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S4095 (designed for the E-flite UMX ASK-21 scale RC sailplane) (s4095-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: S4095 (designed for the E-flite UMX ASK-21 scale RC sailplane) (s4095-il)
Reynolds number: 500,000
Max Cl/Cd: 65.22 at α=7.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s4095-il-500000-n5.txt
Download as CSV file: xf-s4095-il-500000-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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.6614   0.10368   0.10153   0.0249   1.0007   0.0102
  -8.750  -0.6696   0.09813   0.09601   0.0225   1.0007   0.0101
  -8.500  -0.6776   0.09205   0.08994   0.0184   1.0007   0.0101
  -8.250  -0.6790   0.08396   0.08186   0.0106   1.0007   0.0101
  -8.000  -0.6744   0.07309   0.07090  -0.0004   1.0007   0.0101
  -7.750  -0.6648   0.03247   0.02842  -0.0276   1.0007   0.0102
  -7.500  -0.6358   0.02914   0.02459  -0.0294   1.0007   0.0105
  -7.250  -0.6064   0.02730   0.02243  -0.0305   1.0007   0.0107
  -7.000  -0.5765   0.02499   0.01974  -0.0318   1.0007   0.0109
  -6.750  -0.5466   0.02274   0.01717  -0.0330   1.0007   0.0111
  -6.500  -0.5168   0.02119   0.01543  -0.0339   1.0007   0.0114
  -6.250  -0.4870   0.02006   0.01416  -0.0346   1.0007   0.0116
  -6.000  -0.4572   0.01912   0.01311  -0.0352   1.0007   0.0119
  -5.750  -0.4274   0.01829   0.01219  -0.0358   1.0007   0.0122
  -5.500  -0.3975   0.01755   0.01135  -0.0364   1.0007   0.0125
  -5.250  -0.3675   0.01687   0.01059  -0.0370   1.0007   0.0129
  -5.000  -0.3375   0.01625   0.00991  -0.0375   1.0007   0.0132
  -4.750  -0.3074   0.01569   0.00929  -0.0381   1.0007   0.0136
  -4.500  -0.2772   0.01519   0.00873  -0.0387   1.0007   0.0140
  -4.250  -0.2471   0.01475   0.00826  -0.0392   1.0007   0.0143
  -4.000  -0.2156   0.01481   0.00825  -0.0399   0.9420   0.0148
  -3.750  -0.1906   0.01464   0.00793  -0.0389   0.8879   0.0156
  -3.500  -0.1640   0.01448   0.00759  -0.0384   0.8478   0.0163
  -3.250  -0.1358   0.01435   0.00729  -0.0383   0.8141   0.0171
  -3.000  -0.1070   0.01423   0.00702  -0.0384   0.7847   0.0181
  -2.750  -0.0777   0.01413   0.00677  -0.0386   0.7582   0.0193
  -2.500  -0.0482   0.01402   0.00655  -0.0389   0.7342   0.0219
  -2.250  -0.0185   0.01385   0.00637  -0.0393   0.7116   0.0348
  -2.000   0.0112   0.01368   0.00623  -0.0398   0.6912   0.0654
  -1.750   0.0410   0.01353   0.00612  -0.0403   0.6718   0.0963
  -1.500   0.0709   0.01340   0.00603  -0.0409   0.6534   0.1312
  -1.250   0.1007   0.01327   0.00596  -0.0414   0.6362   0.1726
  -1.000   0.1306   0.01311   0.00592  -0.0420   0.6200   0.2305
  -0.750   0.1606   0.01289   0.00590  -0.0427   0.6040   0.3147
  -0.500   0.1907   0.01262   0.00592  -0.0435   0.5886   0.4216
  -0.250   0.2206   0.01220   0.00599  -0.0443   0.5737   0.5912
   0.000   0.2478   0.01169   0.00613  -0.0441   0.5592   0.7953
   0.250   0.2688   0.01076   0.00550  -0.0419   0.5452   0.9993
   0.500   0.2987   0.01086   0.00548  -0.0424   0.5298   0.9993
   0.750   0.3286   0.01096   0.00548  -0.0428   0.5144   0.9993
   1.000   0.3584   0.01107   0.00548  -0.0433   0.4986   0.9993
   1.250   0.3882   0.01118   0.00550  -0.0437   0.4819   0.9993
   1.500   0.4180   0.01130   0.00552  -0.0442   0.4648   0.9993
   1.750   0.4478   0.01143   0.00556  -0.0447   0.4476   0.9993
   2.000   0.4775   0.01158   0.00561  -0.0451   0.4301   0.9993
   2.250   0.5071   0.01173   0.00566  -0.0456   0.4128   0.9993
