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GOE 602 AIRFOIL (goe602-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 602 AIRFOIL (goe602-il)
Reynolds number: 200,000
Max Cl/Cd: 77.49 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe602-il-200000.txt
Download as CSV file: xf-goe602-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 602 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
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3943   0.09740   0.09402  -0.0414   1.0000   0.0457
  -8.750  -0.4058   0.09482   0.09151  -0.0415   1.0000   0.0458
  -8.500  -0.4200   0.09254   0.08932  -0.0405   1.0000   0.0459
  -8.250  -0.4258   0.08750   0.08434  -0.0374   1.0000   0.0469
  -8.000  -0.4253   0.08558   0.08244  -0.0341   1.0000   0.0478
  -7.750  -0.4366   0.08396   0.08088  -0.0312   1.0000   0.0483
  -7.500  -0.4496   0.08200   0.07898  -0.0292   1.0000   0.0487
  -7.250  -0.4577   0.07964   0.07666  -0.0282   1.0000   0.0495
  -7.000  -0.4652   0.07692   0.07398  -0.0280   1.0000   0.0503
  -6.750  -0.4713   0.07380   0.07087  -0.0284   1.0000   0.0514
  -6.500  -0.4735   0.07006   0.06712  -0.0302   0.9997   0.0530
  -6.250  -0.4417   0.05713   0.05355  -0.0500   0.9915   0.0590
  -6.000  -0.4187   0.05438   0.05096  -0.0507   0.9879   0.0610
  -5.750  -0.3884   0.05114   0.04761  -0.0545   0.9841   0.0656
  -5.500  -0.3634   0.04555   0.04163  -0.0595   0.9772   0.0743
  -5.250  -0.3298   0.04179   0.03736  -0.0641   0.9724   0.0863
  -5.000  -0.3028   0.03901   0.03467  -0.0655   0.9677   0.0899
  -4.750  -0.2714   0.02742   0.02145  -0.0663   0.9630   0.0504
  -4.500  -0.2350   0.02499   0.01857  -0.0682   0.9595   0.0523
  -4.250  -0.1955   0.02243   0.01549  -0.0702   0.9572   0.0523
  -4.000  -0.1681   0.02119   0.01397  -0.0700   0.9496   0.0549
  -3.750  -0.1286   0.02008   0.01256  -0.0720   0.9459   0.0575
  -3.500  -0.0881   0.01842   0.01076  -0.0744   0.9436   0.0601
  -3.250  -0.0606   0.01766   0.01001  -0.0743   0.9355   0.0646
  -3.000  -0.0209   0.01683   0.00912  -0.0765   0.9318   0.0684
  -2.750   0.0212   0.01593   0.00821  -0.0792   0.9293   0.0736
  -2.500   0.0478   0.01544   0.00776  -0.0789   0.9205   0.0812
  -2.250   0.0887   0.01471   0.00704  -0.0814   0.9172   0.0963
  -2.000   0.1277   0.01306   0.00644  -0.0842   0.9150   0.3364
  -1.750   0.1493   0.01230   0.00633  -0.0829   0.9056   0.5065
  -1.500   0.1825   0.01145   0.00614  -0.0834   0.9021   0.7032
  -1.250   0.2358   0.01082   0.00603  -0.0871   0.9012   0.9200
  -1.000   0.3242   0.01055   0.00563  -0.0995   0.9023   1.0000
  -0.750   0.3521   0.01041   0.00538  -0.0994   0.8925   1.0000
  -0.500   0.3908   0.01015   0.00500  -0.1013   0.8865   1.0000
  -0.250   0.4157   0.01006   0.00481  -0.1005   0.8749   1.0000
   0.000   0.4431   0.00995   0.00461  -0.1001   0.8640   1.0000
   0.250   0.4726   0.00982   0.00440  -0.1001   0.8537   1.0000
   0.500   0.5021   0.00969   0.00418  -0.1001   0.8429   1.0000
   0.750   0.5270   0.00963   0.00406  -0.0992   0.8293   1.0000
   1.000   0.5523   0.00959   0.00394  -0.0984   0.8153   1.0000
   1.250   0.5780   0.00956   0.00384  -0.0976   0.8006   1.0000
