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S4095 (designed for the E-flite UMX ASK-21 scale RC sailplane) (s4095-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: S4095 (designed for the E-flite UMX ASK-21 scale RC sailplane) (s4095-il)
Reynolds number: 100,000
Max Cl/Cd: 43.52 at α=7.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s4095-il-100000-n5.txt
Download as CSV file: xf-s4095-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.5036   0.08950   0.08500  -0.0010   1.0007   0.0332
  -8.000  -0.6178   0.09309   0.08838   0.0044   1.0007   0.0334
  -7.750  -0.6107   0.08865   0.08393   0.0022   1.0007   0.0327
  -7.500  -0.6018   0.08314   0.07838  -0.0019   1.0007   0.0320
  -7.250  -0.5897   0.07667   0.07183  -0.0074   1.0007   0.0311
  -7.000  -0.5735   0.06916   0.06415  -0.0137   1.0007   0.0301
  -6.750  -0.5519   0.06001   0.05466  -0.0210   1.0007   0.0289
  -6.500  -0.5242   0.04946   0.04343  -0.0280   1.0007   0.0278
  -6.250  -0.4932   0.04204   0.03520  -0.0325   1.0007   0.0275
  -6.000  -0.4640   0.03888   0.03165  -0.0344   1.0007   0.0283
  -5.750  -0.4338   0.03609   0.02847  -0.0360   1.0007   0.0299
  -5.500  -0.4021   0.03296   0.02479  -0.0376   1.0007   0.0310
  -5.250  -0.3703   0.03014   0.02146  -0.0387   1.0007   0.0315
  -5.000  -0.3390   0.02787   0.01878  -0.0395   1.0007   0.0321
  -4.750  -0.3081   0.02601   0.01659  -0.0401   1.0007   0.0329
  -4.500  -0.2777   0.02450   0.01483  -0.0406   1.0007   0.0338
  -4.250  -0.2480   0.02306   0.01336  -0.0412   1.0007   0.0353
  -4.000  -0.2183   0.02212   0.01241  -0.0417   1.0007   0.0384
  -3.750  -0.1884   0.02129   0.01148  -0.0422   1.0007   0.0429
  -3.500  -0.1584   0.02032   0.01050  -0.0428   1.0007   0.0474
  -3.250  -0.1282   0.01952   0.00965  -0.0433   1.0007   0.0559
  -3.000  -0.0980   0.01868   0.00895  -0.0440   1.0007   0.0780
  -2.750  -0.0683   0.01804   0.00853  -0.0447   1.0007   0.1237
  -2.500  -0.0392   0.01734   0.00829  -0.0455   1.0007   0.2036
  -2.250  -0.0101   0.01676   0.00805  -0.0461   1.0007   0.2874
  -2.000   0.0187   0.01616   0.00791  -0.0467   1.0007   0.4057
  -1.750   0.0451   0.01537   0.00788  -0.0466   1.0007   0.5996
  -1.500   0.0695   0.01394   0.00732  -0.0445   0.9684   0.9993
  -1.250   0.1079   0.01418   0.00728  -0.0467   0.9305   0.9993
  -1.000   0.1411   0.01440   0.00723  -0.0476   0.8928   0.9993
  -0.750   0.1698   0.01462   0.00719  -0.0473   0.8584   0.9993
  -0.500   0.1969   0.01482   0.00716  -0.0467   0.8277   0.9993
  -0.250   0.2241   0.01502   0.00713  -0.0462   0.8001   0.9993
   0.000   0.2515   0.01521   0.00711  -0.0458   0.7749   0.9993
   0.250   0.2791   0.01540   0.00710  -0.0455   0.7517   0.9993
   0.500   0.3073   0.01558   0.00711  -0.0453   0.7293   0.9993
   0.750   0.3355   0.01577   0.00713  -0.0452   0.7084   0.9993
   1.000   0.3638   0.01597   0.00717  -0.0452   0.6883   0.9993
   1.250   0.3923   0.01616   0.00724  -0.0452   0.6685   0.9993
   1.500   0.4207   0.01637   0.00731  -0.0452   0.6494   0.9993
   1.750   0.4492   0.01659   0.00740  -0.0452   0.6308   0.9993
   2.000   0.4780   0.01679   0.00752  -0.0454   0.6118   0.9993
   2.250   0.5067   0.01701   0.00764  -0.0455   0.5930   0.9993