   2.500   0.5367   0.01189   0.00573  -0.0461   0.3950   0.9993
   2.750   0.5663   0.01205   0.00582  -0.0465   0.3778   0.9993
   3.000   0.5959   0.01223   0.00591  -0.0470   0.3608   0.9993
   3.250   0.6254   0.01241   0.00602  -0.0475   0.3440   0.9993
   3.500   0.6549   0.01260   0.00615  -0.0479   0.3280   0.9993
   3.750   0.6843   0.01281   0.00628  -0.0484   0.3114   0.9993
   4.000   0.7136   0.01301   0.00642  -0.0489   0.2960   0.9993
   4.250   0.7430   0.01323   0.00658  -0.0493   0.2801   0.9993
   4.500   0.7722   0.01345   0.00674  -0.0498   0.2649   0.9993
   4.750   0.8014   0.01369   0.00692  -0.0503   0.2493   0.9993
   5.000   0.8306   0.01393   0.00711  -0.0507   0.2348   0.9993
   5.250   0.8596   0.01419   0.00733  -0.0512   0.2199   0.9993
   5.500   0.8886   0.01446   0.00755  -0.0516   0.2067   0.9993
   5.750   0.9176   0.01473   0.00779  -0.0521   0.1937   0.9993
   6.000   0.9464   0.01503   0.00804  -0.0525   0.1801   0.9993
   6.500   1.0038   0.01565   0.00861  -0.0534   0.1551   0.9993
   6.750   1.0324   0.01599   0.00892  -0.0538   0.1423   0.9993
   7.000   1.0608   0.01636   0.00924  -0.0542   0.1293   0.9993
   7.250   1.0891   0.01672   0.00960  -0.0546   0.1181   0.9993
   7.500   1.1173   0.01713   0.00997  -0.0551   0.1062   0.9993
   7.750   1.1452   0.01758   0.01038  -0.0555   0.0931   0.9993
   8.000   1.1730   0.01806   0.01081  -0.0559   0.0813   0.9993
   8.250   1.2007   0.01851   0.01126  -0.0562   0.0727   0.9993
   8.500   1.2282   0.01902   0.01175  -0.0566   0.0637   0.9993
   8.750   1.2555   0.01953   0.01224  -0.0569   0.0551   0.9993
   9.000   1.2826   0.02006   0.01277  -0.0572   0.0474   0.9993
   9.250   1.3093   0.02065   0.01336  -0.0575   0.0401   0.9993
   9.500   1.3356   0.02132   0.01401  -0.0578   0.0320   0.9993
   9.750   1.3615   0.02203   0.01470  -0.0580   0.0252   0.9993
  10.000   1.3870   0.02279   0.01546  -0.0581   0.0186   0.9993
  10.250   1.4114   0.02377   0.01642  -0.0582   0.0107   0.9993
  10.500   1.4356   0.02472   0.01742  -0.0582   0.0078   0.9993
  10.750   1.4599   0.02555   0.01833  -0.0582   0.0068   0.9993
  11.000   1.4833   0.02648   0.01935  -0.0581   0.0062   0.9993
  11.250   1.5057   0.02752   0.02051  -0.0579   0.0056   0.9993
  11.500   1.5281   0.02845   0.02154  -0.0576   0.0053   0.9993
  11.750   1.5495   0.02944   0.02266  -0.0573   0.0051   0.9993
  12.000   1.5697   0.03053   0.02389  -0.0568   0.0048   0.9993
  12.250   1.5883   0.03172   0.02521  -0.0561   0.0046   0.9993
  12.500   1.6051   0.03304   0.02666  -0.0553   0.0044   0.9993
  12.750   1.6195   0.03451   0.02826  -0.0542   0.0043   0.9993
  13.000   1.6306   0.03618   0.03007  -0.0528   0.0041   0.9993
  13.250   1.6371   0.03812   0.03216  -0.0509   0.0040   0.9993
  13.500   1.6365   0.04043   0.03463  -0.0484   0.0039   0.9993
  13.750   1.6219   0.04356   0.03792  -0.0446   0.0039   0.9993
  14.000   1.6099   0.04764   0.04218  -0.0435   0.0039   0.9993
  14.250   1.5981   0.05261   0.04734  -0.0442   0.0038   0.9993
  14.500   1.5851   0.05838   0.05329  -0.0460   0.0038   0.9993
  14.750   1.5700   0.06484   0.05994  -0.0485   0.0038   0.9993
  15.000   1.5516   0.07198   0.06726  -0.0513   0.0037   0.9993
  15.250   1.5319   0.07946   0.07491  -0.0543   0.0037   0.9993
  15.500   1.5096   0.08749   0.08311  -0.0576   0.0037   0.9993
  15.750   1.4873   0.09557   0.09135  -0.0609   0.0038   0.9993
  16.000   1.4639   0.10402   0.09996  -0.0644   0.0038   0.9993
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