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RAE 2822 AIRFOIL (rae2822-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: RAE 2822 AIRFOIL (rae2822-il)
Reynolds number: 50,000
Max Cl/Cd: 27.05 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-rae2822-il-50000-n5.txt
Download as CSV file: xf-rae2822-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: RAE 2822 AIRFOIL                                
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.7040   0.07584   0.06790  -0.0584   1.0000   0.0460
 -11.000  -0.7218   0.07171   0.06366  -0.0591   1.0000   0.0459
 -10.750  -0.7408   0.06805   0.05987  -0.0587   1.0000   0.0459
 -10.500  -0.7589   0.06498   0.05667  -0.0572   1.0000   0.0458
 -10.250  -0.7760   0.06198   0.05348  -0.0550   1.0000   0.0460
 -10.000  -0.7838   0.05891   0.05027  -0.0531   1.0000   0.0465
  -9.750  -0.7839   0.05632   0.04763  -0.0515   1.0000   0.0478
  -9.500  -0.7832   0.05394   0.04512  -0.0497   1.0000   0.0492
  -9.250  -0.7819   0.05152   0.04251  -0.0478   1.0000   0.0509
  -9.000  -0.7792   0.04888   0.03958  -0.0458   1.0000   0.0523
  -8.750  -0.7729   0.04616   0.03651  -0.0438   1.0000   0.0537
  -8.500  -0.7625   0.04350   0.03346  -0.0419   1.0000   0.0552
  -8.250  -0.7499   0.04124   0.03072  -0.0400   1.0000   0.0575
  -8.000  -0.7340   0.03933   0.02885  -0.0387   1.0000   0.0610
  -7.750  -0.7168   0.03768   0.02704  -0.0371   1.0000   0.0652
  -7.500  -0.6947   0.03604   0.02510  -0.0354   1.0000   0.0693
  -7.250  -0.6764   0.03471   0.02385  -0.0337   1.0000   0.0749
  -7.000  -0.6585   0.03361   0.02257  -0.0317   1.0000   0.0821
  -6.750  -0.6445   0.03242   0.02143  -0.0293   1.0000   0.0883
  -6.500  -0.6329   0.03135   0.02024  -0.0269   1.0000   0.0980
  -6.250  -0.6238   0.03017   0.01911  -0.0245   1.0000   0.1084
  -6.000  -0.6152   0.02890   0.01790  -0.0222   1.0000   0.1216
  -5.750  -0.6069   0.02748   0.01662  -0.0202   1.0000   0.1421
  -5.500  -0.5984   0.02576   0.01518  -0.0186   1.0000   0.1762
  -5.250  -0.5917   0.02335   0.01362  -0.0175   1.0000   0.2717
  -5.000  -0.5845   0.02319   0.01466  -0.0129   1.0000   0.4741
  -4.750  -0.5681   0.02366   0.01495  -0.0103   1.0000   0.5374
  -4.500  -0.5519   0.02418   0.01528  -0.0076   1.0000   0.5759
  -4.250  -0.5366   0.02483   0.01580  -0.0042   1.0000   0.6044
  -4.000  -0.5235   0.02571   0.01664   0.0003   1.0000   0.6302
  -3.750  -0.5116   0.02654   0.01739   0.0051   1.0000   0.6558
  -3.500  -0.4986   0.02700   0.01774   0.0088   1.0000   0.6790
  -3.250  -0.4834   0.02712   0.01773   0.0116   1.0000   0.6946
  -3.000  -0.4651   0.02693   0.01739   0.0132   1.0000   0.7010
  -2.750  -0.4440   0.02650   0.01676   0.0132   1.0000   0.7082
  -2.500  -0.4239   0.02620   0.01628   0.0138   1.0000   0.7136
  -2.250  -0.4032   0.02591   0.01584   0.0142   1.0000   0.7194
  -2.000  -0.3692   0.02574   0.01547   0.0117   0.9950   0.7255
  -1.750  -0.3381   0.02568   0.01526   0.0103   0.9896   0.7301
  -1.500  -0.3047   0.02562   0.01505   0.0081   0.9844   0.7359
  -1.250  -0.2730   0.02552   0.01483   0.0063   0.9787   0.7414
  -1.000  -0.2416   0.02552   0.01473   0.0048   0.9732   0.7464
