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SELIG 3002-099-83 (s3002-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: SELIG 3002-099-83 (s3002-il)
Reynolds number: 50,000
Max Cl/Cd: 39.17 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s3002-il-50000-n5.txt
Download as CSV file: xf-s3002-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: SELIG 3002-099-83                               
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3734   0.10493   0.09804  -0.0324   1.0000   0.1220
  -8.500  -0.3661   0.09739   0.09046  -0.0354   1.0000   0.0772
  -8.250  -0.3672   0.09257   0.08571  -0.0370   1.0000   0.0637
  -8.000  -0.3665   0.08925   0.08248  -0.0369   1.0000   0.0611
  -7.500  -0.3957   0.08005   0.07353  -0.0440   1.0000   0.0535
  -7.250  -0.3960   0.07712   0.07067  -0.0433   1.0000   0.0527
  -7.000  -0.3994   0.07392   0.06753  -0.0433   1.0000   0.0518
  -6.750  -0.4038   0.07060   0.06424  -0.0434   1.0000   0.0509
  -6.500  -0.4079   0.06712   0.06075  -0.0437   1.0000   0.0500
  -6.250  -0.4104   0.06340   0.05697  -0.0442   1.0000   0.0491
  -6.000  -0.4098   0.05946   0.05290  -0.0449   1.0000   0.0482
  -5.750  -0.4053   0.05530   0.04852  -0.0459   1.0000   0.0473
  -5.500  -0.3963   0.05105   0.04395  -0.0470   1.0000   0.0465
  -5.250  -0.3830   0.04716   0.03966  -0.0479   1.0000   0.0463
  -5.000  -0.3670   0.04408   0.03626  -0.0484   1.0000   0.0474
  -4.750  -0.3482   0.04118   0.03297  -0.0490   1.0000   0.0491
  -4.500  -0.3266   0.03829   0.02957  -0.0496   1.0000   0.0509
  -4.250  -0.2973   0.03534   0.02604  -0.0510   0.9979   0.0521
  -4.000  -0.2592   0.03266   0.02265  -0.0534   0.9927   0.0539
  -3.750  -0.2248   0.03085   0.02073  -0.0556   0.9870   0.0585
  -3.500  -0.1888   0.02919   0.01870  -0.0572   0.9814   0.0627
  -3.250  -0.1539   0.02775   0.01699  -0.0584   0.9753   0.0678
  -3.000  -0.1196   0.02671   0.01583  -0.0596   0.9691   0.0756
  -2.750  -0.0869   0.02572   0.01474  -0.0604   0.9621   0.0836
  -2.500  -0.0513   0.02489   0.01383  -0.0620   0.9556   0.0984
  -2.250  -0.0172   0.02400   0.01296  -0.0635   0.9478   0.1253
  -2.000   0.0221   0.02236   0.01216  -0.0668   0.9422   0.2583
  -1.750   0.0344   0.02097   0.01274  -0.0627   0.9332   0.6764
  -1.500   0.0498   0.02103   0.01288  -0.0581   0.9237   0.8186
  -1.250   0.0743   0.02077   0.01259  -0.0553   0.9151   0.9142
  -1.000   0.1300   0.02062   0.01211  -0.0605   0.9069   1.0000
  -0.750   0.1703   0.02071   0.01187  -0.0633   0.8983   1.0000
  -0.500   0.2028   0.02084   0.01174  -0.0647   0.8870   1.0000
  -0.250   0.2407   0.02094   0.01161  -0.0668   0.8775   1.0000
   0.000   0.2776   0.02101   0.01148  -0.0686   0.8674   1.0000
   0.250   0.3090   0.02113   0.01143  -0.0694   0.8552   1.0000
   0.500   0.3427   0.02122   0.01138  -0.0705   0.8439   1.0000
   0.750   0.3817   0.02119   0.01121  -0.0722   0.8343   1.0000
   1.000   0.4113   0.02130   0.01122  -0.0725   0.8208   1.0000
   1.250   0.4414   0.02139   0.01122  -0.0727   0.8074   1.0000
   1.500   0.4719   0.02145   0.01122  -0.0730   0.7939   1.0000
   1.750   0.5026   0.02149   0.01120  -0.0731   0.7803   1.0000
   2.000   0.5331   0.02152   0.01119  -0.0732   0.7663   1.0000
