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GOE 122 (MVA H.2) AIRFOIL (goe122-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 122 (MVA H.2) AIRFOIL (goe122-il)
Reynolds number: 100,000
Max Cl/Cd: 55.83 at α=7.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe122-il-100000.txt
Download as CSV file: xf-goe122-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 122 (MVA H.2) 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.4186   0.10263   0.09788  -0.0038   1.0000   0.0585
  -8.000  -0.4154   0.10002   0.09532  -0.0070   1.0000   0.0606
  -7.750  -0.4139   0.09819   0.09357  -0.0142   1.0000   0.0619
  -7.500  -0.4023   0.09576   0.09112  -0.0255   1.0000   0.0624
  -7.250  -0.3969   0.08948   0.08494  -0.0202   1.0000   0.0637
  -7.000  -0.3872   0.08562   0.08111  -0.0169   1.0000   0.0661
  -6.750  -0.3763   0.08225   0.07774  -0.0186   1.0000   0.0691
  -6.500  -0.3623   0.07888   0.07438  -0.0240   1.0000   0.0737
  -6.250  -0.3395   0.07513   0.07048  -0.0369   1.0000   0.0769
  -6.000  -0.3364   0.07111   0.06663  -0.0305   1.0000   0.0799
  -5.750  -0.3234   0.06803   0.06356  -0.0313   1.0000   0.0846
  -5.500  -0.2972   0.06472   0.05997  -0.0417   1.0000   0.0913
  -5.250  -0.2937   0.06098   0.05643  -0.0376   1.0000   0.0936
  -5.000  -0.2845   0.05843   0.05391  -0.0365   1.0000   0.0985
  -4.750  -0.2662   0.05533   0.05058  -0.0406   1.0000   0.1069
  -4.500  -0.2609   0.05281   0.04817  -0.0378   1.0000   0.1109
  -4.250  -0.2440   0.05019   0.04534  -0.0399   1.0000   0.1221
  -3.750  -0.2237   0.04578   0.04097  -0.0376   1.0000   0.1424
  -3.500  -0.2095   0.04360   0.03872  -0.0377   1.0000   0.1562
  -3.250  -0.1951   0.04164   0.03670  -0.0376   1.0000   0.1719
  -2.000   0.0736   0.02504   0.01757  -0.0654   0.9598   0.1315
  -1.750   0.1282   0.02320   0.01484  -0.0685   0.9511   0.1056
  -1.500   0.1772   0.02092   0.01240  -0.0721   0.9425   0.1000
  -1.250   0.2202   0.01960   0.01084  -0.0742   0.9300   0.0972
  -1.000   0.2599   0.01865   0.00978  -0.0757   0.9161   0.1006
  -0.750   0.2952   0.01780   0.00887  -0.0762   0.9009   0.1011
  -0.500   0.3258   0.01711   0.00816  -0.0757   0.8843   0.1025
  -0.250   0.3524   0.01661   0.00763  -0.0744   0.8661   0.1050
   0.000   0.3767   0.01608   0.00713  -0.0729   0.8459   0.1103
   0.250   0.4013   0.01572   0.00671  -0.0712   0.8266   0.1225
   0.500   0.4264   0.01517   0.00634  -0.0697   0.8068   0.1696
   0.750   0.4554   0.01308   0.00600  -0.0687   0.7857   1.0000
   1.000   0.4798   0.01313   0.00574  -0.0671   0.7653   1.0000
   1.250   0.5045   0.01325   0.00565  -0.0658   0.7421   1.0000
   1.500   0.5294   0.01339   0.00555  -0.0645   0.7214   1.0000
   1.750   0.5546   0.01360   0.00558  -0.0635   0.6987   1.0000
   2.000   0.5799   0.01382   0.00560  -0.0625   0.6784   1.0000
   2.250   0.6055   0.01409   0.00571  -0.0617   0.6583   1.0000
   2.500   0.6313   0.01438   0.00588  -0.0610   0.6388   1.0000
   2.750   0.6571   0.01468   0.00604  -0.0604   0.6211   1.0000
   3.000   0.6832   0.01500   0.00625  -0.0598   0.6052   1.0000
