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USA 22 AIRFOIL (usa22-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: USA 22 AIRFOIL (usa22-il)
Reynolds number: 200,000
Max Cl/Cd: 72.97 at α=7.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-usa22-il-200000.txt
Download as CSV file: xf-usa22-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: USA 22 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.3856   0.11099   0.10758  -0.0113   1.0000   0.0385
  -9.000  -0.3837   0.10824   0.10487  -0.0151   1.0000   0.0389
  -8.750  -0.3808   0.10510   0.10178  -0.0183   1.0000   0.0391
  -8.500  -0.3768   0.10179   0.09851  -0.0209   1.0000   0.0392
  -8.250  -0.3734   0.09836   0.09513  -0.0234   1.0000   0.0392
  -8.000  -0.3682   0.09208   0.08888  -0.0205   1.0000   0.0404
  -7.750  -0.3591   0.08907   0.08589  -0.0196   1.0000   0.0414
  -7.500  -0.3528   0.08621   0.08307  -0.0199   1.0000   0.0424
  -7.250  -0.3481   0.08328   0.08018  -0.0211   1.0000   0.0435
  -7.000  -0.3419   0.08005   0.07699  -0.0233   1.0000   0.0449
  -6.750  -0.3358   0.07670   0.07367  -0.0263   1.0000   0.0470
  -6.500  -0.3261   0.07259   0.06958  -0.0351   1.0000   0.0503
  -6.250  -0.3144   0.06856   0.06549  -0.0416   1.0000   0.0510
  -6.000  -0.3181   0.06275   0.05970  -0.0420   1.0000   0.0519
  -5.750  -0.3188   0.06086   0.05788  -0.0381   1.0000   0.0530
  -5.500  -0.3135   0.05880   0.05585  -0.0366   0.9995   0.0541
  -5.250  -0.2744   0.05444   0.05140  -0.0432   0.9940   0.0575
  -5.000  -0.1641   0.02847   0.02534  -0.0629   0.9668   0.0683
  -4.750  -0.1847   0.04141   0.03787  -0.0616   0.9789   0.0687
  -4.500  -0.1351   0.02837   0.02360  -0.0703   0.9720   0.0490
  -4.250  -0.0959   0.02323   0.01775  -0.0736   0.9639   0.0470
  -4.000  -0.0532   0.02014   0.01400  -0.0764   0.9571   0.0486
  -3.750  -0.0164   0.01794   0.01132  -0.0780   0.9457   0.0536
  -3.500   0.0200   0.01647   0.00968  -0.0794   0.9330   0.0582
  -3.250   0.0554   0.01588   0.00879  -0.0801   0.9177   0.0646
  -3.000   0.0863   0.01422   0.00708  -0.0804   0.9009   0.0711
  -2.750   0.1151   0.01368   0.00638  -0.0799   0.8803   0.0779
  -2.500   0.1411   0.01282   0.00549  -0.0791   0.8576   0.0844
  -2.250   0.1672   0.01243   0.00497  -0.0781   0.8334   0.0921
  -2.000   0.1927   0.01192   0.00443  -0.0771   0.8092   0.1013
  -1.750   0.2184   0.01160   0.00406  -0.0762   0.7839   0.1188
  -1.500   0.2436   0.01108   0.00381  -0.0754   0.7591   0.1964
  -1.250   0.2697   0.01116   0.00387  -0.0746   0.7351   0.2773
  -1.000   0.2959   0.01129   0.00384  -0.0740   0.7116   0.3101
  -0.750   0.3221   0.01138   0.00380  -0.0734   0.6890   0.3364
  -0.500   0.3481   0.01137   0.00372  -0.0728   0.6677   0.3592
  -0.250   0.3740   0.01134   0.00362  -0.0723   0.6480   0.3846
   0.000   0.3999   0.01122   0.00352  -0.0718   0.6288   0.4139
   0.250   0.4245   0.01088   0.00343  -0.0712   0.6117   0.4791
   0.500   0.4615   0.00985   0.00339  -0.0724   0.5946   1.0000
   0.750   0.4882   0.01004   0.00337  -0.0719   0.5795   1.0000
   1.000   0.5149   0.01023   0.00338  -0.0716   0.5652   1.0000
   1.250   0.5415   0.01041   0.00341  -0.0712   0.5515   1.0000
   1.500   0.5682   0.01060   0.00346  -0.0708   0.5386   1.0000
   1.750   0.5948   0.01080   0.00353  -0.0705   0.5268   1.0000