   2.500   0.5353   0.01724   0.00777  -0.0456   0.5746   0.9993
   2.750   0.5641   0.01748   0.00793  -0.0458   0.5560   0.9993
   3.000   0.5929   0.01771   0.00811  -0.0460   0.5368   0.9993
   3.250   0.6216   0.01796   0.00829  -0.0462   0.5177   0.9993
   3.500   0.6502   0.01822   0.00850  -0.0464   0.4988   0.9993
   3.750   0.6790   0.01848   0.00873  -0.0466   0.4787   0.9993
   4.000   0.7075   0.01877   0.00896  -0.0468   0.4589   0.9993
   4.250   0.7360   0.01907   0.00921  -0.0471   0.4394   0.9993
   4.500   0.7646   0.01939   0.00952  -0.0473   0.4190   0.9993
   4.750   0.7929   0.01974   0.00982  -0.0476   0.3992   0.9993
   5.000   0.8213   0.02011   0.01016  -0.0478   0.3797   0.9993
   5.250   0.8496   0.02050   0.01057  -0.0481   0.3599   0.9993
   5.500   0.8777   0.02092   0.01096  -0.0484   0.3410   0.9993
   5.750   0.9057   0.02136   0.01139  -0.0487   0.3222   0.9993
   6.000   0.9337   0.02182   0.01187  -0.0490   0.3035   0.9993
   6.250   0.9614   0.02232   0.01239  -0.0493   0.2851   0.9993
   6.500   0.9890   0.02285   0.01292  -0.0495   0.2677   0.9993
   6.750   1.0164   0.02341   0.01350  -0.0498   0.2505   0.9993
   7.000   1.0437   0.02399   0.01412  -0.0501   0.2337   0.9993
   7.250   1.0707   0.02460   0.01481  -0.0503   0.2175   0.9993
   7.500   1.0975   0.02526   0.01552  -0.0505   0.2021   0.9993
   7.750   1.1240   0.02596   0.01628  -0.0508   0.1873   0.9993
   8.000   1.1501   0.02671   0.01708  -0.0509   0.1730   0.9993
   8.250   1.1759   0.02750   0.01797  -0.0511   0.1596   0.9993
   8.500   1.2012   0.02834   0.01889  -0.0512   0.1467   0.9993
   8.750   1.2260   0.02925   0.01988  -0.0513   0.1351   0.9993
   9.000   1.2502   0.03022   0.02092  -0.0513   0.1243   0.9993
   9.250   1.2737   0.03126   0.02205  -0.0512   0.1143   0.9993
   9.500   1.2970   0.03232   0.02331  -0.0510   0.1048   0.9993
   9.750   1.3189   0.03351   0.02462  -0.0508   0.0965   0.9993
  10.000   1.3398   0.03478   0.02601  -0.0504   0.0892   0.9993
  10.250   1.3603   0.03609   0.02751  -0.0500   0.0813   0.9993
  10.500   1.3788   0.03742   0.02895  -0.0496   0.0729   0.9993
  10.750   1.3957   0.03879   0.03039  -0.0491   0.0636   0.9993
  11.000   1.4129   0.04013   0.03196  -0.0486   0.0540   0.9993
  11.250   1.4267   0.04182   0.03387  -0.0477   0.0470   0.9993
  11.500   1.4355   0.04389   0.03604  -0.0464   0.0414   0.9993
  11.750   1.4420   0.04607   0.03845  -0.0449   0.0358   0.9993
  12.000   1.4401   0.04888   0.04139  -0.0429   0.0323   0.9993
  12.250   1.4314   0.05196   0.04472  -0.0402   0.0298   0.9993
  12.500   1.4189   0.05584   0.04880  -0.0387   0.0282   0.9993
  12.750   1.4058   0.06057   0.05372  -0.0388   0.0270   0.9993
  13.000   1.3908   0.06620   0.05951  -0.0402   0.0261   0.9993
  13.250   1.3752   0.07236   0.06583  -0.0423   0.0254   0.9993
  13.500   1.3607   0.07868   0.07240  -0.0446   0.0247   0.9993
  13.750   1.3447   0.08544   0.07937  -0.0473   0.0242   0.9993
  14.000   1.3277   0.09253   0.08667  -0.0503   0.0237   0.9993
  14.250   1.3104   0.09990   0.09422  -0.0536   0.0234   0.9993
  14.500   1.2929   0.10745   0.10195  -0.0571   0.0231   0.9993
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