   2.250   0.5629   0.02153   0.01117  -0.0731   0.7517   1.0000
   2.500   0.5920   0.02155   0.01116  -0.0728   0.7361   1.0000
   2.750   0.6205   0.02158   0.01119  -0.0724   0.7197   1.0000
   3.000   0.6488   0.02159   0.01119  -0.0720   0.7025   1.0000
   3.250   0.6772   0.02160   0.01119  -0.0715   0.6847   1.0000
   3.500   0.7059   0.02158   0.01115  -0.0709   0.6663   1.0000
   3.750   0.7325   0.02167   0.01125  -0.0702   0.6458   1.0000
   4.000   0.7590   0.02177   0.01135  -0.0695   0.6241   1.0000
   4.250   0.7867   0.02184   0.01136  -0.0688   0.6027   1.0000
   4.500   0.8118   0.02206   0.01161  -0.0679   0.5785   1.0000
   4.750   0.8379   0.02227   0.01176  -0.0671   0.5549   1.0000
   5.000   0.8630   0.02257   0.01202  -0.0663   0.5301   1.0000
   5.250   0.8874   0.02295   0.01239  -0.0654   0.5051   1.0000
   5.500   0.9120   0.02335   0.01270  -0.0645   0.4811   1.0000
   5.750   0.9348   0.02389   0.01322  -0.0636   0.4559   1.0000
   6.000   0.9578   0.02445   0.01372  -0.0627   0.4321   1.0000
   6.250   0.9800   0.02508   0.01436  -0.0618   0.4084   1.0000
   6.500   1.0019   0.02577   0.01500  -0.0609   0.3856   1.0000
   6.750   1.0231   0.02650   0.01573  -0.0599   0.3631   1.0000
   7.000   1.0441   0.02728   0.01649  -0.0590   0.3422   1.0000
   7.250   1.0641   0.02813   0.01739  -0.0580   0.3208   1.0000
   7.500   1.0838   0.02900   0.01826  -0.0569   0.3011   1.0000
   7.750   1.1030   0.02993   0.01915  -0.0559   0.2825   1.0000
   8.000   1.1213   0.03093   0.02027  -0.0548   0.2637   1.0000
   8.250   1.1389   0.03197   0.02137  -0.0537   0.2459   1.0000
   8.500   1.1560   0.03308   0.02252  -0.0525   0.2295   1.0000
   8.750   1.1720   0.03424   0.02373  -0.0513   0.2138   1.0000
   9.000   1.1876   0.03548   0.02503  -0.0500   0.1994   1.0000
   9.250   1.2022   0.03679   0.02644  -0.0487   0.1859   1.0000
   9.500   1.2164   0.03820   0.02792  -0.0474   0.1737   1.0000
   9.750   1.2296   0.03964   0.02941  -0.0461   0.1627   1.0000
  10.000   1.2418   0.04113   0.03095  -0.0447   0.1526   1.0000
  10.250   1.2525   0.04286   0.03289  -0.0432   0.1431   1.0000
  10.500   1.2626   0.04453   0.03463  -0.0416   0.1352   1.0000
  10.750   1.2709   0.04639   0.03668  -0.0401   0.1276   1.0000
  11.000   1.2807   0.04837   0.03877  -0.0388   0.1215   1.0000
  11.250   1.2857   0.05056   0.04119  -0.0373   0.1154   1.0000
  11.500   1.2948   0.05246   0.04307  -0.0361   0.1102   1.0000
  11.750   1.2944   0.05540   0.04641  -0.0348   0.1057   1.0000
  12.000   1.2968   0.05807   0.04931  -0.0337   0.1018   1.0000
  12.250   1.3075   0.06008   0.05125  -0.0329   0.0978   1.0000
  12.500   1.2952   0.06416   0.05578  -0.0322   0.0953   1.0000
  12.750   1.2831   0.06845   0.06040  -0.0320   0.0928   1.0000
  13.000   1.2718   0.07287   0.06507  -0.0324   0.0906   1.0000
  13.250   1.2628   0.07723   0.06961  -0.0330   0.0886   1.0000
  13.500   1.2624   0.08074   0.07321  -0.0334   0.0865   1.0000
  13.750   1.2496   0.08608   0.07871  -0.0350   0.0851   1.0000
  14.000   1.2182   0.09453   0.08744  -0.0390   0.0850   1.0000
  14.250   1.1809   0.10506   0.09819  -0.0450   0.0851   1.0000
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