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S4095 (designed for the E-flite UMX ASK-21 scale RC sailplane) (s4095-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: S4095 (designed for the E-flite UMX ASK-21 scale RC sailplane) (s4095-il)
Reynolds number: 1,000,000
Max Cl/Cd: 72.55 at α=7.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s4095-il-1000000-n5.txt
Download as CSV file: xf-s4095-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S4095 (designed for the E-flite UMX ASK-21 scale
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.6788   0.14596   0.14438   0.0460   1.0007   0.0060
 -11.000  -0.6763   0.14128   0.13970   0.0440   1.0007   0.0061
  -9.500  -0.8605   0.03527   0.03240  -0.0220   1.0007   0.0074
  -9.250  -0.8353   0.03191   0.02868  -0.0240   1.0007   0.0074
  -9.000  -0.8084   0.02954   0.02604  -0.0254   1.0007   0.0075
  -8.750  -0.7807   0.02767   0.02393  -0.0266   1.0007   0.0075
  -8.500  -0.7525   0.02445   0.02029  -0.0283   1.0007   0.0077
  -8.250  -0.7237   0.02240   0.01797  -0.0295   1.0007   0.0078
  -8.000  -0.6947   0.02112   0.01653  -0.0303   1.0007   0.0080
  -7.750  -0.6655   0.02015   0.01543  -0.0310   1.0007   0.0081
  -7.500  -0.6362   0.01943   0.01464  -0.0316   1.0007   0.0082
  -7.250  -0.6068   0.01880   0.01394  -0.0322   1.0007   0.0084
  -7.000  -0.5774   0.01819   0.01326  -0.0328   1.0007   0.0086
  -6.750  -0.5477   0.01750   0.01248  -0.0333   1.0007   0.0088
  -6.500  -0.5180   0.01684   0.01173  -0.0339   1.0007   0.0090
  -6.250  -0.4882   0.01623   0.01105  -0.0344   1.0007   0.0092
  -6.000  -0.4583   0.01566   0.01041  -0.0350   1.0007   0.0095
  -5.750  -0.4284   0.01516   0.00985  -0.0355   1.0007   0.0098
  -5.500  -0.3985   0.01471   0.00934  -0.0360   1.0007   0.0100
  -5.250  -0.3693   0.01465   0.00919  -0.0363   0.9453   0.0102
  -5.000  -0.3453   0.01461   0.00896  -0.0351   0.8874   0.0104
  -4.750  -0.3176   0.01446   0.00862  -0.0349   0.8461   0.0106
  -4.500  -0.2887   0.01429   0.00828  -0.0351   0.8114   0.0107
  -4.250  -0.2593   0.01412   0.00796  -0.0354   0.7813   0.0108
  -4.000  -0.2294   0.01377   0.00746  -0.0359   0.7545   0.0112
  -3.750  -0.1995   0.01354   0.00711  -0.0363   0.7305   0.0117
  -3.500  -0.1697   0.01338   0.00685  -0.0368   0.7079   0.0122
  -3.250  -0.1398   0.01326   0.00664  -0.0372   0.6871   0.0129
  -3.000  -0.1099   0.01314   0.00644  -0.0377   0.6675   0.0135
  -2.750  -0.0800   0.01305   0.00626  -0.0381   0.6495   0.0141
  -2.500  -0.0501   0.01298   0.00610  -0.0385   0.6325   0.0147
  -2.250  -0.0202   0.01290   0.00595  -0.0390   0.6163   0.0159
  -2.000   0.0098   0.01282   0.00583  -0.0394   0.6012   0.0182
  -1.750   0.0398   0.01269   0.00572  -0.0399   0.5869   0.0350
  -1.500   0.0698   0.01257   0.00564  -0.0405   0.5724   0.0586
  -1.250   0.0999   0.01245   0.00558  -0.0410   0.5584   0.0880
  -1.000   0.1299   0.01236   0.00554  -0.0416   0.5448   0.1198
  -0.750   0.1599   0.01224   0.00551  -0.0422   0.5308   0.1639
  -0.500   0.1900   0.01215   0.00550  -0.0427   0.5164   0.2059
  -0.250   0.2200   0.01207   0.00549  -0.0433   0.5017   0.2515
   0.000   0.2502   0.01190   0.00552  -0.0441   0.4863   0.3366
   0.250   0.2805   0.01164   0.00560  -0.0449   0.4707   0.4682
   0.500   0.3107   0.01141   0.00569  -0.0457   0.4545   0.6021
   0.750   0.3406   0.01123   0.00579  -0.0463   0.4379   0.7134
   1.000   0.3676   0.01093   0.00594  -0.0461   0.4225   0.8709
   1.250   0.3910   0.01038   0.00551  -0.0448   0.4071   0.9993
   1.500   0.4209   0.01048   0.00553  -0.0452   0.3916   0.9993
   1.750   0.4507   0.01060   0.00555  -0.0457   0.3743   0.9993
   2.000   0.4804   0.01072   0.00559  -0.0462   0.3580   0.9993