   2.000   0.6214   0.01102   0.00361  -0.0701   0.5160   1.0000
   2.250   0.6481   0.01122   0.00372  -0.0698   0.5055   1.0000
   2.500   0.6749   0.01142   0.00386  -0.0695   0.4953   1.0000
   2.750   0.7016   0.01165   0.00400  -0.0693   0.4862   1.0000
   3.000   0.7283   0.01187   0.00416  -0.0690   0.4770   1.0000
   3.250   0.7549   0.01209   0.00437  -0.0687   0.4677   1.0000
   3.500   0.7814   0.01236   0.00454  -0.0684   0.4590   1.0000
   3.750   0.8079   0.01256   0.00474  -0.0681   0.4492   1.0000
   4.000   0.8343   0.01281   0.00497  -0.0678   0.4401   1.0000
   4.250   0.8607   0.01309   0.00520  -0.0675   0.4316   1.0000
   4.500   0.8870   0.01330   0.00547  -0.0672   0.4218   1.0000
   4.750   0.9131   0.01358   0.00573  -0.0669   0.4127   1.0000
   5.000   0.9392   0.01384   0.00599  -0.0666   0.4031   1.0000
   5.250   0.9650   0.01408   0.00629  -0.0662   0.3923   1.0000
   5.500   0.9907   0.01435   0.00658  -0.0658   0.3817   1.0000
   5.750   1.0160   0.01459   0.00682  -0.0654   0.3700   1.0000
   6.000   1.0406   0.01471   0.00699  -0.0648   0.3538   1.0000
   6.250   1.0653   0.01487   0.00719  -0.0643   0.3378   1.0000
   6.500   1.0900   0.01510   0.00745  -0.0638   0.3234   1.0000
   6.750   1.1140   0.01530   0.00764  -0.0632   0.3039   1.0000
   7.000   1.1378   0.01560   0.00796  -0.0626   0.2866   1.0000
   7.250   1.1617   0.01592   0.00832  -0.0620   0.2665   1.0000
   7.500   1.1833   0.01643   0.00869  -0.0613   0.2338   1.0000
   7.750   1.2042   0.01712   0.00923  -0.0604   0.1973   1.0000
   8.000   1.2222   0.01822   0.01001  -0.0592   0.1434   1.0000
   8.250   1.2243   0.02119   0.01214  -0.0565   0.0371   1.0000
   8.500   1.2419   0.02229   0.01336  -0.0552   0.0311   1.0000
   8.750   1.2584   0.02344   0.01469  -0.0537   0.0285   1.0000
   9.000   1.2722   0.02479   0.01623  -0.0519   0.0269   1.0000
   9.250   1.2814   0.02640   0.01807  -0.0498   0.0258   1.0000
   9.500   1.2877   0.02807   0.01990  -0.0474   0.0253   1.0000
   9.750   1.2915   0.02963   0.02160  -0.0447   0.0250   1.0000
  10.000   1.2934   0.03134   0.02347  -0.0421   0.0246   1.0000
  10.250   1.2946   0.03327   0.02551  -0.0400   0.0240   1.0000
  10.500   1.2950   0.03545   0.02780  -0.0384   0.0233   1.0000
  10.750   1.2952   0.03785   0.03030  -0.0371   0.0227   1.0000
  11.000   1.2959   0.04038   0.03292  -0.0360   0.0225   1.0000
  11.250   1.2981   0.04289   0.03552  -0.0349   0.0223   1.0000
  11.500   1.3021   0.04528   0.03800  -0.0337   0.0221   1.0000
  11.750   1.3084   0.04753   0.04032  -0.0324   0.0221   1.0000
  12.000   1.3171   0.04964   0.04252  -0.0308   0.0221   1.0000
  12.250   1.3272   0.05180   0.04480  -0.0292   0.0224   1.0000
  12.500   1.3387   0.05409   0.04725  -0.0275   0.0228   1.0000
  12.750   1.3503   0.05673   0.05007  -0.0258   0.0235   1.0000
  13.000   1.3576   0.05984   0.05338  -0.0245   0.0240   1.0000
  13.250   1.3595   0.06334   0.05708  -0.0238   0.0242   1.0000
  13.500   1.3565   0.06711   0.06107  -0.0235   0.0243   1.0000
  13.750   1.3510   0.07128   0.06546  -0.0235   0.0244   1.0000
  14.500   1.3578   0.08379   0.07894  -0.0221   0.0356   1.0000
  14.750   1.3285   0.09017   0.08565  -0.0255   0.0363   1.0000
  15.000   1.3017   0.09711   0.09284  -0.0295   0.0367   1.0000
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