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GOE 648 AIRFOIL (goe648-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 648 AIRFOIL (goe648-il)
Reynolds number: 200,000
Max Cl/Cd: 57.42 at α=6.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe648-il-200000.txt
Download as CSV file: xf-goe648-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 648 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
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.5181   0.06878   0.06503  -0.0669   1.0000   0.0554
 -10.750  -0.5425   0.06466   0.06094  -0.0670   1.0000   0.0550
 -10.500  -0.5738   0.06155   0.05784  -0.0657   1.0000   0.0548
 -10.250  -0.6098   0.05978   0.05609  -0.0620   1.0000   0.0545
 -10.000  -0.6460   0.05823   0.05451  -0.0569   1.0000   0.0543
  -9.750  -0.6737   0.05107   0.04695  -0.0596   0.9944   0.0538
  -9.500  -0.6813   0.04306   0.03815  -0.0633   0.9847   0.0544
  -9.250  -0.6750   0.03789   0.03215  -0.0646   0.9771   0.0556
  -9.000  -0.6426   0.03693   0.03136  -0.0662   0.9725   0.0570
  -8.750  -0.6098   0.03529   0.02959  -0.0685   0.9688   0.0586
  -8.500  -0.5907   0.03311   0.02706  -0.0683   0.9614   0.0602
  -8.250  -0.5644   0.03092   0.02421  -0.0692   0.9560   0.0624
  -8.000  -0.5275   0.02931   0.02265  -0.0718   0.9535   0.0644
  -7.750  -0.5062   0.02840   0.02170  -0.0709   0.9451   0.0660
  -7.500  -0.4718   0.02714   0.02015  -0.0724   0.9410   0.0688
  -7.250  -0.4341   0.02563   0.01841  -0.0746   0.9384   0.0716
  -7.000  -0.4128   0.02486   0.01766  -0.0735   0.9296   0.0736
  -6.750  -0.3759   0.02392   0.01659  -0.0752   0.9256   0.0768
  -6.500  -0.3356   0.02273   0.01524  -0.0775   0.9230   0.0807
  -6.250  -0.3100   0.02201   0.01457  -0.0770   0.9147   0.0838
  -6.000  -0.2703   0.02117   0.01358  -0.0789   0.9100   0.0885
  -5.750  -0.2251   0.01993   0.01242  -0.0821   0.9074   0.0943
  -5.500  -0.1762   0.01893   0.01133  -0.0857   0.9054   0.1013
  -5.250  -0.1538   0.01826   0.01076  -0.0845   0.8946   0.1068
  -5.000  -0.1118   0.01739   0.00987  -0.0868   0.8907   0.1150
  -4.750  -0.0793   0.01681   0.00932  -0.0874   0.8833   0.1230
  -4.500  -0.0461   0.01609   0.00865  -0.0880   0.8752   0.1316
  -4.250  -0.0072   0.01546   0.00800  -0.0897   0.8691   0.1425
  -4.000   0.0189   0.01498   0.00757  -0.0889   0.8575   0.1535
  -3.750   0.0488   0.01444   0.00708  -0.0889   0.8476   0.1685
  -3.500   0.0782   0.01389   0.00662  -0.0889   0.8375   0.1917
  -3.250   0.1019   0.01338   0.00632  -0.0878   0.8258   0.2305
  -3.000   0.1318   0.01284   0.00597  -0.0879   0.8163   0.2929
  -2.750   0.1529   0.01248   0.00581  -0.0863   0.8028   0.3453
  -2.500   0.1763   0.01215   0.00566  -0.0851   0.7905   0.4020
  -2.250   0.2031   0.01185   0.00552  -0.0845   0.7796   0.4668
  -2.000   0.2244   0.01168   0.00549  -0.0827   0.7658   0.5226
  -1.750   0.2473   0.01152   0.00543  -0.0812   0.7522   0.5705
  -1.500   0.2716   0.01138   0.00534  -0.0799   0.7389   0.6132
  -1.250   0.2962   0.01124   0.00525  -0.0787   0.7252   0.6541
  -1.000   0.3185   0.01115   0.00523  -0.0769   0.7100   0.6931
  -0.750   0.3407   0.01109   0.00523  -0.0751   0.6948   0.7335
  -0.500   0.3631   0.01104   0.00522  -0.0733   0.6795   0.7733
  -0.250   0.3861   0.01100   0.00519  -0.0716   0.6635   0.8122
   0.000   0.4117   0.01097   0.00517  -0.0704   0.6464   0.8524
   0.250   0.4470   0.01102   0.00518  -0.0711   0.6265   0.8924
   0.500   0.4949   0.01121   0.00523  -0.0746   0.6036   0.9245
   0.750   0.5429   0.01146   0.00530  -0.0783   0.5785   0.9502
   1.000   0.5903   0.01174   0.00537  -0.0821   0.5489   0.9691
   1.250   0.6364   0.01204   0.00544  -0.0858   0.5161   0.9866
   1.500   0.6813   0.01236   0.00550  -0.0895   0.4844   1.0000
   1.750   0.6887   0.01253   0.00550  -0.0860   0.4649   1.0000
   2.000   0.7011   0.01276   0.00556  -0.0831   0.4475   1.0000
   2.250   0.7164   0.01303   0.00567  -0.0808   0.4325   1.0000
   2.500   0.7334   0.01334   0.00579  -0.0787   0.4203   1.0000
   2.750   0.7523   0.01360   0.00596  -0.0770   0.4088   1.0000
   3.000   0.7718   0.01391   0.00614  -0.0753   0.3994   1.0000
