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S2060 8% (s2060-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: S2060 8% (s2060-il)
Reynolds number: 100,000
Max Cl/Cd: 50.65 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s2060-il-100000-n5.txt
Download as CSV file: xf-s2060-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S2060 8%                                        
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.5054   0.09006   0.08497  -0.0248   1.0000   0.0238
  -9.000  -0.5082   0.08549   0.08046  -0.0270   1.0000   0.0237
  -8.750  -0.5124   0.08083   0.07587  -0.0293   1.0000   0.0234
  -8.500  -0.5199   0.07579   0.07091  -0.0320   1.0000   0.0233
  -8.250  -0.5311   0.07034   0.06556  -0.0357   1.0000   0.0230
  -8.000  -0.5401   0.06320   0.05842  -0.0415   1.0000   0.0227
  -7.750  -0.5488   0.05619   0.05129  -0.0451   1.0000   0.0223
  -7.500  -0.5560   0.04954   0.04439  -0.0471   1.0000   0.0221
  -7.250  -0.5580   0.04350   0.03795  -0.0478   1.0000   0.0220
  -7.000  -0.5537   0.03830   0.03224  -0.0477   1.0000   0.0223
  -6.750  -0.5441   0.03382   0.02717  -0.0471   1.0000   0.0229
  -6.500  -0.5299   0.03016   0.02292  -0.0461   1.0000   0.0238
  -6.250  -0.5123   0.02713   0.01928  -0.0450   1.0000   0.0252
  -6.000  -0.4937   0.02513   0.01706  -0.0440   1.0000   0.0273
  -5.750  -0.4733   0.02419   0.01597  -0.0432   1.0000   0.0314
  -5.500  -0.4520   0.02236   0.01375  -0.0420   1.0000   0.0361
  -5.250  -0.4311   0.02139   0.01269  -0.0412   1.0000   0.0421
  -5.000  -0.4095   0.02048   0.01161  -0.0403   1.0000   0.0504
  -4.750  -0.3871   0.01976   0.01065  -0.0394   1.0000   0.0589
  -4.500  -0.3655   0.01894   0.00987  -0.0386   1.0000   0.0667
  -4.250  -0.3432   0.01814   0.00893  -0.0377   1.0000   0.0739
  -4.000  -0.3209   0.01754   0.00826  -0.0369   1.0000   0.0826
  -3.750  -0.2985   0.01694   0.00764  -0.0361   1.0000   0.0919
  -3.500  -0.2758   0.01639   0.00705  -0.0354   1.0000   0.1023
  -3.250  -0.2531   0.01595   0.00663  -0.0347   1.0000   0.1183
  -3.000  -0.2299   0.01554   0.00624  -0.0341   0.9999   0.1392
  -2.750  -0.1946   0.01507   0.00590  -0.0361   0.9949   0.1777
  -2.500  -0.1605   0.01458   0.00565  -0.0379   0.9893   0.2396
  -2.250  -0.1255   0.01404   0.00551  -0.0399   0.9842   0.3386
  -2.000  -0.0942   0.01344   0.00542  -0.0410   0.9779   0.4744
  -1.750  -0.0629   0.01298   0.00552  -0.0414   0.9720   0.6307
  -1.500  -0.0346   0.01275   0.00558  -0.0409   0.9647   0.7393
  -1.250  -0.0037   0.01260   0.00560  -0.0406   0.9581   0.8286
  -1.000   0.0346   0.01248   0.00552  -0.0420   0.9524   0.9159
  -0.750   0.0880   0.01238   0.00533  -0.0472   0.9475   1.0000
  -0.500   0.1279   0.01239   0.00521  -0.0498   0.9406   1.0000
  -0.250   0.1639   0.01238   0.00509  -0.0516   0.9314   1.0000
   0.000   0.1988   0.01236   0.00500  -0.0530   0.9218   1.0000
   0.250   0.2375   0.01232   0.00490  -0.0551   0.9137   1.0000
   0.500   0.2699   0.01229   0.00483  -0.0559   0.9020   1.0000
