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RAE 2822 AIRFOIL (rae2822-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: RAE 2822 AIRFOIL (rae2822-il)
Reynolds number: 200,000
Max Cl/Cd: 53.63 at α=4°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-rae2822-il-200000.txt
Download as CSV file: xf-rae2822-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.750  -0.4643   0.09944   0.09591  -0.0418   1.0000   0.0732
 -11.500  -0.5733   0.06898   0.06531  -0.0586   1.0000   0.0441
 -11.250  -0.5964   0.06239   0.05867  -0.0604   1.0000   0.0425
 -11.000  -0.6289   0.05578   0.05195  -0.0622   1.0000   0.0411
 -10.750  -0.7246   0.04764   0.04326  -0.0619   1.0000   0.0365
 -10.500  -0.7424   0.04670   0.04220  -0.0585   1.0000   0.0362
 -10.250  -0.8067   0.05369   0.04895  -0.0544   1.0000   0.0351
 -10.000  -0.8187   0.05010   0.04522  -0.0517   1.0000   0.0343
  -9.750  -0.8296   0.04679   0.04170  -0.0485   1.0000   0.0337
  -9.500  -0.8374   0.04352   0.03814  -0.0452   1.0000   0.0333
  -9.250  -0.8404   0.04071   0.03504  -0.0420   1.0000   0.0335
  -9.000  -0.8387   0.03829   0.03231  -0.0392   1.0000   0.0340
  -8.750  -0.8336   0.03585   0.02955  -0.0365   1.0000   0.0345
  -8.500  -0.8256   0.03341   0.02678  -0.0341   1.0000   0.0348
  -8.250  -0.8142   0.03122   0.02428  -0.0319   1.0000   0.0352
  -8.000  -0.8005   0.02957   0.02234  -0.0299   1.0000   0.0357
  -7.750  -0.7854   0.02683   0.01936  -0.0282   1.0000   0.0367
  -7.500  -0.7695   0.02522   0.01777  -0.0268   1.0000   0.0390
  -7.250  -0.7528   0.02430   0.01676  -0.0254   1.0000   0.0413
  -7.000  -0.7350   0.02321   0.01555  -0.0239   1.0000   0.0434
  -6.750  -0.7167   0.02230   0.01451  -0.0224   1.0000   0.0454
  -6.500  -0.7005   0.02078   0.01299  -0.0208   1.0000   0.0486
  -6.250  -0.6829   0.02004   0.01227  -0.0196   1.0000   0.0529
  -6.000  -0.6641   0.01938   0.01151  -0.0184   1.0000   0.0569
  -5.750  -0.6469   0.01822   0.01041  -0.0174   1.0000   0.0628
  -5.500  -0.6240   0.01748   0.00965  -0.0173   0.9993   0.0722
  -5.250  -0.5895   0.01649   0.00874  -0.0197   0.9960   0.0903
  -5.000  -0.5555   0.01527   0.00780  -0.0223   0.9927   0.1407
  -4.750  -0.5279   0.01280   0.00701  -0.0251   0.9894   0.4589
  -4.500  -0.4921   0.01311   0.00735  -0.0268   0.9854   0.5305
  -4.250  -0.4571   0.01349   0.00766  -0.0283   0.9814   0.5607
  -4.000  -0.4250   0.01380   0.00794  -0.0290   0.9761   0.5798
  -3.750  -0.3891   0.01416   0.00826  -0.0306   0.9723   0.5964
  -3.500  -0.3555   0.01448   0.00854  -0.0317   0.9683   0.6105
  -3.250  -0.3257   0.01473   0.00875  -0.0320   0.9627   0.6236
  -3.000  -0.2911   0.01512   0.00916  -0.0330   0.9587   0.6387
  -2.750  -0.2562   0.01559   0.00965  -0.0340   0.9555   0.6538
  -2.500  -0.2306   0.01565   0.00968  -0.0336   0.9489   0.6610
  -2.250  -0.1938   0.01551   0.00943  -0.0360   0.9451   0.6656
  -2.000  -0.1554   0.01546   0.00937  -0.0383   0.9426   0.6686
  -1.750  -0.1292   0.01542   0.00929  -0.0383   0.9362   0.6720
  -1.500  -0.0949   0.01533   0.00915  -0.0399   0.9319   0.6764
