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S4095 (designed for the E-flite UMX ASK-21 scale RC sailplane) (s4095-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: S4095 (designed for the E-flite UMX ASK-21 scale RC sailplane) (s4095-il)
Reynolds number: 50,000
Max Cl/Cd: 32.85 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s4095-il-50000-n5.txt
Download as CSV file: xf-s4095-il-50000-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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.6105   0.10417   0.09746   0.0032   1.0007   0.0554
  -8.000  -0.6033   0.09940   0.09269   0.0013   1.0007   0.0551
  -7.750  -0.5957   0.09432   0.08760  -0.0015   1.0007   0.0547
  -7.500  -0.5867   0.08901   0.08225  -0.0049   1.0007   0.0544
  -7.250  -0.5756   0.08357   0.07675  -0.0085   1.0007   0.0538
  -7.000  -0.5621   0.07795   0.07103  -0.0124   1.0007   0.0530
  -6.750  -0.5455   0.07207   0.06496  -0.0166   1.0007   0.0520
  -6.500  -0.5251   0.06587   0.05851  -0.0212   1.0007   0.0509
  -6.250  -0.5007   0.05957   0.05185  -0.0260   1.0007   0.0500
  -6.000  -0.4726   0.05353   0.04532  -0.0303   1.0007   0.0494
  -5.750  -0.4422   0.04824   0.03947  -0.0338   1.0007   0.0492
  -5.500  -0.4103   0.04370   0.03434  -0.0366   1.0007   0.0495
  -5.250  -0.3781   0.04003   0.03007  -0.0386   1.0007   0.0514
  -5.000  -0.3452   0.03686   0.02621  -0.0401   1.0007   0.0543
  -4.750  -0.3140   0.03421   0.02314  -0.0412   1.0007   0.0568
  -4.500  -0.2838   0.03210   0.02082  -0.0418   1.0007   0.0591
  -4.250  -0.2535   0.03019   0.01866  -0.0422   1.0007   0.0623
  -4.000  -0.2234   0.02846   0.01662  -0.0423   1.0007   0.0670
  -3.750  -0.1946   0.02713   0.01527  -0.0426   1.0007   0.0758
  -3.500  -0.1654   0.02584   0.01392  -0.0428   1.0007   0.0890
  -3.250  -0.1356   0.02466   0.01276  -0.0432   1.0007   0.1152
  -3.000  -0.1059   0.02359   0.01191  -0.0439   1.0007   0.1683
  -2.750  -0.0765   0.02244   0.01110  -0.0446   1.0007   0.2389
  -2.500  -0.0482   0.02129   0.01055  -0.0451   1.0007   0.3532
  -2.250  -0.0253   0.01991   0.01021  -0.0441   1.0007   0.5624
  -2.000  -0.0076   0.01774   0.00907  -0.0401   1.0007   0.9993
  -1.750   0.0216   0.01783   0.00878  -0.0407   1.0007   0.9993
  -1.500   0.0500   0.01799   0.00864  -0.0413   1.0007   0.9993
  -1.250   0.0777   0.01821   0.00864  -0.0418   1.0007   0.9993
  -1.000   0.1043   0.01855   0.00878  -0.0423   1.0007   0.9993
  -0.750   0.1292   0.01905   0.00915  -0.0426   1.0007   0.9993
  -0.500   0.1732   0.01926   0.00911  -0.0465   0.9790   0.9993
  -0.250   0.2182   0.01935   0.00898  -0.0503   0.9513   0.9993
   0.000   0.2609   0.01948   0.00892  -0.0535   0.9228   0.9993
   0.250   0.2987   0.01968   0.00894  -0.0554   0.8930   0.9993
   0.500   0.3312   0.01994   0.00903  -0.0560   0.8634   0.9993
   0.750   0.3601   0.02026   0.00918  -0.0557   0.8353   0.9993
   1.000   0.3872   0.02059   0.00936  -0.0550   0.8093   0.9993
   1.250   0.4138   0.02093   0.00956  -0.0544   0.7838   0.9993
   1.500   0.4403   0.02127   0.00976  -0.0537   0.7599   0.9993
   1.750   0.4667   0.02161   0.00998  -0.0530   0.7374   0.9993
