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S4095 (designed for the E-flite UMX ASK-21 scale RC sailplane) (s4095-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: S4095 (designed for the E-flite UMX ASK-21 scale RC sailplane) (s4095-il)
Reynolds number: 200,000
Max Cl/Cd: 53.38 at α=7°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s4095-il-200000.txt
Download as CSV file: xf-s4095-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.6112   0.11907   0.11569   0.0269   1.0007   0.0432
  -8.750  -0.6174   0.11366   0.11032   0.0222   1.0007   0.0446
  -8.500  -0.6276   0.10795   0.10467   0.0177   1.0007   0.0450
  -8.250  -0.6152   0.10531   0.10203   0.0199   1.0007   0.0458
  -8.000  -0.6151   0.10148   0.09822   0.0185   1.0007   0.0468
  -7.750  -0.6141   0.09591   0.09267   0.0126   1.0007   0.0485
  -7.500  -0.6092   0.08817   0.08490   0.0029   1.0007   0.0497
  -7.250  -0.5213   0.07931   0.07625  -0.0018   1.0007   0.0557
  -7.000  -0.5819   0.07679   0.07339  -0.0078   1.0007   0.0546
  -6.750  -0.5597   0.06976   0.06612  -0.0160   1.0007   0.0590
  -6.500  -0.5431   0.06607   0.06243  -0.0166   1.0007   0.0601
  -6.250  -0.5153   0.05900   0.05499  -0.0237   1.0007   0.0651
  -6.000  -0.4875   0.05469   0.05038  -0.0273   1.0007   0.0704
  -5.750  -0.4647   0.05108   0.04681  -0.0283   1.0007   0.0718
  -5.500  -0.4342   0.04674   0.04214  -0.0316   1.0007   0.0780
  -5.250  -0.3878   0.03421   0.02834  -0.0368   1.0007   0.0506
  -5.000  -0.3469   0.02642   0.01928  -0.0386   1.0007   0.0383
  -4.750  -0.3148   0.02437   0.01681  -0.0394   1.0007   0.0396
  -4.500  -0.2832   0.02242   0.01454  -0.0399   1.0007   0.0397
  -4.250  -0.2520   0.02082   0.01270  -0.0403   1.0007   0.0401
  -4.000  -0.2216   0.01947   0.01128  -0.0407   1.0007   0.0412
  -3.750  -0.1914   0.01845   0.01029  -0.0412   1.0007   0.0431
  -3.500  -0.1611   0.01752   0.00937  -0.0416   1.0007   0.0459
  -3.250  -0.1309   0.01682   0.00873  -0.0422   1.0007   0.0516
  -3.000  -0.1002   0.01607   0.00806  -0.0429   1.0007   0.0603
  -2.750  -0.0689   0.01507   0.00736  -0.0437   1.0007   0.1027
  -2.500  -0.0384   0.01440   0.00707  -0.0447   1.0007   0.1758
  -2.250  -0.0081   0.01378   0.00691  -0.0457   1.0007   0.2791
  -2.000   0.0212   0.01284   0.00690  -0.0468   1.0007   0.4946
  -1.750   0.0390   0.01171   0.00705  -0.0439   1.0007   0.8266
  -1.500   0.0672   0.01087   0.00633  -0.0438   1.0007   0.9993
  -1.250   0.1067   0.01130   0.00657  -0.0465   0.9749   0.9993
  -1.000   0.1435   0.01153   0.00660  -0.0482   0.9305   0.9993
  -0.750   0.1691   0.01175   0.00662  -0.0471   0.8881   0.9993
  -0.500   0.1937   0.01195   0.00660  -0.0458   0.8534   0.9993
  -0.250   0.2195   0.01214   0.00658  -0.0449   0.8242   0.9993
   0.000   0.2467   0.01231   0.00654  -0.0445   0.7974   0.9993
   0.250   0.2744   0.01248   0.00653  -0.0442   0.7732   0.9993
   0.500   0.3026   0.01265   0.00653  -0.0441   0.7508   0.9993
   0.750   0.3311   0.01282   0.00654  -0.0441   0.7295   0.9993
   1.000   0.3597   0.01299   0.00656  -0.0441   0.7091   0.9993
   1.250   0.3885   0.01316   0.00660  -0.0442   0.6895   0.9993
   1.500   0.4174   0.01334   0.00664  -0.0444   0.6703   0.9993
   1.750   0.4462   0.01352   0.00670  -0.0445   0.6516   0.9993
   2.000   0.4751   0.01371   0.00677  -0.0447   0.6332   0.9993
   2.250   0.5041   0.01390   0.00685  -0.0448   0.6145   0.9993
   2.500   0.5332   0.01407   0.00694  -0.0451   0.5953   0.9993
   2.750   0.5623   0.01425   0.00704  -0.0454   0.5761   0.9993
   3.000   0.5914   0.01444   0.00716  -0.0456   0.5569   0.9993
   3.250   0.6204   0.01463   0.00730  -0.0459   0.5376   0.9993