   3.250   0.7094   0.01533   0.00650  -0.0593   0.5900   1.0000
   3.500   0.7355   0.01565   0.00679  -0.0589   0.5752   1.0000
   3.750   0.7616   0.01596   0.00706  -0.0584   0.5606   1.0000
   4.000   0.7877   0.01627   0.00735  -0.0580   0.5465   1.0000
   4.250   0.8139   0.01662   0.00773  -0.0576   0.5336   1.0000
   4.500   0.8402   0.01698   0.00812  -0.0572   0.5215   1.0000
   4.750   0.8663   0.01734   0.00850  -0.0568   0.5093   1.0000
   5.000   0.8919   0.01763   0.00880  -0.0563   0.4942   1.0000
   5.250   0.9167   0.01783   0.00901  -0.0555   0.4755   1.0000
   5.500   0.9414   0.01805   0.00915  -0.0547   0.4565   1.0000
   5.750   0.9665   0.01841   0.00952  -0.0541   0.4406   1.0000
   6.000   0.9912   0.01878   0.00999  -0.0535   0.4238   1.0000
   6.250   1.0149   0.01904   0.01036  -0.0527   0.4024   1.0000
   6.500   1.0386   0.01929   0.01060  -0.0519   0.3819   1.0000
   6.750   1.0623   0.01955   0.01106  -0.0512   0.3614   1.0000
   7.000   1.0854   0.01973   0.01135  -0.0503   0.3388   1.0000
   7.250   1.1076   0.01984   0.01164  -0.0494   0.3056   1.0000
   7.500   1.1282   0.02021   0.01195  -0.0483   0.2434   1.0000
   7.750   1.1404   0.02214   0.01318  -0.0466   0.1486   1.0000
   8.000   1.1540   0.02416   0.01476  -0.0451   0.0950   1.0000
   8.250   1.1683   0.02589   0.01643  -0.0436   0.0830   1.0000
   8.500   1.1804   0.02770   0.01829  -0.0417   0.0758   1.0000
   8.750   1.1927   0.02941   0.02006  -0.0399   0.0700   1.0000
   9.000   1.2025   0.03166   0.02219  -0.0377   0.0666   1.0000
   9.250   1.2199   0.03333   0.02402  -0.0361   0.0636   1.0000
   9.500   1.2371   0.03526   0.02602  -0.0348   0.0596   1.0000
   9.750   1.2587   0.03779   0.02850  -0.0339   0.0569   1.0000
  10.000   1.2875   0.04199   0.03271  -0.0338   0.0551   1.0000
  10.250   1.3024   0.04418   0.03532  -0.0322   0.0539   1.0000
  10.500   1.3143   0.04676   0.03832  -0.0305   0.0523   1.0000
  10.750   1.3246   0.05004   0.04201  -0.0288   0.0518   1.0000
  11.000   1.3300   0.05371   0.04610  -0.0269   0.0520   1.0000
  11.250   1.3301   0.05762   0.05041  -0.0249   0.0524   1.0000
  11.500   1.3255   0.06174   0.05489  -0.0229   0.0530   1.0000
  11.750   1.3163   0.06591   0.05936  -0.0208   0.0536   1.0000
  12.000   1.3036   0.07023   0.06392  -0.0190   0.0541   1.0000
  12.250   1.2905   0.07517   0.06908  -0.0180   0.0547   1.0000
  12.500   1.2817   0.08038   0.07450  -0.0176   0.0553   1.0000
  12.750   1.2609   0.08360   0.07795  -0.0176   0.0557   1.0000
  13.000   1.2304   0.08819   0.08286  -0.0200   0.0566   1.0000
  13.250   1.1821   0.09682   0.09182  -0.0269   0.0575   1.0000
  13.500   1.1382   0.10783   0.10303  -0.0356   0.0581   1.0000
  13.750   1.0592   0.13108   0.12638  -0.0536   0.0612   1.0000
  14.000   1.0243   0.14916   0.14439  -0.0635   0.0690   1.0000
  14.250   1.0373   0.14948   0.14475  -0.0614   0.0674   1.0000
  14.500   0.7522   0.16449   0.15979  -0.0544   0.1398   1.0000
  14.750   0.7397   0.16734   0.16263  -0.0565   0.1390   1.0000
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