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S3021-095-84 (s3021-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: S3021-095-84 (s3021-il)
Reynolds number: 100,000
Max Cl/Cd: 53.71 at α=6.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s3021-il-100000.txt
Download as CSV file: xf-s3021-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S3021-095-84                                    
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.3970   0.10551   0.10059  -0.0228   1.0000   0.0898
  -9.000  -0.4136   0.10389   0.09910  -0.0284   1.0000   0.0917
  -8.750  -0.4298   0.10176   0.09709  -0.0332   1.0000   0.0921
  -8.500  -0.3899   0.09522   0.09045  -0.0260   1.0000   0.0960
  -8.250  -0.3846   0.09223   0.08749  -0.0262   1.0000   0.0996
  -8.000  -0.3887   0.08946   0.08480  -0.0281   1.0000   0.1033
  -7.750  -0.4126   0.08731   0.08282  -0.0336   1.0000   0.1055
  -7.500  -0.4210   0.08305   0.07863  -0.0375   1.0000   0.1068
  -7.250  -0.3990   0.08002   0.07563  -0.0306   1.0000   0.1102
  -7.000  -0.3972   0.07721   0.07287  -0.0307   1.0000   0.1144
  -6.750  -0.4271   0.07453   0.07003  -0.0414   1.0000   0.1203
  -6.500  -0.4095   0.07017   0.06593  -0.0354   1.0000   0.1226
  -6.250  -0.4033   0.06804   0.06387  -0.0324   1.0000   0.1276
  -6.000  -0.4198   0.06494   0.06059  -0.0368   1.0000   0.1353
  -5.750  -0.4120   0.06265   0.05852  -0.0313   1.0000   0.1389
  -5.500  -0.4217   0.06034   0.05603  -0.0326   1.0000   0.1498
  -5.250  -0.4186   0.05814   0.05399  -0.0285   1.0000   0.1527
  -5.000  -0.4202   0.05592   0.05162  -0.0287   1.0000   0.1648
  -4.750  -0.4160   0.05389   0.04971  -0.0255   1.0000   0.1689
  -4.250  -0.3364   0.03965   0.03343  -0.0393   0.9889   0.1060
  -4.000  -0.2963   0.03163   0.02477  -0.0417   0.9845   0.0717
  -3.750  -0.2550   0.02831   0.02049  -0.0435   0.9766   0.0638
  -3.500  -0.2117   0.02567   0.01740  -0.0464   0.9707   0.0624
  -3.250  -0.1730   0.02399   0.01531  -0.0482   0.9617   0.0638
  -3.000  -0.1313   0.02223   0.01336  -0.0508   0.9549   0.0675
  -2.750  -0.0919   0.02092   0.01204  -0.0528   0.9464   0.0723
  -2.500  -0.0538   0.01981   0.01087  -0.0545   0.9379   0.0796
  -2.250  -0.0129   0.01852   0.00978  -0.0568   0.9305   0.1096
  -2.000   0.0729   0.01476   0.00934  -0.0660   0.9363   1.0000
  -1.750   0.1265   0.01467   0.00880  -0.0711   0.9294   1.0000
  -1.500   0.1649   0.01463   0.00846  -0.0733   0.9179   1.0000
  -1.250   0.2034   0.01459   0.00817  -0.0754   0.9072   1.0000
  -1.000   0.2458   0.01447   0.00783  -0.0781   0.8985   1.0000
  -0.750   0.2793   0.01444   0.00761  -0.0790   0.8871   1.0000
  -0.500   0.3084   0.01448   0.00750  -0.0790   0.8747   1.0000
  -0.250   0.3366   0.01453   0.00741  -0.0789   0.8627   1.0000
   0.000   0.3643   0.01458   0.00734  -0.0785   0.8512   1.0000
   0.250   0.3924   0.01461   0.00724  -0.0781   0.8403   1.0000
   0.500   0.4176   0.01470   0.00722  -0.0772   0.8283   1.0000
   0.750   0.4406   0.01486   0.00730  -0.0759   0.8154   1.0000
   1.000   0.4639   0.01502   0.00738  -0.0747   0.8027   1.0000
   1.250   0.4875   0.01518   0.00747  -0.0735   0.7903   1.0000
   1.500   0.5115   0.01532   0.00754  -0.0724   0.7783   1.0000
   1.750   0.5361   0.01544   0.00760  -0.0712   0.7665   1.0000
   2.000   0.5610   0.01555   0.00764  -0.0701   0.7548   1.0000
