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RAE 5215 AIRFOIL (rae5215-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: RAE 5215 AIRFOIL (rae5215-il)
Reynolds number: 100,000
Max Cl/Cd: 35.28 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-rae5215-il-100000-n5.txt
Download as CSV file: xf-rae5215-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: RAE 5215 AIRFOIL                                
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.5797   0.08896   0.08353  -0.0217   1.0000   0.0311
  -9.250  -0.5867   0.08174   0.07634  -0.0270   1.0000   0.0307
  -9.000  -0.6022   0.07314   0.06772  -0.0344   1.0000   0.0300
  -8.750  -0.6254   0.06556   0.06002  -0.0409   1.0000   0.0293
  -8.500  -0.6380   0.05939   0.05360  -0.0445   1.0000   0.0291
  -8.250  -0.6411   0.05440   0.04833  -0.0462   1.0000   0.0291
  -8.000  -0.6388   0.04979   0.04339  -0.0471   1.0000   0.0292
  -7.750  -0.6323   0.04541   0.03860  -0.0475   1.0000   0.0292
  -7.500  -0.6213   0.04162   0.03441  -0.0475   1.0000   0.0294
  -7.250  -0.6071   0.03830   0.03069  -0.0472   1.0000   0.0297
  -7.000  -0.5905   0.03546   0.02742  -0.0467   1.0000   0.0308
  -6.750  -0.5724   0.03248   0.02382  -0.0461   1.0000   0.0323
  -6.500  -0.5522   0.03104   0.02235  -0.0455   1.0000   0.0333
  -6.250  -0.5315   0.02921   0.02028  -0.0447   1.0000   0.0341
  -6.000  -0.5101   0.02741   0.01823  -0.0438   1.0000   0.0350
  -5.750  -0.4882   0.02576   0.01628  -0.0428   1.0000   0.0363
  -5.500  -0.4668   0.02462   0.01507  -0.0420   1.0000   0.0380
  -5.250  -0.4451   0.02365   0.01403  -0.0411   1.0000   0.0402
  -5.000  -0.4228   0.02256   0.01276  -0.0400   1.0000   0.0421
  -4.750  -0.4013   0.02169   0.01198  -0.0392   1.0000   0.0442
  -4.500  -0.3790   0.02092   0.01115  -0.0383   1.0000   0.0471
  -4.250  -0.3566   0.02008   0.01033  -0.0376   1.0000   0.0492
  -4.000  -0.3338   0.01940   0.00969  -0.0369   1.0000   0.0522
  -3.750  -0.3104   0.01880   0.00906  -0.0364   1.0000   0.0562
  -3.500  -0.2864   0.01822   0.00851  -0.0361   1.0000   0.0605
  -3.250  -0.2615   0.01768   0.00796  -0.0359   1.0000   0.0660
  -3.000  -0.2337   0.01715   0.00747  -0.0363   0.9992   0.0773
  -2.750  -0.1986   0.01644   0.00694  -0.0383   0.9961   0.1092
  -2.500  -0.1637   0.01450   0.00645  -0.0415   0.9949   0.3936
  -2.250  -0.1335   0.01437   0.00700  -0.0417   0.9906   0.5780
  -2.000  -0.1021   0.01475   0.00751  -0.0417   0.9859   0.6491
  -1.750  -0.0737   0.01513   0.00797  -0.0410   0.9807   0.6955
  -1.500  -0.0436   0.01529   0.00814  -0.0408   0.9758   0.7188
  -1.250  -0.0081   0.01530   0.00805  -0.0425   0.9720   0.7284
  -1.000   0.0228   0.01528   0.00800  -0.0432   0.9662   0.7347
  -0.750   0.0583   0.01529   0.00795  -0.0448   0.9620   0.7422
  -0.500   0.0926   0.01529   0.00793  -0.0462   0.9576   0.7487
  -0.250   0.1267   0.01525   0.00789  -0.0475   0.9502   0.7552
   0.000   0.1691   0.01514   0.00775  -0.0502   0.9413   0.7624
   0.250   0.2112   0.01484   0.00749  -0.0522   0.9275   0.7679