  -1.250  -0.0560   0.01522   0.00899  -0.0426   0.9291   0.6808
  -1.000  -0.0202   0.01517   0.00894  -0.0443   0.9259   0.6837
  -0.750   0.0048   0.01516   0.00894  -0.0440   0.9188   0.6874
  -0.500   0.0428   0.01506   0.00883  -0.0463   0.9157   0.6922
  -0.250   0.0835   0.01494   0.00871  -0.0491   0.9135   0.6964
   0.000   0.1075   0.01497   0.00878  -0.0486   0.9063   0.6997
   0.250   0.1441   0.01487   0.00873  -0.0504   0.9025   0.7039
   0.500   0.1857   0.01473   0.00859  -0.0534   0.9000   0.7093
   0.750   0.2269   0.01454   0.00849  -0.0559   0.8979   0.7130
   1.000   0.2492   0.01456   0.00858  -0.0549   0.8889   0.7173
   1.250   0.2896   0.01433   0.00840  -0.0573   0.8854   0.7224
   1.500   0.3221   0.01418   0.00833  -0.0581   0.8793   0.7269
   1.750   0.3559   0.01394   0.00820  -0.0589   0.8723   0.7315
   2.000   0.3923   0.01359   0.00793  -0.0601   0.8646   0.7373
   2.250   0.4317   0.01297   0.00737  -0.0613   0.8541   0.7420
   2.500   0.4601   0.01239   0.00687  -0.0601   0.8332   0.7468
   2.750   0.4901   0.01196   0.00646  -0.0595   0.8130   0.7530
   3.000   0.5184   0.01168   0.00624  -0.0588   0.7942   0.7582
   3.250   0.5427   0.01152   0.00615  -0.0574   0.7697   0.7644
   3.500   0.5684   0.01137   0.00603  -0.0564   0.7398   0.7708
   3.750   0.5915   0.01130   0.00595  -0.0548   0.6981   0.7766
   4.000   0.6124   0.01142   0.00582  -0.0527   0.6179   0.7841
   4.250   0.6163   0.01247   0.00594  -0.0477   0.4224   0.7904
   4.500   0.6146   0.01455   0.00674  -0.0431   0.1820   0.7989
   4.750   0.6252   0.01589   0.00758  -0.0402   0.1013   0.8060
   5.000   0.6438   0.01669   0.00832  -0.0386   0.0819   0.8147
   5.250   0.6617   0.01743   0.00909  -0.0368   0.0711   0.8232
   5.500   0.6785   0.01847   0.01008  -0.0350   0.0635   0.8326
   5.750   0.7001   0.01911   0.01086  -0.0337   0.0583   0.8434
   6.000   0.7194   0.01998   0.01173  -0.0322   0.0531   0.8545
   6.250   0.7409   0.02118   0.01303  -0.0310   0.0496   0.8659
   6.500   0.7636   0.02215   0.01414  -0.0298   0.0468   0.8791
   6.750   0.7847   0.02303   0.01512  -0.0284   0.0439   0.8950
   7.000   0.8095   0.02557   0.01771  -0.0280   0.0405   0.9124
   7.250   0.8306   0.02646   0.01891  -0.0264   0.0395   0.9410
   7.500   0.8646   0.02858   0.02140  -0.0277   0.0383   1.0000
   7.750   0.8917   0.03097   0.02412  -0.0279   0.0370   1.0000
   8.000   0.9151   0.03291   0.02630  -0.0278   0.0350   1.0000
   8.250   0.9337   0.03621   0.03002  -0.0267   0.0350   1.0000
   8.500   0.9439   0.04095   0.03531  -0.0243   0.0365   1.0000
   8.750   0.9493   0.04601   0.04077  -0.0220   0.0385   1.0000
   9.750   0.9114   0.07306   0.06940  -0.0107   0.0629   1.0000
  10.000   0.8771   0.07498   0.07158  -0.0064   0.0621   1.0000
  10.250   0.8476   0.07866   0.07541  -0.0050   0.0615   1.0000
  10.500   0.8210   0.08370   0.08056  -0.0062   0.0613   1.0000
  10.750   0.7931   0.09038   0.08731  -0.0101   0.0612   1.0000
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