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GOE 655 AIRFOIL (goe655-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 655 AIRFOIL (goe655-il)
Reynolds number: 200,000
Max Cl/Cd: 64.93 at α=7.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe655-il-200000-n5.txt
Download as CSV file: xf-goe655-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 655 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.3612   0.09654   0.09285  -0.0478   1.0000   0.0298
 -11.000  -0.3620   0.09401   0.09036  -0.0477   1.0000   0.0300
 -10.500  -0.5965   0.04586   0.04174  -0.0811   0.9878   0.0301
 -10.250  -0.5716   0.04423   0.04007  -0.0841   0.9831   0.0307
 -10.000  -0.5585   0.04132   0.03695  -0.0866   0.9750   0.0313
  -9.750  -0.5448   0.03821   0.03354  -0.0888   0.9677   0.0321
  -9.500  -0.5296   0.03472   0.02961  -0.0908   0.9608   0.0330
  -9.250  -0.5151   0.03173   0.02612  -0.0914   0.9529   0.0342
  -9.000  -0.4924   0.02937   0.02334  -0.0925   0.9472   0.0353
  -8.750  -0.4600   0.02811   0.02200  -0.0944   0.9441   0.0361
  -8.500  -0.4383   0.02704   0.02080  -0.0939   0.9354   0.0368
  -8.250  -0.4081   0.02581   0.01939  -0.0951   0.9304   0.0378
  -8.000  -0.3824   0.02467   0.01804  -0.0952   0.9230   0.0390
  -7.750  -0.3552   0.02347   0.01657  -0.0955   0.9157   0.0401
  -7.500  -0.3251   0.02231   0.01512  -0.0962   0.9099   0.0410
  -7.250  -0.3006   0.02127   0.01401  -0.0958   0.9004   0.0418
  -7.000  -0.2688   0.02043   0.01314  -0.0968   0.8944   0.0429
  -6.750  -0.2439   0.01980   0.01244  -0.0963   0.8838   0.0440
  -6.500  -0.2147   0.01908   0.01162  -0.0965   0.8755   0.0453
  -6.250  -0.1868   0.01836   0.01078  -0.0964   0.8648   0.0464
  -6.000  -0.1600   0.01772   0.01001  -0.0961   0.8523   0.0475
  -5.750  -0.1325   0.01713   0.00928  -0.0958   0.8381   0.0486
  -5.500  -0.1061   0.01646   0.00859  -0.0954   0.8216   0.0502
  -5.250  -0.0794   0.01600   0.00805  -0.0950   0.8054   0.0519
  -5.000  -0.0529   0.01558   0.00753  -0.0946   0.7910   0.0537
  -4.750  -0.0265   0.01519   0.00703  -0.0941   0.7788   0.0555
  -4.500  -0.0006   0.01484   0.00657  -0.0935   0.7665   0.0574
  -4.250   0.0243   0.01445   0.00614  -0.0929   0.7544   0.0600
  -4.000   0.0501   0.01419   0.00579  -0.0923   0.7427   0.0636
  -3.500   0.1009   0.01367   0.00514  -0.0910   0.7195   0.0735
  -3.250   0.1264   0.01345   0.00486  -0.0904   0.7088   0.0811
  -3.000   0.1517   0.01320   0.00461  -0.0898   0.6978   0.0955
  -2.750   0.1760   0.01290   0.00442  -0.0891   0.6859   0.1275
  -2.500   0.2006   0.01266   0.00429  -0.0884   0.6739   0.1712
  -2.250   0.2253   0.01248   0.00418  -0.0877   0.6616   0.2116
  -2.000   0.2500   0.01234   0.00410  -0.0869   0.6484   0.2486
  -1.750   0.2746   0.01222   0.00404  -0.0862   0.6352   0.2850
  -1.500   0.2992   0.01211   0.00398  -0.0854   0.6217   0.3204
  -1.250   0.3233   0.01201   0.00394  -0.0845   0.6076   0.3590
  -1.000   0.3467   0.01189   0.00392  -0.0835   0.5928   0.4099
  -0.750   0.3695   0.01176   0.00390  -0.0824   0.5773   0.4643
  -0.500   0.3922   0.01168   0.00388  -0.0812   0.5613   0.5111
  -0.250   0.4145   0.01160   0.00387  -0.0800   0.5451   0.5583
   0.000   0.4354   0.01146   0.00390  -0.0783   0.5297   0.6286
   0.250   0.4560   0.01128   0.00397  -0.0764   0.5149   0.7314
   0.500   0.4936   0.01121   0.00411  -0.0779   0.4988   0.8618
   0.750   0.5594   0.01140   0.00420  -0.0856   0.4800   0.9576
   1.000   0.6056   0.01162   0.00425  -0.0895   0.4645   0.9919
   1.250   0.6332   0.01183   0.00433  -0.0895   0.4513   1.0000
   1.500   0.6541   0.01202   0.00440  -0.0881   0.4389   1.0000
   1.750   0.6746   0.01224   0.00449  -0.0867   0.4264   1.0000
   2.000   0.6950   0.01247   0.00458  -0.0852   0.4153   1.0000
   2.250   0.7166   0.01267   0.00470  -0.0839   0.4053   1.0000