   0.750   0.3021   0.01226   0.00477  -0.0566   0.8897   1.0000
   1.000   0.3341   0.01222   0.00471  -0.0571   0.8766   1.0000
   1.250   0.3654   0.01218   0.00468  -0.0575   0.8625   1.0000
   1.500   0.3960   0.01215   0.00464  -0.0577   0.8471   1.0000
   1.750   0.4262   0.01211   0.00460  -0.0577   0.8305   1.0000
   2.000   0.4546   0.01211   0.00463  -0.0574   0.8113   1.0000
   2.250   0.4826   0.01212   0.00464  -0.0570   0.7903   1.0000
   2.500   0.5102   0.01214   0.00467  -0.0564   0.7671   1.0000
   2.750   0.5376   0.01219   0.00471  -0.0558   0.7413   1.0000
   3.000   0.5642   0.01227   0.00480  -0.0551   0.7117   1.0000
   3.250   0.5903   0.01240   0.00488  -0.0543   0.6784   1.0000
   3.500   0.6159   0.01259   0.00500  -0.0533   0.6414   1.0000
   3.750   0.6406   0.01285   0.00516  -0.0523   0.5998   1.0000
   4.000   0.6645   0.01318   0.00540  -0.0512   0.5544   1.0000
   4.250   0.6878   0.01358   0.00567  -0.0500   0.5063   1.0000
   4.500   0.7104   0.01406   0.00599  -0.0489   0.4568   1.0000
   4.750   0.7325   0.01461   0.00638  -0.0477   0.4050   1.0000
   5.000   0.7540   0.01525   0.00686  -0.0466   0.3502   1.0000
   5.250   0.7736   0.01609   0.00735  -0.0454   0.2789   1.0000
   5.500   0.7925   0.01711   0.00792  -0.0442   0.1990   1.0000
   5.750   0.8119   0.01822   0.00860  -0.0433   0.1286   1.0000
   6.000   0.8321   0.01932   0.00946  -0.0423   0.0824   1.0000
   6.250   0.8515   0.02060   0.01059  -0.0411   0.0529   1.0000
   6.500   0.8711   0.02184   0.01188  -0.0398   0.0426   1.0000
   6.750   0.8903   0.02308   0.01316  -0.0386   0.0363   1.0000
   7.000   0.9102   0.02418   0.01441  -0.0374   0.0328   1.0000
   7.250   0.9295   0.02541   0.01580  -0.0361   0.0306   1.0000
   7.500   0.9484   0.02676   0.01726  -0.0348   0.0291   1.0000
   7.750   0.9670   0.02827   0.01887  -0.0336   0.0278   1.0000
   8.000   0.9854   0.03014   0.02082  -0.0324   0.0269   1.0000
   8.250   1.0052   0.03233   0.02321  -0.0314   0.0262   1.0000
   8.500   1.0254   0.03438   0.02554  -0.0303   0.0256   1.0000
   8.750   1.0438   0.03645   0.02796  -0.0291   0.0244   1.0000
   9.000   1.0599   0.03862   0.03047  -0.0278   0.0231   1.0000
   9.250   1.0735   0.04113   0.03332  -0.0264   0.0223   1.0000
   9.500   1.0836   0.04406   0.03663  -0.0247   0.0219   1.0000
   9.750   1.0895   0.04720   0.04016  -0.0228   0.0216   1.0000
  10.000   1.0906   0.05055   0.04390  -0.0207   0.0214   1.0000
  10.250   1.0862   0.05405   0.04777  -0.0185   0.0212   1.0000
  10.500   1.0748   0.05749   0.05156  -0.0158   0.0212   1.0000
  10.750   1.0586   0.06117   0.05553  -0.0137   0.0212   1.0000
  11.000   1.0395   0.06539   0.06000  -0.0129   0.0213   1.0000
  11.250   1.0175   0.07052   0.06533  -0.0139   0.0214   1.0000
  11.500   0.9928   0.07694   0.07197  -0.0170   0.0216   1.0000
  11.750   0.9653   0.08532   0.08054  -0.0228   0.0219   1.0000
  12.000   0.9339   0.09707   0.09243  -0.0318   0.0224   1.0000
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