   3.500   0.6494   0.01483   0.00743  -0.0462   0.5178   0.9993
   3.750   0.6784   0.01505   0.00757  -0.0464   0.4978   0.9993
   4.000   0.7074   0.01527   0.00773  -0.0467   0.4774   0.9993
   4.250   0.7363   0.01551   0.00792  -0.0470   0.4568   0.9993
   4.500   0.7651   0.01577   0.00812  -0.0474   0.4360   0.9993
   4.750   0.7939   0.01606   0.00834  -0.0477   0.4152   0.9993
   5.000   0.8226   0.01637   0.00859  -0.0480   0.3945   0.9993
   5.250   0.8512   0.01671   0.00888  -0.0483   0.3740   0.9993
   5.500   0.8797   0.01707   0.00918  -0.0487   0.3538   0.9993
   5.750   0.9081   0.01746   0.00951  -0.0490   0.3338   0.9993
   6.000   0.9365   0.01785   0.00988  -0.0494   0.3140   0.9993
   6.250   0.9648   0.01826   0.01028  -0.0498   0.2946   0.9993
   6.500   0.9930   0.01870   0.01070  -0.0501   0.2756   0.9993
   6.750   1.0211   0.01916   0.01116  -0.0504   0.2571   0.9993
   7.000   1.0489   0.01965   0.01164  -0.0508   0.2391   0.9993
   7.250   1.0766   0.02018   0.01216  -0.0511   0.2217   0.9993
   7.500   1.1040   0.02075   0.01272  -0.0514   0.2050   0.9993
   7.750   1.1312   0.02136   0.01331  -0.0517   0.1890   0.9993
   8.000   1.1580   0.02205   0.01396  -0.0520   0.1740   0.9993
   8.250   1.1846   0.02274   0.01467  -0.0522   0.1598   0.9993
   8.500   1.2111   0.02345   0.01542  -0.0524   0.1463   0.9993
   8.750   1.2372   0.02423   0.01624  -0.0526   0.1338   0.9993
   9.000   1.2628   0.02505   0.01709  -0.0527   0.1222   0.9993
   9.250   1.2878   0.02590   0.01795  -0.0528   0.1111   0.9993
   9.500   1.3124   0.02674   0.01882  -0.0529   0.1000   0.9993
   9.750   1.3373   0.02743   0.01959  -0.0531   0.0886   0.9993
  10.000   1.3611   0.02828   0.02048  -0.0532   0.0789   0.9993
  10.250   1.3845   0.02919   0.02150  -0.0531   0.0703   0.9993
  10.500   1.4065   0.03025   0.02261  -0.0529   0.0626   0.9993
  10.750   1.4279   0.03135   0.02383  -0.0527   0.0532   0.9993
  11.000   1.4467   0.03283   0.02538  -0.0522   0.0410   0.9993
  11.250   1.4606   0.03488   0.02746  -0.0512   0.0312   0.9993
  11.500   1.4717   0.03700   0.02965  -0.0499   0.0267   0.9993
  11.750   1.4797   0.03924   0.03202  -0.0482   0.0241   0.9993
  12.000   1.4833   0.04164   0.03453  -0.0461   0.0226   0.9993
  12.250   1.4841   0.04411   0.03716  -0.0437   0.0214   0.9993
  12.500   1.4754   0.04691   0.04006  -0.0405   0.0208   0.9993
  12.750   1.4660   0.05037   0.04360  -0.0385   0.0203   0.9993
  13.000   1.4600   0.05412   0.04759  -0.0377   0.0197   0.9993
  13.250   1.4543   0.05813   0.05179  -0.0376   0.0192   0.9993
  13.500   1.4488   0.06230   0.05611  -0.0379   0.0188   0.9993
  13.750   1.4436   0.06655   0.06048  -0.0384   0.0184   0.9993
  14.000   1.4388   0.07071   0.06473  -0.0389   0.0181   0.9993
  14.250   1.4352   0.07464   0.06869  -0.0390   0.0177   0.9993
  14.500   1.4262   0.07981   0.07410  -0.0403   0.0176   0.9993
  14.750   1.4163   0.08516   0.07968  -0.0418   0.0174   0.9993
  15.000   1.4052   0.09082   0.08555  -0.0437   0.0173   0.9993
  15.250   1.3932   0.09677   0.09172  -0.0459   0.0172   0.9993
  15.500   1.3798   0.10310   0.09826  -0.0486   0.0171   0.9993
  15.750   1.3658   0.10976   0.10513  -0.0518   0.0171   0.9993
  16.000   1.3515   0.11691   0.11248  -0.0556   0.0171   0.9993
  16.250   1.3365   0.12458   0.12035  -0.0600   0.0171   0.9993
  16.500   1.3211   0.13267   0.12864  -0.0649   0.0172   0.9993
  16.750   1.3053   0.14124   0.13740  -0.0704   0.0173   0.9993
  17.000   1.2892   0.15035   0.14669  -0.0765   0.0174   0.9993
  17.250   1.2731   0.15991   0.15641  -0.0830   0.0175   0.9993
  17.500   1.2574   0.16977   0.16641  -0.0898   0.0177   0.9993
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