   2.250   0.5102   0.01084   0.00563  -0.0467   0.3425   0.9993
   2.500   0.5399   0.01098   0.00568  -0.0471   0.3269   0.9993
   2.750   0.5695   0.01111   0.00575  -0.0476   0.3124   0.9993
   3.000   0.5992   0.01125   0.00582  -0.0481   0.2973   0.9993
   3.250   0.6288   0.01140   0.00590  -0.0486   0.2828   0.9993
   3.500   0.6583   0.01156   0.00599  -0.0490   0.2686   0.9993
   3.750   0.6878   0.01173   0.00609  -0.0495   0.2541   0.9993
   4.000   0.7173   0.01190   0.00620  -0.0500   0.2402   0.9993
   4.250   0.7467   0.01209   0.00632  -0.0505   0.2260   0.9993
   4.500   0.7761   0.01227   0.00645  -0.0509   0.2128   0.9993
   4.750   0.8054   0.01247   0.00660  -0.0514   0.1994   0.9993
   5.000   0.8347   0.01266   0.00674  -0.0518   0.1891   0.9993
   5.250   0.8639   0.01287   0.00691  -0.0523   0.1769   0.9993
   5.500   0.8930   0.01310   0.00709  -0.0528   0.1648   0.9993
   6.000   0.9511   0.01358   0.00747  -0.0537   0.1424   0.9993
   6.250   0.9800   0.01385   0.00770  -0.0541   0.1295   0.9993
   6.500   1.0087   0.01419   0.00795  -0.0546   0.1146   0.9993
   6.750   1.0374   0.01450   0.00821  -0.0550   0.1019   0.9993
   7.000   1.0660   0.01482   0.00848  -0.0555   0.0907   0.9993
   7.250   1.0946   0.01515   0.00877  -0.0559   0.0807   0.9993
   7.500   1.1230   0.01548   0.00907  -0.0563   0.0722   0.9993
   7.750   1.1512   0.01587   0.00940  -0.0567   0.0624   0.9993
   8.000   1.1793   0.01629   0.00978  -0.0571   0.0527   0.9993
   8.250   1.2073   0.01668   0.01015  -0.0575   0.0450   0.9993
   8.500   1.2351   0.01715   0.01057  -0.0579   0.0365   0.9993
   8.750   1.2627   0.01760   0.01100  -0.0582   0.0303   0.9993
   9.000   1.2902   0.01809   0.01146  -0.0586   0.0244   0.9993
   9.250   1.3173   0.01866   0.01201  -0.0589   0.0177   0.9993
   9.500   1.3433   0.01955   0.01283  -0.0592   0.0074   0.9993
   9.750   1.3699   0.02015   0.01345  -0.0594   0.0055   0.9993
  10.000   1.3966   0.02067   0.01402  -0.0596   0.0049   0.9993
  10.250   1.4230   0.02124   0.01463  -0.0598   0.0045   0.9993
  10.500   1.4489   0.02188   0.01534  -0.0600   0.0040   0.9993
  10.750   1.4745   0.02255   0.01608  -0.0601   0.0037   0.9993
  11.000   1.5000   0.02315   0.01674  -0.0601   0.0036   0.9993
  11.250   1.5250   0.02380   0.01745  -0.0602   0.0034   0.9993
  11.500   1.5496   0.02448   0.01821  -0.0602   0.0033   0.9993
  11.750   1.5736   0.02522   0.01902  -0.0601   0.0032   0.9993
  12.000   1.5969   0.02602   0.01991  -0.0599   0.0031   0.9993
  12.250   1.6195   0.02686   0.02083  -0.0597   0.0030   0.9993
  12.500   1.6412   0.02776   0.02182  -0.0594   0.0029   0.9993
  12.750   1.6619   0.02873   0.02287  -0.0589   0.0028   0.9993
  13.000   1.6812   0.02979   0.02403  -0.0583   0.0027   0.9993
  13.250   1.6989   0.03096   0.02529  -0.0576   0.0026   0.9993
  13.500   1.7146   0.03226   0.02669  -0.0565   0.0025   0.9993
  13.750   1.7272   0.03374   0.02830  -0.0552   0.0025   0.9993
  14.000   1.7357   0.03549   0.03017  -0.0534   0.0024   0.9993
  14.250   1.7380   0.03757   0.03240  -0.0510   0.0023   0.9993
  14.500   1.7239   0.04037   0.03534  -0.0466   0.0023   0.9993
  14.750   1.7100   0.04415   0.03928  -0.0444   0.0023   0.9993
  15.000   1.6971   0.04892   0.04423  -0.0445   0.0023   0.9993
  15.250   1.6837   0.05453   0.05001  -0.0459   0.0022   0.9993
  15.750   1.6493   0.06800   0.06382  -0.0509   0.0022   0.9993
  16.000   1.6275   0.07566   0.07165  -0.0538   0.0022   0.9993
  16.250   1.6016   0.08418   0.08034  -0.0572   0.0022   0.9993
  16.500   1.5752   0.09282   0.08914  -0.0607   0.0022   0.9993
  16.750   1.5480   0.10177   0.09824  -0.0643   0.0022   0.9993
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