   2.500   0.7379   0.01290   0.00482  -0.0826   0.3975   1.0000
   2.750   0.7600   0.01310   0.00496  -0.0815   0.3902   1.0000
   3.000   0.7814   0.01334   0.00511  -0.0803   0.3837   1.0000
   3.250   0.8040   0.01354   0.00526  -0.0792   0.3770   1.0000
   3.500   0.8258   0.01378   0.00543  -0.0780   0.3701   1.0000
   3.750   0.8477   0.01403   0.00561  -0.0769   0.3642   1.0000
   4.000   0.8703   0.01424   0.00580  -0.0759   0.3583   1.0000
   4.250   0.8926   0.01449   0.00600  -0.0749   0.3535   1.0000
   4.500   0.9146   0.01476   0.00622  -0.0738   0.3490   1.0000
   4.750   0.9374   0.01497   0.00644  -0.0729   0.3436   1.0000
   5.000   0.9594   0.01522   0.00667  -0.0718   0.3382   1.0000
   5.250   0.9806   0.01553   0.00691  -0.0707   0.3336   1.0000
   5.500   1.0033   0.01575   0.00716  -0.0698   0.3289   1.0000
   5.750   1.0253   0.01600   0.00742  -0.0688   0.3240   1.0000
   6.000   1.0465   0.01629   0.00769  -0.0676   0.3195   1.0000
   6.250   1.0676   0.01659   0.00797  -0.0665   0.3154   1.0000
   6.500   1.0896   0.01684   0.00828  -0.0655   0.3109   1.0000
   6.750   1.1103   0.01712   0.00858  -0.0643   0.3060   1.0000
   7.000   1.1299   0.01744   0.00889  -0.0630   0.3016   1.0000
   7.250   1.1502   0.01773   0.00922  -0.0617   0.2970   1.0000
   7.500   1.1693   0.01801   0.00955  -0.0603   0.2917   1.0000
   7.750   1.1862   0.01834   0.00988  -0.0585   0.2862   1.0000
   8.000   1.2039   0.01866   0.01025  -0.0568   0.2808   1.0000
   8.250   1.2209   0.01898   0.01063  -0.0551   0.2742   1.0000
   8.500   1.2360   0.01938   0.01102  -0.0531   0.2680   1.0000
   8.750   1.2535   0.01973   0.01145  -0.0516   0.2611   1.0000
   9.000   1.2678   0.02019   0.01191  -0.0496   0.2544   1.0000
   9.250   1.2841   0.02061   0.01241  -0.0480   0.2466   1.0000
   9.500   1.2971   0.02116   0.01295  -0.0460   0.2394   1.0000
   9.750   1.3121   0.02167   0.01353  -0.0444   0.2313   1.0000
  10.000   1.3242   0.02232   0.01418  -0.0424   0.2240   1.0000
  10.250   1.3369   0.02298   0.01489  -0.0406   0.2164   1.0000
  10.500   1.3474   0.02376   0.01567  -0.0386   0.2099   1.0000
  10.750   1.3575   0.02461   0.01653  -0.0368   0.2020   1.0000
  11.000   1.3659   0.02558   0.01750  -0.0348   0.1957   1.0000
  11.250   1.3749   0.02658   0.01852  -0.0331   0.1894   1.0000
  11.500   1.3803   0.02782   0.01975  -0.0311   0.1841   1.0000
  11.750   1.3909   0.02884   0.02085  -0.0297   0.1796   1.0000
  12.000   1.3989   0.03005   0.02211  -0.0283   0.1755   1.0000
  12.250   1.4047   0.03144   0.02352  -0.0268   0.1718   1.0000
  12.500   1.4115   0.03283   0.02496  -0.0255   0.1686   1.0000
  12.750   1.4205   0.03412   0.02637  -0.0244   0.1647   1.0000
  13.000   1.4270   0.03563   0.02795  -0.0233   0.1612   1.0000
  13.250   1.4305   0.03741   0.02978  -0.0223   0.1577   1.0000
  13.500   1.4342   0.03924   0.03165  -0.0213   0.1549   1.0000
  13.750   1.4420   0.04082   0.03339  -0.0207   0.1508   1.0000
  14.000   1.4465   0.04271   0.03539  -0.0200   0.1470   1.0000
  14.250   1.4465   0.04507   0.03781  -0.0194   0.1429   1.0000
  14.500   1.4487   0.04733   0.04015  -0.0190   0.1392   1.0000
  14.750   1.4531   0.04945   0.04243  -0.0188   0.1351   1.0000
  15.000   1.4521   0.05220   0.04526  -0.0187   0.1302   1.0000
  15.250   1.4504   0.05513   0.04829  -0.0188   0.1255   1.0000
  15.500   1.4493   0.05815   0.05143  -0.0190   0.1186   1.0000
  15.750   1.4442   0.06171   0.05508  -0.0195   0.1118   1.0000
  16.000   1.4354   0.06588   0.05931  -0.0203   0.1022   1.0000
  16.250   1.4201   0.07106   0.06451  -0.0215   0.0885   1.0000
  16.500   1.3960   0.07763   0.07105  -0.0234   0.0731   1.0000
  16.750   1.3709   0.08456   0.07795  -0.0255   0.0606   1.0000
  17.000   1.3452   0.09180   0.08521  -0.0279   0.0497   1.0000
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