0.8822
   5.250   0.6152   0.04981   0.03961  -0.0638   0.7557   0.8841
   5.500   0.6497   0.04967   0.03975  -0.0654   0.7463   0.8863
   5.750   0.6733   0.04964   0.03997  -0.0652   0.7339   0.8888
   6.000   0.6963   0.04973   0.04032  -0.0651   0.7217   0.8915
   6.250   0.7209   0.04979   0.04066  -0.0652   0.7094   0.8945
   6.500   0.7478   0.04967   0.04085  -0.0654   0.6967   0.8976
   6.750   0.7758   0.04937   0.04095  -0.0655   0.6827   0.9007
   7.000   0.8033   0.04881   0.04076  -0.0652   0.6676   0.9040
   7.250   0.8335   0.04787   0.04024  -0.0648   0.6512   0.9076
   7.500   0.8700   0.04432   0.03713  -0.0623   0.6177   0.9119
   7.750   0.9035   0.03805   0.02945  -0.0542   0.3446   0.9162
   8.000   0.8946   0.04056   0.03091  -0.0500   0.2066   0.9207
   8.250   0.8883   0.04347   0.03305  -0.0470   0.1113   0.9262
   8.500   0.8901   0.04583   0.03513  -0.0447   0.0795   0.9335
   8.750   0.8960   0.04774   0.03707  -0.0428   0.0677   0.9454
   9.000   0.9005   0.04923   0.03868  -0.0406   0.0613   0.9960
   9.250   0.9134   0.05121   0.04076  -0.0401   0.0545   0.9981
   9.500   0.9297   0.05296   0.04269  -0.0394   0.0494   0.9981
   9.750   0.9544   0.05431   0.04430  -0.0391   0.0460   0.9981
  10.000   0.9962   0.05530   0.04542  -0.0399   0.0427   0.9981
  10.250   1.0627   0.05715   0.04753  -0.0430   0.0395   0.9981
  10.500   1.0931   0.05980   0.05070  -0.0436   0.0365   0.9981
  10.750   1.1164   0.06294   0.05424  -0.0438   0.0346   0.9981
  11.000   1.1319   0.06656   0.05828  -0.0432   0.0339   0.9981
  11.250   1.1376   0.07030   0.06242  -0.0419   0.0335   0.9981
  11.500   1.1361   0.07414   0.06665  -0.0401   0.0333   0.9981
  11.750   1.1291   0.07811   0.07098  -0.0382   0.0331   0.9981
  12.000   1.1174   0.08227   0.07548  -0.0364   0.0331   0.9981
  12.250   1.1021   0.08666   0.08020  -0.0349   0.0332   0.9981
  12.500   1.0842   0.09133   0.08516  -0.0338   0.0332   0.9981
  12.750   1.0638   0.09640   0.09051  -0.0335   0.0334   0.9981
  13.000   1.0416   0.10202   0.09640  -0.0341   0.0336   0.9981
  13.250   1.0182   0.10835   0.10296  -0.0359   0.0340   0.9981
  13.500   0.9943   0.11557   0.11038  -0.0391   0.0344   0.9981
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