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GOE 375 AIRFOIL (goe375-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 375 AIRFOIL (goe375-il)
Reynolds number: 100,000
Max Cl/Cd: 52.05 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe375-il-100000-n5.txt
Download as CSV file: xf-goe375-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 375 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3375   0.10869   0.10389  -0.0184   1.0000   0.0216
  -8.250  -0.3362   0.10642   0.10170  -0.0197   1.0000   0.0216
  -8.000  -0.3333   0.10394   0.09929  -0.0210   1.0000   0.0216
  -7.750  -0.3217   0.09803   0.09342  -0.0185   1.0000   0.0219
  -7.500  -0.3158   0.09431   0.08974  -0.0177   1.0000   0.0222
  -7.250  -0.3126   0.09144   0.08693  -0.0177   1.0000   0.0224
  -7.000  -0.3082   0.08854   0.08409  -0.0180   1.0000   0.0228
  -6.750  -0.3038   0.08575   0.08137  -0.0187   1.0000   0.0234
  -6.500  -0.2986   0.08308   0.07876  -0.0196   1.0000   0.0238
  -6.250  -0.2927   0.08041   0.07615  -0.0207   1.0000   0.0245
  -6.000  -0.2861   0.07776   0.07355  -0.0219   1.0000   0.0252
  -5.750  -0.2790   0.07516   0.07099  -0.0231   1.0000   0.0258
  -5.500  -0.2714   0.07264   0.06850  -0.0243   1.0000   0.0263
  -5.250  -0.2636   0.07028   0.06616  -0.0252   1.0000   0.0267
  -4.750  -0.1959   0.06368   0.05924  -0.0381   0.9893   0.0276
  -4.500  -0.1522   0.05997   0.05526  -0.0449   0.9805   0.0278
  -4.250  -0.1215   0.05520   0.05043  -0.0488   0.9723   0.0280
  -4.000  -0.0972   0.05039   0.04565  -0.0515   0.9652   0.0289
  -3.750  -0.0670   0.04688   0.04205  -0.0547   0.9557   0.0306
  -3.500  -0.0240   0.04427   0.03910  -0.0588   0.9467   0.0347
  -3.250   0.0214   0.04175   0.03610  -0.0626   0.9389   0.0359
  -3.000   0.0449   0.03743   0.03186  -0.0645   0.9285   0.0378
  -2.750   0.0786   0.03478   0.02900  -0.0665   0.9188   0.0413
  -2.500   0.1176   0.03247   0.02626  -0.0686   0.9092   0.0476
  -2.250   0.1481   0.03024   0.02377  -0.0699   0.8969   0.0608
  -2.000   0.1776   0.02790   0.02130  -0.0712   0.8843   0.0778
  -1.500   0.2367   0.02459   0.01753  -0.0731   0.8526   0.1578
  -1.250   0.2666   0.02250   0.01525  -0.0731   0.8334   0.1671
  -1.000   0.3100   0.02167   0.01351  -0.0710   0.8147   0.0699
  -0.750   0.3401   0.02042   0.01187  -0.0701   0.7949   0.0614
  -0.500   0.3688   0.02019   0.01124  -0.0690   0.7741   0.0589
  -0.250   0.3953   0.01882   0.00975  -0.0682   0.7522   0.0559
   0.000   0.4218   0.01801   0.00877  -0.0673   0.7281   0.0543
   0.250   0.4481   0.01752   0.00808  -0.0663   0.7011   0.0565
   0.500   0.4739   0.01701   0.00738  -0.0653   0.6709   0.0568
   0.750   0.4993   0.01651   0.00674  -0.0643   0.6386   0.0560
   1.000   0.5241   0.01615   0.00621  -0.0632   0.6061   0.0555
   1.250   0.5486   0.01593   0.00580  -0.0622   0.5748   0.0552
   1.500   0.5730   0.01584   0.00549  -0.0612   0.5463   0.0553
   1.750   0.5980   0.01587   0.00528  -0.0604   0.5202   0.0565
