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GOE 167 (V.KARMAN PROP.2) AIRFOIL (goe167-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 167 (V.KARMAN PROP.2) AIRFOIL (goe167-il)
Reynolds number: 100,000
Max Cl/Cd: 58.04 at α=8.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe167-il-100000.txt
Download as CSV file: xf-goe167-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 167 (V.KARMAN PROP.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
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3585   0.10437   0.09975  -0.0210   1.0000   0.0691
  -8.250  -0.3662   0.10302   0.09851  -0.0263   1.0000   0.0702
  -8.000  -0.3666   0.10083   0.09638  -0.0362   1.0000   0.0707
  -7.750  -0.3556   0.09443   0.09004  -0.0296   1.0000   0.0721
  -7.500  -0.3437   0.09064   0.08627  -0.0268   1.0000   0.0744
  -7.250  -0.3364   0.08746   0.08314  -0.0279   1.0000   0.0769
  -7.000  -0.3304   0.08430   0.08004  -0.0307   1.0000   0.0799
  -6.750  -0.3250   0.08158   0.07735  -0.0388   1.0000   0.0836
  -6.500  -0.3223   0.07953   0.07517  -0.0469   1.0000   0.0850
  -6.250  -0.3251   0.07530   0.07122  -0.0406   1.0000   0.0862
  -6.000  -0.3258   0.07319   0.06925  -0.0373   0.9970   0.0883
  -5.750  -0.2650   0.06741   0.06302  -0.0566   0.9834   0.0996
  -5.500  -0.2345   0.06192   0.05768  -0.0578   0.9729   0.1034
  -5.250  -0.1829   0.05662   0.05204  -0.0698   0.9579   0.1149
  -4.750  -0.1156   0.04907   0.04429  -0.0772   0.9143   0.1362
  -4.500  -0.0886   0.04599   0.04101  -0.0794   0.8885   0.1494
  -4.250  -0.0647   0.04337   0.03817  -0.0803   0.8662   0.1643
  -4.000  -0.0410   0.04152   0.03603  -0.0810   0.8439   0.1863
  -3.750  -0.0208   0.03905   0.03342  -0.0808   0.8258   0.2078
  -3.500  -0.0008   0.03719   0.03146  -0.0801   0.8098   0.2389
  -2.750   0.0526   0.03236   0.02667  -0.0747   0.7710   0.3791
  -2.500   0.0710   0.03076   0.02507  -0.0723   0.7615   0.4273
  -2.250   0.1743   0.02783   0.01926  -0.0859   0.7515   0.1426
  -2.000   0.2048   0.02568   0.01683  -0.0859   0.7437   0.1244
  -1.750   0.2371   0.02511   0.01570  -0.0856   0.7349   0.1130
  -1.500   0.2658   0.02354   0.01402  -0.0857   0.7276   0.1083
  -1.250   0.2956   0.02267   0.01290  -0.0856   0.7198   0.1039
  -1.000   0.3249   0.02209   0.01204  -0.0854   0.7137   0.1014
  -0.750   0.3541   0.02154   0.01142  -0.0855   0.7068   0.1011
  -0.500   0.3821   0.02099   0.01083  -0.0853   0.7015   0.1031
  -0.250   0.4103   0.02066   0.01055  -0.0855   0.6954   0.1087
   0.000   0.4383   0.02038   0.01025  -0.0854   0.6895   0.1125
   0.250   0.4653   0.01999   0.00986  -0.0851   0.6852   0.1176
   0.500   0.4938   0.01995   0.00983  -0.0855   0.6794   0.1274
   0.750   0.5229   0.01973   0.00970  -0.0858   0.6747   0.1569
   1.000   0.5473   0.01769   0.00951  -0.0843   0.6710   1.0000
   1.250   0.5757   0.01816   0.00981  -0.0848   0.6658   1.0000
   1.500   0.6037   0.01858   0.01012  -0.0851   0.6607   1.0000
   1.750   0.6316   0.01895   0.01034  -0.0852   0.6565   1.0000
   2.000   0.6592   0.01946   0.01080  -0.0855   0.6516   1.0000
   2.250   0.6866   0.01989   0.01119  -0.0858   0.6455   1.0000
   2.500   0.7140   0.02016   0.01134  -0.0854   0.6403   1.0000
   2.750   0.7407   0.02071   0.01194  -0.0858   0.6333   1.0000
   3.000   0.7680   0.02107   0.01225  -0.0857   0.6278   1.0000
   3.250   0.7949   0.02150   0.01265  -0.0857   0.6225   1.0000
   3.500   0.8212   0.02203   0.01323  -0.0859   0.6157   1.0000