   3.250   0.7918   0.01420   0.00633  -0.0738   0.3904   1.0000
   3.500   0.8130   0.01454   0.00655  -0.0725   0.3830   1.0000
   3.750   0.8341   0.01482   0.00679  -0.0712   0.3755   1.0000
   4.000   0.8568   0.01524   0.00704  -0.0703   0.3690   1.0000
   4.250   0.8785   0.01552   0.00732  -0.0690   0.3628   1.0000
   4.500   0.9004   0.01583   0.00759  -0.0679   0.3565   1.0000
   4.750   0.9258   0.01633   0.00792  -0.0676   0.3508   1.0000
   5.000   0.9468   0.01659   0.00824  -0.0662   0.3456   1.0000
   5.250   0.9691   0.01692   0.00855  -0.0652   0.3401   1.0000
   5.500   0.9938   0.01737   0.00889  -0.0647   0.3348   1.0000
   5.750   1.0165   0.01777   0.00930  -0.0638   0.3299   1.0000
   6.000   1.0380   0.01810   0.00965  -0.0627   0.3248   1.0000
   6.250   1.0612   0.01848   0.01000  -0.0619   0.3200   1.0000
   6.500   1.0885   0.01909   0.01050  -0.0620   0.3150   1.0000
   6.750   1.1068   0.01938   0.01089  -0.0603   0.3104   1.0000
   7.000   1.1277   0.01973   0.01127  -0.0591   0.3054   1.0000
   7.250   1.1513   0.02017   0.01166  -0.0585   0.3009   1.0000
   7.500   1.1764   0.02078   0.01223  -0.0582   0.2964   1.0000
   7.750   1.1938   0.02112   0.01268  -0.0564   0.2919   1.0000
   8.000   1.2139   0.02150   0.01309  -0.0552   0.2872   1.0000
   8.250   1.2372   0.02196   0.01348  -0.0545   0.2828   1.0000
   8.500   1.2587   0.02254   0.01409  -0.0537   0.2784   1.0000
   8.750   1.2743   0.02292   0.01459  -0.0517   0.2741   1.0000
   9.000   1.2933   0.02333   0.01503  -0.0503   0.2698   1.0000
   9.250   1.3158   0.02380   0.01544  -0.0496   0.2658   1.0000
   9.500   1.3353   0.02440   0.01609  -0.0485   0.2617   1.0000
   9.750   1.3459   0.02477   0.01660  -0.0457   0.2573   1.0000
  10.000   1.3590   0.02510   0.01695  -0.0433   0.2530   1.0000
  10.250   1.3774   0.02548   0.01727  -0.0419   0.2490   1.0000
  10.500   1.3896   0.02603   0.01790  -0.0396   0.2449   1.0000
  10.750   1.3983   0.02652   0.01851  -0.0367   0.2410   1.0000
  11.000   1.4110   0.02697   0.01901  -0.0346   0.2372   1.0000
  11.250   1.4272   0.02740   0.01942  -0.0331   0.2337   1.0000
  11.500   1.4440   0.02807   0.02010  -0.0318   0.2301   1.0000
  11.750   1.4491   0.02873   0.02093  -0.0288   0.2265   1.0000
  12.000   1.4587   0.02933   0.02162  -0.0266   0.2229   1.0000
  12.250   1.4704   0.02983   0.02212  -0.0247   0.2193   1.0000
  12.500   1.4896   0.03046   0.02268  -0.0240   0.2156   1.0000
  12.750   1.4897   0.03139   0.02382  -0.0209   0.2124   1.0000
  13.000   1.4952   0.03225   0.02480  -0.0187   0.2087   1.0000
  13.250   1.5046   0.03302   0.02561  -0.0170   0.2054   1.0000
  13.500   1.5194   0.03372   0.02628  -0.0159   0.2023   1.0000
  13.750   1.5263   0.03485   0.02752  -0.0143   0.1992   1.0000
  14.000   1.5274   0.03617   0.02901  -0.0122   0.1960   1.0000
  14.250   1.5319   0.03736   0.03030  -0.0106   0.1926   1.0000
  14.500   1.5397   0.03839   0.03135  -0.0093   0.1894   1.0000
  14.750   1.5520   0.03939   0.03232  -0.0084   0.1859   1.0000
  15.000   1.5469   0.04137   0.03453  -0.0067   0.1829   1.0000
  15.250   1.5462   0.04316   0.03645  -0.0055   0.1794   1.0000
  15.500   1.5496   0.04470   0.03803  -0.0045   0.1760   1.0000
  15.750   1.5621   0.04574   0.03899  -0.0039   0.1722   1.0000
  16.000   1.5507   0.04865   0.04216  -0.0029   0.1692   1.0000
  16.250   1.5456   0.05123   0.04488  -0.0023   0.1655   1.0000
  16.500   1.5458   0.05339   0.04709  -0.0020   0.1619   1.0000
  16.750   1.5493   0.05535   0.04904  -0.0017   0.1579   1.0000
  17.000   1.5342   0.05941   0.05333  -0.0019   0.1542   1.0000
  17.250   1.5268   0.06277   0.05679  -0.0023   0.1500   1.0000
  17.500   1.5315   0.06473   0.05864  -0.0023   0.1453   1.0000
  17.750   1.5085   0.07038   0.06458  -0.0037   0.1413   1.0000
  18.000   1.4959   0.07485   0.06914  -0.0050   0.1366   1.0000
  18.250   1.4922   0.07811   0.07237  -0.0057   0.1318   1.0000
  18.500   1.4672   0.08472   0.07919  -0.0080   0.1272   1.0000
  18.750   1.4599   0.08876   0.08322  -0.0094   0.1228   1.0000
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