  -0.750  -0.2086   0.02549   0.01460   0.0027   0.9679   0.7525
  -0.500  -0.1788   0.02548   0.01454   0.0015   0.9617   0.7577
  -0.250  -0.1448   0.02557   0.01457  -0.0005   0.9566   0.7632
   0.000  -0.1158   0.02553   0.01449  -0.0019   0.9501   0.7696
   0.250  -0.0845   0.02562   0.01459  -0.0031   0.9442   0.7749
   0.500  -0.0540   0.02568   0.01464  -0.0045   0.9380   0.7814
   0.750  -0.0242   0.02576   0.01475  -0.0057   0.9314   0.7874
   1.000   0.0083   0.02589   0.01491  -0.0073   0.9255   0.7940
   1.250   0.0358   0.02596   0.01504  -0.0080   0.9179   0.8010
   1.500   0.0708   0.02612   0.01528  -0.0099   0.9123   0.8078
   1.750   0.0957   0.02620   0.01544  -0.0101   0.9035   0.8156
   2.000   0.1306   0.02635   0.01570  -0.0119   0.8973   0.8231
   2.250   0.1556   0.02645   0.01594  -0.0120   0.8879   0.8314
   2.500   0.1871   0.02657   0.01620  -0.0132   0.8799   0.8403
   2.750   0.2171   0.02666   0.01646  -0.0139   0.8709   0.8493
   3.000   0.2447   0.02675   0.01674  -0.0143   0.8608   0.8596
   3.250   0.2801   0.02679   0.01699  -0.0158   0.8519   0.8701
   3.500   0.3112   0.02677   0.01721  -0.0164   0.8406   0.8816
   3.750   0.3421   0.02671   0.01743  -0.0169   0.8277   0.8945
   4.000   0.3782   0.02651   0.01752  -0.0181   0.8135   0.9081
   4.250   0.4236   0.02593   0.01729  -0.0201   0.7966   0.9215
   4.500   0.4778   0.02433   0.01609  -0.0216   0.7631   0.9333
   4.750   0.5218   0.02240   0.01443  -0.0205   0.7035   0.9483
   5.000   0.5577   0.02137   0.01355  -0.0197   0.6141   0.9728
   5.250   0.5875   0.02172   0.01244  -0.0175   0.3415   1.0000
   5.500   0.5894   0.02375   0.01340  -0.0148   0.2041   1.0000
   5.750   0.6019   0.02553   0.01461  -0.0137   0.1462   1.0000
   6.000   0.6203   0.02703   0.01591  -0.0131   0.1196   1.0000
   6.250   0.6423   0.02843   0.01721  -0.0128   0.1024   1.0000
   6.500   0.6686   0.02989   0.01868  -0.0130   0.0907   1.0000
   6.750   0.7007   0.03131   0.02023  -0.0137   0.0802   1.0000
   7.000   0.7375   0.03315   0.02216  -0.0150   0.0727   1.0000
   7.250   0.7707   0.03502   0.02415  -0.0160   0.0665   1.0000
   7.500   0.8013   0.03724   0.02655  -0.0167   0.0614   1.0000
   7.750   0.8303   0.03983   0.02953  -0.0168   0.0583   1.0000
   8.000   0.8539   0.04234   0.03233  -0.0165   0.0554   1.0000
   8.250   0.8739   0.04474   0.03483  -0.0163   0.0524   1.0000
   8.500   0.8887   0.04777   0.03826  -0.0151   0.0504   1.0000
   8.750   0.8992   0.05112   0.04217  -0.0134   0.0493   1.0000
   9.000   0.9054   0.05465   0.04617  -0.0115   0.0487   1.0000
   9.250   0.9071   0.05830   0.05024  -0.0094   0.0483   1.0000
   9.500   0.9038   0.06200   0.05431  -0.0073   0.0479   1.0000
   9.750   0.8958   0.06569   0.05833  -0.0051   0.0475   1.0000
  10.000   0.8824   0.06930   0.06219  -0.0028   0.0472   1.0000
  10.250   0.8655   0.07305   0.06615  -0.0010   0.0471   1.0000
  10.500   0.8462   0.07729   0.07056  -0.0004   0.0472   1.0000
  10.750   0.8248   0.08222   0.07564  -0.0011   0.0475   1.0000
  11.000   0.8030   0.08796   0.08149  -0.0034   0.0480   1.0000
  11.250   0.7822   0.09466   0.08826  -0.0071   0.0486   1.0000
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