   1.500   0.6041   0.00955   0.00375  -0.0969   0.7853   1.0000
   1.750   0.6278   0.00959   0.00372  -0.0958   0.7673   1.0000
   2.000   0.6523   0.00964   0.00368  -0.0948   0.7482   1.0000
   2.250   0.6775   0.00971   0.00365  -0.0940   0.7287   1.0000
   2.500   0.7010   0.00984   0.00369  -0.0929   0.7084   1.0000
   2.750   0.7248   0.00998   0.00375  -0.0918   0.6884   1.0000
   3.000   0.7490   0.01016   0.00383  -0.0909   0.6701   1.0000
   3.250   0.7721   0.01035   0.00398  -0.0898   0.6506   1.0000
   3.500   0.7953   0.01055   0.00412  -0.0888   0.6311   1.0000
   3.750   0.8186   0.01078   0.00426  -0.0877   0.6125   1.0000
   4.000   0.8416   0.01100   0.00447  -0.0867   0.5940   1.0000
   4.250   0.8646   0.01124   0.00468  -0.0856   0.5760   1.0000
   4.500   0.8876   0.01150   0.00490  -0.0846   0.5582   1.0000
   4.750   0.9101   0.01177   0.00512  -0.0835   0.5398   1.0000
   5.000   0.9314   0.01202   0.00537  -0.0821   0.5173   1.0000
   5.250   0.9509   0.01231   0.00557  -0.0804   0.4895   1.0000
   5.500   0.9697   0.01263   0.00579  -0.0786   0.4594   1.0000
   5.750   0.9883   0.01298   0.00606  -0.0769   0.4288   1.0000
   6.000   1.0077   0.01335   0.00637  -0.0753   0.4012   1.0000
   6.250   1.0259   0.01376   0.00672  -0.0735   0.3691   1.0000
   6.500   1.0420   0.01428   0.00709  -0.0714   0.3259   1.0000
   6.750   1.0542   0.01507   0.00756  -0.0688   0.2654   1.0000
   7.000   1.0639   0.01617   0.00822  -0.0659   0.1914   1.0000
   7.250   1.0667   0.01793   0.00929  -0.0622   0.0942   1.0000
   7.500   1.0746   0.01934   0.01034  -0.0591   0.0454   1.0000
   7.750   1.0873   0.02030   0.01133  -0.0565   0.0386   1.0000
   8.000   1.0982   0.02125   0.01237  -0.0537   0.0357   1.0000
   8.250   1.1051   0.02240   0.01365  -0.0503   0.0337   1.0000
   8.500   1.1131   0.02347   0.01484  -0.0472   0.0323   1.0000
   8.750   1.1210   0.02459   0.01607  -0.0443   0.0308   1.0000
   9.000   1.1276   0.02586   0.01744  -0.0413   0.0296   1.0000
   9.250   1.1340   0.02725   0.01893  -0.0385   0.0288   1.0000
   9.500   1.1412   0.02876   0.02051  -0.0359   0.0281   1.0000
   9.750   1.1504   0.03036   0.02217  -0.0337   0.0275   1.0000
  10.000   1.1633   0.03209   0.02396  -0.0319   0.0270   1.0000
  10.250   1.1825   0.03410   0.02599  -0.0309   0.0263   1.0000
  10.500   1.2333   0.03912   0.03111  -0.0346   0.0247   1.0000
  10.750   1.2608   0.04221   0.03447  -0.0351   0.0248   1.0000
  11.000   1.2756   0.04419   0.03665  -0.0335   0.0250   1.0000
  11.250   1.2848   0.04590   0.03858  -0.0312   0.0253   1.0000
  11.500   1.2882   0.04737   0.04029  -0.0280   0.0257   1.0000
  11.750   1.2845   0.04902   0.04236  -0.0241   0.0271   1.0000
  12.000   1.2701   0.05325   0.04721  -0.0199   0.0298   1.0000
  12.250   1.2698   0.06285   0.05757  -0.0176   0.0415   1.0000
  12.750   1.1583   0.06038   0.05556  -0.0091   0.0357   1.0000
  13.000   1.1191   0.06671   0.06227  -0.0083   0.0368   1.0000
  13.250   1.0855   0.07344   0.06930  -0.0090   0.0376   1.0000
  13.500   1.0558   0.07985   0.07593  -0.0106   0.0378   1.0000
  13.750   1.0275   0.08616   0.08242  -0.0130   0.0376   1.0000
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