   2.000   0.6231   0.01593   0.00511  -0.0597   0.4962   0.0598
   2.250   0.6483   0.01603   0.00502  -0.0591   0.4732   0.0610
   2.500   0.6734   0.01620   0.00499  -0.0584   0.4514   0.0618
   2.750   0.6984   0.01640   0.00502  -0.0578   0.4305   0.0627
   3.000   0.7233   0.01662   0.00511  -0.0571   0.4098   0.0642
   3.250   0.7479   0.01689   0.00521  -0.0565   0.3899   0.0665
   3.500   0.7726   0.01714   0.00538  -0.0559   0.3704   0.0702
   3.750   0.8077   0.01582   0.00570  -0.0578   0.3497   1.0000
   4.000   0.8317   0.01620   0.00594  -0.0571   0.3336   1.0000
   4.250   0.8556   0.01658   0.00619  -0.0564   0.3187   1.0000
   4.500   0.8796   0.01698   0.00649  -0.0557   0.3054   1.0000
   4.750   0.9034   0.01739   0.00683  -0.0551   0.2933   1.0000
   5.000   0.9270   0.01783   0.00718  -0.0544   0.2825   1.0000
   5.250   0.9506   0.01828   0.00757  -0.0537   0.2725   1.0000
   5.500   0.9744   0.01872   0.00801  -0.0531   0.2635   1.0000
   5.750   0.9975   0.01924   0.00848  -0.0524   0.2558   1.0000
   6.000   1.0214   0.01971   0.00902  -0.0518   0.2475   1.0000
   6.250   1.0441   0.02027   0.00952  -0.0511   0.2405   1.0000
   6.500   1.0677   0.02077   0.01016  -0.0505   0.2324   1.0000
   6.750   1.0901   0.02138   0.01071  -0.0497   0.2260   1.0000
   7.000   1.1133   0.02192   0.01141  -0.0491   0.2186   1.0000
   7.250   1.1358   0.02253   0.01205  -0.0484   0.2128   1.0000
   7.500   1.1586   0.02319   0.01286  -0.0477   0.2074   1.0000
   7.750   1.1813   0.02385   0.01365  -0.0470   0.2019   1.0000
   8.000   1.2036   0.02456   0.01442  -0.0463   0.1976   1.0000
   8.250   1.2260   0.02533   0.01535  -0.0457   0.1931   1.0000
   8.500   1.2479   0.02606   0.01632  -0.0449   0.1881   1.0000
   8.750   1.2676   0.02656   0.01688  -0.0439   0.1807   1.0000
   9.000   1.2853   0.02682   0.01734  -0.0427   0.1692   1.0000
   9.250   1.3038   0.02725   0.01800  -0.0416   0.1588   1.0000
   9.500   1.3213   0.02763   0.01854  -0.0404   0.1458   1.0000
   9.750   1.3383   0.02815   0.01918  -0.0392   0.1306   1.0000
  10.000   1.3533   0.02894   0.02004  -0.0379   0.1123   1.0000
  10.500   1.3581   0.03333   0.02390  -0.0332   0.0277   1.0000
  10.750   1.3558   0.03562   0.02628  -0.0303   0.0230   1.0000
  11.000   1.3526   0.03782   0.02865  -0.0274   0.0207   1.0000
  11.250   1.3469   0.04028   0.03133  -0.0249   0.0193   1.0000
  11.500   1.3398   0.04302   0.03432  -0.0231   0.0185   1.0000
  11.750   1.3292   0.04637   0.03792  -0.0221   0.0179   1.0000
  12.000   1.3163   0.05037   0.04216  -0.0220   0.0176   1.0000
  12.250   1.3015   0.05511   0.04714  -0.0231   0.0174   1.0000
  12.500   1.2838   0.06095   0.05322  -0.0254   0.0173   1.0000
  12.750   1.2651   0.06771   0.06019  -0.0288   0.0174   1.0000
  13.000   1.2443   0.07542   0.06812  -0.0330   0.0175   1.0000
  13.250   1.2239   0.08335   0.07623  -0.0371   0.0178   1.0000
  13.500   1.2037   0.09135   0.08441  -0.0410   0.0181   1.0000
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