   3.750   0.8487   0.02227   0.01342  -0.0855   0.6104   1.0000
   4.000   0.8741   0.02286   0.01412  -0.0856   0.6026   1.0000
   4.250   0.9013   0.02314   0.01439  -0.0854   0.5968   1.0000
   4.500   0.9271   0.02373   0.01507  -0.0854   0.5908   1.0000
   4.750   0.9532   0.02410   0.01550  -0.0851   0.5834   1.0000
   5.000   0.9791   0.02437   0.01580  -0.0847   0.5750   1.0000
   5.250   1.0063   0.02425   0.01566  -0.0839   0.5656   1.0000
   5.500   1.0311   0.02447   0.01598  -0.0833   0.5545   1.0000
   5.750   1.0578   0.02454   0.01607  -0.0828   0.5459   1.0000
   6.000   1.0835   0.02483   0.01647  -0.0824   0.5374   1.0000
   6.250   1.1088   0.02511   0.01689  -0.0819   0.5284   1.0000
   6.500   1.1367   0.02494   0.01672  -0.0813   0.5194   1.0000
   6.750   1.1606   0.02519   0.01715  -0.0807   0.5079   1.0000
   7.000   1.1860   0.02530   0.01739  -0.0801   0.4976   1.0000
   7.250   1.2142   0.02505   0.01718  -0.0796   0.4884   1.0000
   7.500   1.2387   0.02486   0.01713  -0.0787   0.4744   1.0000
   7.750   1.2642   0.02424   0.01656  -0.0776   0.4581   1.0000
   8.000   1.2858   0.02388   0.01645  -0.0763   0.4376   1.0000
   8.250   1.3089   0.02350   0.01624  -0.0752   0.4177   1.0000
   8.500   1.3304   0.02332   0.01624  -0.0739   0.3924   1.0000
   8.750   1.3501   0.02326   0.01624  -0.0724   0.3571   1.0000
   9.000   1.3622   0.02387   0.01655  -0.0701   0.2909   1.0000
   9.250   1.3606   0.02599   0.01812  -0.0666   0.2240   1.0000
   9.500   1.3517   0.02880   0.02043  -0.0627   0.1368   1.0000
   9.750   1.3338   0.03190   0.02308  -0.0579   0.1034   1.0000
  10.000   1.3159   0.03505   0.02615  -0.0537   0.0902   1.0000
  10.250   1.2986   0.03878   0.02984  -0.0509   0.0818   1.0000
  10.500   1.2872   0.04243   0.03355  -0.0491   0.0739   1.0000
  10.750   1.2781   0.04593   0.03703  -0.0473   0.0684   1.0000
  11.000   1.2781   0.04864   0.03978  -0.0458   0.0625   1.0000
  11.250   1.2844   0.05067   0.04160  -0.0429   0.0572   1.0000
  11.500   1.2986   0.05227   0.04333  -0.0411   0.0535   1.0000
  11.750   1.3191   0.05364   0.04472  -0.0390   0.0502   1.0000
  12.000   1.3697   0.05534   0.04622  -0.0372   0.0461   1.0000
  12.250   1.3744   0.05765   0.04885  -0.0358   0.0448   1.0000
  12.500   1.3823   0.06022   0.05170  -0.0347   0.0432   1.0000
  12.750   1.3922   0.06320   0.05495  -0.0335   0.0423   1.0000
  13.000   1.3963   0.06660   0.05865  -0.0324   0.0418   1.0000
  13.250   1.3947   0.07034   0.06270  -0.0314   0.0417   1.0000
  13.500   1.3881   0.07443   0.06711  -0.0307   0.0416   1.0000
  13.750   1.3775   0.07887   0.07186  -0.0304   0.0418   1.0000
  14.000   1.3636   0.08370   0.07698  -0.0306   0.0420   1.0000
  14.250   1.3474   0.08890   0.08246  -0.0313   0.0423   1.0000
  14.500   1.3291   0.09450   0.08833  -0.0326   0.0426   1.0000
  14.750   1.3090   0.10052   0.09460  -0.0345   0.0429   1.0000
  15.000   1.2876   0.10696   0.10126  -0.0370   0.0433   1.0000
  15.250   1.2653   0.11384   0.10835  -0.0402   0.0438   1.0000
  15.500   1.2429   0.12123   0.11592  -0.0441   0.0442   1.0000
  15.750   1.2205   0.12921   0.12407  -0.0486   0.0447   1.0000
  16.000   1.1993   0.13770   0.13269  -0.0537   0.0453   1.0000
  16.250   1.1821   0.14620   0.14130  -0.0585   0.0459   1.0000
  16.500   1.1734   0.15355   0.14875  -0.0623   0.0468   1.0000
  16.750   1.0760   0.19919   0.19439  -0.0937   0.0690   1.0000
  17.000   0.8130   0.17442   0.16999  -0.0590   0.0711   1.0000
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