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GOE 177 AIRFOIL (goe177-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 177 AIRFOIL (goe177-il)
Reynolds number: 100,000
Max Cl/Cd: 58.28 at α=7.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe177-il-100000.txt
Download as CSV file: xf-goe177-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 177 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
  ------ -------- --------- --------- -------- -------- --------
  -7.000  -0.3187   0.09172   0.08735  -0.0194   1.0000   0.0681
  -6.750  -0.3138   0.08897   0.08467  -0.0208   1.0000   0.0703
  -6.500  -0.3089   0.08643   0.08219  -0.0233   1.0000   0.0727
  -6.250  -0.3007   0.08507   0.08088  -0.0316   1.0000   0.0750
  -6.000  -0.2855   0.08310   0.07889  -0.0406   1.0000   0.0757
  -5.750  -0.2870   0.07757   0.07349  -0.0339   1.0000   0.0769
  -5.500  -0.2828   0.07429   0.07028  -0.0307   1.0000   0.0785
  -5.250  -0.2761   0.07152   0.06756  -0.0301   1.0000   0.0808
  -5.000  -0.2676   0.06881   0.06488  -0.0311   1.0000   0.0837
  -4.750  -0.2322   0.06708   0.06284  -0.0449   1.0000   0.0895
  -4.500  -0.2369   0.06278   0.05875  -0.0402   1.0000   0.0906
  -4.250  -0.2393   0.06051   0.05658  -0.0361   1.0000   0.0929
  -4.000  -0.2346   0.05865   0.05476  -0.0353   1.0000   0.0973
  -3.750  -0.1761   0.05306   0.04895  -0.0470   0.9918   0.1073
  -3.500  -0.1145   0.04785   0.04346  -0.0581   0.9832   0.1200
  -3.250  -0.0612   0.04343   0.03881  -0.0659   0.9727   0.1343
  -3.000  -0.0107   0.03996   0.03513  -0.0721   0.9620   0.1574
  -2.750   0.0607   0.03202   0.02634  -0.0821   0.9560   0.1093
  -2.500   0.1197   0.02498   0.01801  -0.0874   0.9472   0.0805
  -2.250   0.1707   0.02237   0.01483  -0.0915   0.9366   0.0938
  -2.000   0.2163   0.02034   0.01241  -0.0943   0.9231   0.1125
  -1.750   0.2564   0.01880   0.01067  -0.0960   0.9065   0.1396
  -1.500   0.2937   0.01764   0.00934  -0.0971   0.8885   0.1656
  -1.250   0.3272   0.01693   0.00849  -0.0973   0.8685   0.1890
  -1.000   0.3575   0.01623   0.00777  -0.0970   0.8470   0.2059
  -0.750   0.3861   0.01568   0.00714  -0.0962   0.8249   0.2203
  -0.500   0.4130   0.01526   0.00667  -0.0952   0.8031   0.2421
  -0.250   0.4389   0.01489   0.00633  -0.0940   0.7807   0.2762
   0.000   0.4640   0.01272   0.00583  -0.0923   0.7609   1.0000
   0.250   0.4903   0.01295   0.00563  -0.0914   0.7394   1.0000
   0.500   0.5164   0.01320   0.00555  -0.0905   0.7192   1.0000
   0.750   0.5424   0.01348   0.00555  -0.0897   0.6997   1.0000
   1.000   0.5683   0.01375   0.00561  -0.0890   0.6801   1.0000
   1.250   0.5943   0.01404   0.00568  -0.0883   0.6623   1.0000
   1.500   0.6205   0.01435   0.00577  -0.0877   0.6455   1.0000
   1.750   0.6465   0.01465   0.00594  -0.0872   0.6278   1.0000
   2.000   0.6726   0.01497   0.00612  -0.0867   0.6114   1.0000
   2.250   0.6989   0.01531   0.00633  -0.0862   0.5963   1.0000
   2.500   0.7252   0.01567   0.00660  -0.0858   0.5823   1.0000