   2.000   0.4936   0.02194   0.01022  -0.0525   0.7147   0.9993
   2.250   0.5203   0.02229   0.01046  -0.0519   0.6933   0.9993
   2.500   0.5475   0.02263   0.01073  -0.0515   0.6717   0.9993
   2.750   0.5747   0.02298   0.01103  -0.0511   0.6505   0.9993
   3.000   0.6019   0.02333   0.01131  -0.0508   0.6299   0.9993
   3.250   0.6294   0.02369   0.01164  -0.0505   0.6083   0.9993
   3.500   0.6566   0.02405   0.01198  -0.0502   0.5882   0.9993
   3.750   0.6843   0.02443   0.01236  -0.0501   0.5666   0.9993
   4.000   0.7117   0.02481   0.01272  -0.0499   0.5458   0.9993
   4.250   0.7392   0.02521   0.01312  -0.0497   0.5248   0.9993
   4.500   0.7666   0.02562   0.01358  -0.0496   0.5035   0.9993
   4.750   0.7938   0.02604   0.01399  -0.0494   0.4829   0.9993
   5.000   0.8212   0.02650   0.01450  -0.0494   0.4611   0.9993
   5.250   0.8483   0.02696   0.01494  -0.0492   0.4409   0.9993
   5.500   0.8757   0.02749   0.01558  -0.0493   0.4190   0.9993
   5.750   0.9026   0.02803   0.01613  -0.0491   0.3987   0.9993
   6.000   0.9295   0.02863   0.01678  -0.0491   0.3779   0.9993
   6.250   0.9561   0.02928   0.01747  -0.0491   0.3575   0.9993
   6.500   0.9824   0.02995   0.01819  -0.0490   0.3386   0.9993
   6.750   1.0088   0.03071   0.01907  -0.0490   0.3181   0.9993
   7.000   1.0346   0.03150   0.01994  -0.0490   0.2993   0.9993
   7.250   1.0600   0.03232   0.02079  -0.0489   0.2813   0.9993
   7.500   1.0854   0.03326   0.02189  -0.0488   0.2633   0.9993
   7.750   1.1102   0.03425   0.02301  -0.0488   0.2456   0.9993
   8.000   1.1345   0.03530   0.02418  -0.0486   0.2293   0.9993
   8.250   1.1582   0.03641   0.02541  -0.0485   0.2136   0.9993
   8.500   1.1814   0.03763   0.02679  -0.0483   0.1990   0.9993
   8.750   1.2039   0.03892   0.02823  -0.0480   0.1850   0.9993
   9.000   1.2256   0.04033   0.02981  -0.0477   0.1719   0.9993
   9.250   1.2464   0.04185   0.03152  -0.0473   0.1597   0.9993
   9.500   1.2662   0.04345   0.03329  -0.0468   0.1485   0.9993
   9.750   1.2853   0.04507   0.03503  -0.0462   0.1389   0.9993
  10.000   1.3023   0.04692   0.03715  -0.0455   0.1287   0.9993
  10.250   1.3179   0.04914   0.03969  -0.0447   0.1200   0.9993
  10.500   1.3330   0.05099   0.04158  -0.0438   0.1126   0.9993
  10.750   1.3426   0.05360   0.04463  -0.0426   0.1046   0.9993
  11.000   1.3529   0.05598   0.04715  -0.0414   0.0986   0.9993
  11.250   1.3553   0.05912   0.05072  -0.0398   0.0925   0.9993
  11.500   1.3606   0.06132   0.05291  -0.0383   0.0870   0.9993
  11.750   1.3494   0.06553   0.05765  -0.0362   0.0830   0.9993
  12.000   1.3369   0.06923   0.06164  -0.0341   0.0798   0.9993
  12.250   1.3361   0.07139   0.06365  -0.0327   0.0754   0.9993
  12.500   1.3121   0.07731   0.06998  -0.0328   0.0741   0.9993
  12.750   1.2875   0.08426   0.07727  -0.0347   0.0732   0.9993
  13.000   1.2610   0.09238   0.08567  -0.0381   0.0728   0.9993
  13.250   1.2315   0.10188   0.09536  -0.0429   0.0732   0.9993
  13.500   1.1993   0.11291   0.10656  -0.0491   0.0742   0.9993
  13.750   1.1653   0.12544   0.11918  -0.0564   0.0751   0.9993
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