   2.250   0.5841   0.01575   0.00780  -0.0689   0.7415   1.0000
   2.500   0.6076   0.01594   0.00797  -0.0678   0.7284   1.0000
   2.750   0.6313   0.01612   0.00815  -0.0666   0.7152   1.0000
   3.000   0.6552   0.01630   0.00831  -0.0655   0.7019   1.0000
   3.250   0.6794   0.01647   0.00846  -0.0644   0.6884   1.0000
   3.500   0.7037   0.01663   0.00861  -0.0633   0.6747   1.0000
   3.750   0.7280   0.01678   0.00878  -0.0622   0.6606   1.0000
   4.000   0.7523   0.01692   0.00893  -0.0611   0.6459   1.0000
   4.250   0.7767   0.01705   0.00907  -0.0600   0.6307   1.0000
   4.500   0.8011   0.01718   0.00920  -0.0590   0.6149   1.0000
   4.750   0.8256   0.01729   0.00934  -0.0579   0.5986   1.0000
   5.000   0.8503   0.01738   0.00942  -0.0568   0.5819   1.0000
   5.250   0.8739   0.01753   0.00960  -0.0556   0.5635   1.0000
   5.500   0.8970   0.01768   0.00979  -0.0544   0.5436   1.0000
   5.750   0.9213   0.01779   0.00991  -0.0532   0.5241   1.0000
   6.000   0.9435   0.01800   0.01017  -0.0519   0.5017   1.0000
   6.250   0.9670   0.01818   0.01029  -0.0507   0.4801   1.0000
   6.500   0.9881   0.01846   0.01063  -0.0493   0.4549   1.0000
   6.750   1.0093   0.01879   0.01100  -0.0479   0.4295   1.0000
   7.000   1.0299   0.01919   0.01137  -0.0464   0.4033   1.0000
   7.250   1.0499   0.01968   0.01183  -0.0449   0.3767   1.0000
   7.500   1.0689   0.02025   0.01236  -0.0434   0.3494   1.0000
   7.750   1.0871   0.02092   0.01300  -0.0418   0.3219   1.0000
   8.000   1.1043   0.02170   0.01371  -0.0401   0.2946   1.0000
   8.250   1.1196   0.02251   0.01448  -0.0382   0.2663   1.0000
   8.500   1.1326   0.02331   0.01526  -0.0362   0.2373   1.0000
   8.750   1.1437   0.02411   0.01606  -0.0340   0.2080   1.0000
   9.000   1.1537   0.02500   0.01695  -0.0318   0.1794   1.0000
   9.250   1.1621   0.02603   0.01801  -0.0295   0.1497   1.0000
   9.500   1.1659   0.02750   0.01936  -0.0268   0.1172   1.0000
   9.750   1.1582   0.02982   0.02140  -0.0227   0.0800   1.0000
  10.000   1.1504   0.03232   0.02371  -0.0188   0.0641   1.0000
  10.250   1.1492   0.03457   0.02595  -0.0159   0.0550   1.0000
  10.500   1.1547   0.03680   0.02826  -0.0136   0.0500   1.0000
  10.750   1.1630   0.03890   0.03039  -0.0118   0.0461   1.0000
  11.000   1.1779   0.04165   0.03309  -0.0106   0.0426   1.0000
  11.250   1.1895   0.04381   0.03552  -0.0092   0.0403   1.0000
  11.500   1.1996   0.04616   0.03808  -0.0079   0.0382   1.0000
  11.750   1.2075   0.04871   0.04081  -0.0066   0.0365   1.0000
  12.000   1.2163   0.05168   0.04402  -0.0055   0.0357   1.0000
  12.250   1.2207   0.05494   0.04752  -0.0044   0.0352   1.0000
  12.500   1.2199   0.05855   0.05139  -0.0034   0.0349   1.0000
  12.750   1.2131   0.06231   0.05545  -0.0026   0.0349   1.0000
  13.000   1.2021   0.06636   0.05979  -0.0022   0.0350   1.0000
  13.250   1.1868   0.07097   0.06470  -0.0025   0.0351   1.0000
  13.500   1.1677   0.07618   0.07022  -0.0037   0.0355   1.0000
  13.750   1.1455   0.08214   0.07645  -0.0059   0.0358   1.0000
  14.000   1.1174   0.08929   0.08389  -0.0095   0.0363   1.0000
  14.250   1.0827   0.09833   0.09322  -0.0151   0.0371   1.0000
  14.500   1.0467   0.10902   0.10410  -0.0223   0.0380   1.0000
  14.750   1.0073   0.12239   0.11763  -0.0316   0.0393   1.0000
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