   0.500   0.2479   0.01447   0.00711  -0.0528   0.9045   0.7743
   0.750   0.2841   0.01404   0.00665  -0.0530   0.8773   0.7808
   1.000   0.3109   0.01379   0.00640  -0.0517   0.8477   0.7868
   1.250   0.3394   0.01361   0.00619  -0.0509   0.8201   0.7937
   1.500   0.3659   0.01349   0.00609  -0.0499   0.7915   0.8003
   1.750   0.3920   0.01339   0.00595  -0.0487   0.7522   0.8075
   2.000   0.4176   0.01335   0.00576  -0.0473   0.6798   0.8150
   2.250   0.4366   0.01395   0.00544  -0.0443   0.4802   0.8224
   2.500   0.4547   0.01522   0.00576  -0.0427   0.3017   0.8314
   2.750   0.4767   0.01592   0.00608  -0.0418   0.2315   0.8404
   3.000   0.5007   0.01642   0.00640  -0.0411   0.2005   0.8509
   3.250   0.5247   0.01682   0.00672  -0.0403   0.1823   0.8636
   3.500   0.5482   0.01721   0.00707  -0.0394   0.1694   0.8795
   3.750   0.5726   0.01751   0.00741  -0.0386   0.1588   0.9017
   4.000   0.5998   0.01791   0.00779  -0.0385   0.1497   0.9453
   4.250   0.6288   0.01840   0.00827  -0.0391   0.1409   1.0000
   4.500   0.6563   0.01906   0.00883  -0.0393   0.1338   1.0000
   4.750   0.6839   0.01966   0.00940  -0.0395   0.1266   1.0000
   5.000   0.7105   0.02042   0.01005  -0.0396   0.1206   1.0000
   5.250   0.7379   0.02104   0.01075  -0.0397   0.1140   1.0000
   5.500   0.7641   0.02180   0.01141  -0.0397   0.1085   1.0000
   5.750   0.7909   0.02251   0.01221  -0.0396   0.1022   1.0000
   6.000   0.8168   0.02319   0.01286  -0.0395   0.0965   1.0000
   6.250   0.8428   0.02396   0.01371  -0.0393   0.0908   1.0000
   6.500   0.8682   0.02461   0.01436  -0.0391   0.0855   1.0000
   6.750   0.8936   0.02547   0.01532  -0.0389   0.0806   1.0000
   7.000   0.9185   0.02619   0.01609  -0.0386   0.0761   1.0000
   7.250   0.9431   0.02713   0.01711  -0.0383   0.0722   1.0000
   7.500   0.9674   0.02801   0.01811  -0.0379   0.0682   1.0000
   7.750   0.9909   0.02891   0.01901  -0.0375   0.0655   1.0000
   8.000   1.0143   0.03025   0.02061  -0.0369   0.0619   1.0000
   8.250   1.0369   0.03111   0.02151  -0.0364   0.0595   1.0000
   8.500   1.0586   0.03255   0.02314  -0.0358   0.0570   1.0000
   8.750   1.0793   0.03420   0.02504  -0.0350   0.0548   1.0000
   9.000   1.0997   0.03557   0.02654  -0.0343   0.0533   1.0000
   9.250   1.1199   0.03675   0.02774  -0.0336   0.0521   1.0000
   9.500   1.1341   0.03950   0.03099  -0.0323   0.0503   1.0000
   9.750   1.1474   0.04190   0.03375  -0.0310   0.0488   1.0000
  10.000   1.1612   0.04376   0.03581  -0.0298   0.0475   1.0000
  10.250   1.1753   0.04535   0.03752  -0.0287   0.0466   1.0000
  10.500   1.1880   0.04717   0.03942  -0.0276   0.0460   1.0000
  10.750   1.1798   0.05184   0.04472  -0.0250   0.0454   1.0000
  11.000   1.1636   0.05675   0.05014  -0.0224   0.0449   1.0000
  11.250   1.1378   0.06159   0.05536  -0.0196   0.0447   1.0000
  11.500   1.1048   0.06749   0.06159  -0.0186   0.0447   1.0000
  11.750   1.0628   0.07577   0.07017  -0.0213   0.0449   1.0000
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