   2.750   0.7515   0.01602   0.00686  -0.0854   0.5686   1.0000
   3.000   0.7774   0.01634   0.00708  -0.0849   0.5541   1.0000
   3.250   0.8031   0.01663   0.00728  -0.0844   0.5393   1.0000
   3.500   0.8288   0.01691   0.00752  -0.0838   0.5250   1.0000
   3.750   0.8546   0.01722   0.00779  -0.0834   0.5121   1.0000
   4.000   0.8807   0.01756   0.00808  -0.0830   0.5009   1.0000
   4.250   0.9067   0.01787   0.00833  -0.0825   0.4898   1.0000
   4.500   0.9323   0.01817   0.00865  -0.0821   0.4780   1.0000
   4.750   0.9578   0.01849   0.00908  -0.0817   0.4666   1.0000
   5.000   0.9836   0.01885   0.00949  -0.0813   0.4570   1.0000
   5.250   1.0094   0.01914   0.00977  -0.0809   0.4472   1.0000
   5.500   1.0330   0.01918   0.00987  -0.0800   0.4297   1.0000
   5.750   1.0575   0.01936   0.01013  -0.0794   0.4165   1.0000
   6.000   1.0812   0.01945   0.01028  -0.0786   0.4003   1.0000
   6.250   1.1040   0.01948   0.01032  -0.0776   0.3810   1.0000
   6.500   1.1274   0.01966   0.01054  -0.0768   0.3650   1.0000
   6.750   1.1504   0.01988   0.01086  -0.0760   0.3468   1.0000
   7.000   1.1727   0.02013   0.01123  -0.0751   0.3249   1.0000
   7.250   1.1959   0.02052   0.01176  -0.0742   0.3092   1.0000
   7.500   1.2183   0.02091   0.01233  -0.0733   0.2843   1.0000
   7.750   1.2389   0.02147   0.01293  -0.0722   0.2396   1.0000
   8.000   1.2415   0.02433   0.01474  -0.0696   0.0941   1.0000
   8.250   1.2447   0.02730   0.01739  -0.0670   0.0530   1.0000
   8.500   1.2543   0.02925   0.01958  -0.0647   0.0448   1.0000
   8.750   1.2619   0.03113   0.02173  -0.0623   0.0408   1.0000
   9.000   1.2622   0.03342   0.02420  -0.0595   0.0388   1.0000
   9.250   1.2652   0.03520   0.02615  -0.0567   0.0376   1.0000
   9.500   1.2653   0.03712   0.02823  -0.0537   0.0367   1.0000
   9.750   1.2656   0.03923   0.03045  -0.0512   0.0359   1.0000
  10.000   1.2685   0.04137   0.03267  -0.0489   0.0353   1.0000
  10.250   1.2772   0.04341   0.03474  -0.0467   0.0347   1.0000
  10.500   1.2952   0.04538   0.03672  -0.0447   0.0342   1.0000
  10.750   1.3138   0.04750   0.03893  -0.0431   0.0330   1.0000
  11.000   1.3289   0.04978   0.04132  -0.0418   0.0316   1.0000
  11.250   1.3508   0.05260   0.04425  -0.0408   0.0309   1.0000
  11.500   1.3731   0.05626   0.04832  -0.0397   0.0317   1.0000
  11.750   1.3746   0.06002   0.05251  -0.0376   0.0326   1.0000
  12.000   1.3691   0.06390   0.05678  -0.0357   0.0335   1.0000
  12.250   1.3600   0.06799   0.06121  -0.0343   0.0342   1.0000
  12.500   1.3483   0.07235   0.06587  -0.0335   0.0349   1.0000
  12.750   1.3348   0.07699   0.07079  -0.0333   0.0355   1.0000
  13.000   1.3196   0.08200   0.07605  -0.0339   0.0360   1.0000
  13.250   1.3030   0.08735   0.08163  -0.0351   0.0364   1.0000
  13.500   1.2856   0.09307   0.08756  -0.0370   0.0369   1.0000
  13.750   1.2675   0.09917   0.09385  -0.0394   0.0372   1.0000
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