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GOE 480 AIRFOIL (goe480-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 480 AIRFOIL (goe480-il)
Reynolds number: 1,000,000
Max Cl/Cd: 138.31 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe480-il-1000000.txt
Download as CSV file: xf-goe480-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 480 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.500  -0.3088   0.12588   0.12409  -0.0399   1.0000   0.0260
 -12.250  -0.3010   0.12412   0.12233  -0.0399   1.0000   0.0263
 -12.000  -0.2939   0.12229   0.12052  -0.0400   1.0000   0.0268
 -11.750  -0.3045   0.11678   0.11502  -0.0428   1.0000   0.0293
 -11.250  -0.3063   0.10987   0.10813  -0.0433   1.0000   0.0293
 -11.000  -0.2863   0.10747   0.10574  -0.0456   0.9992   0.0299
 -10.750  -0.2658   0.10491   0.10316  -0.0487   0.9978   0.0303
 -10.500  -0.2477   0.10187   0.10013  -0.0521   0.9946   0.0308
 -10.250  -0.2335   0.09886   0.09711  -0.0549   0.9887   0.0323
  -9.750  -0.2290   0.08562   0.08385  -0.0673   0.9714   0.0341
  -9.500  -0.2000   0.08415   0.08237  -0.0701   0.9629   0.0345
  -9.250  -0.1697   0.08089   0.07907  -0.0763   0.9540   0.0350
  -8.750  -0.1188   0.06377   0.06174  -0.1064   0.9125   0.0389
  -8.500  -0.0973   0.06251   0.06033  -0.1083   0.8810   0.0392
  -8.250  -0.0913   0.06124   0.05892  -0.1077   0.8505   0.0395
  -8.000  -0.0941   0.05953   0.05712  -0.1069   0.8263   0.0397
  -7.750  -0.0892   0.05759   0.05511  -0.1075   0.8102   0.0402
  -7.500  -0.0838   0.05520   0.05266  -0.1089   0.7968   0.0411
  -7.250  -0.1207   0.03859   0.03571  -0.1214   0.7821   0.0432
  -7.000  -0.1634   0.02189   0.01782  -0.1225   0.7723   0.0425
  -6.750  -0.1465   0.01972   0.01527  -0.1215   0.7655   0.0431
  -6.500  -0.1222   0.01930   0.01466  -0.1209   0.7588   0.0436
  -6.250  -0.1062   0.01675   0.01170  -0.1198   0.7525   0.0442
  -6.000  -0.0825   0.01573   0.01059  -0.1193   0.7471   0.0447
  -5.750  -0.0574   0.01514   0.00993  -0.1189   0.7412   0.0450
  -5.500  -0.0321   0.01470   0.00939  -0.1184   0.7356   0.0454
  -5.250  -0.0059   0.01428   0.00893  -0.1180   0.7306   0.0458
  -5.000   0.0202   0.01387   0.00846  -0.1177   0.7251   0.0462
  -4.750   0.0462   0.01353   0.00805  -0.1173   0.7196   0.0467
  -4.500   0.0724   0.01305   0.00748  -0.1169   0.7147   0.0472
  -4.250   0.0987   0.01254   0.00688  -0.1165   0.7095   0.0476
  -4.000   0.1250   0.01210   0.00635  -0.1161   0.7041   0.0480
  -3.750   0.1514   0.01172   0.00587  -0.1156   0.6988   0.0484
  -3.500   0.1785   0.01138   0.00548  -0.1153   0.6937   0.0489
  -3.250   0.2054   0.01109   0.00513  -0.1150   0.6882   0.0492
  -3.000   0.2321   0.01091   0.00486  -0.1146   0.6824   0.0495
  -2.750   0.2598   0.01075   0.00469  -0.1143   0.6772   0.0498
  -2.500   0.2853   0.01001   0.00390  -0.1139   0.6713   0.0507
  -2.250   0.3114   0.00970   0.00355  -0.1134   0.6651   0.0513
  -2.000   0.3386   0.00944   0.00331  -0.1131   0.6593   0.0519
  -1.750   0.3653   0.00925   0.00311  -0.1127   0.6525   0.0524
  -1.500   0.3921   0.00910   0.00293  -0.1124   0.6461   0.0529
  -1.250   0.4191   0.00894   0.00276  -0.1120   0.6390   0.0535
  -1.000   0.4454   0.00883   0.00261  -0.1115   0.6315   0.0542
  -0.750   0.4726   0.00869   0.00248  -0.1112   0.6238   0.0549
  -0.500   0.4989   0.00862   0.00236  -0.1108   0.6154   0.0556
  -0.250   0.5260   0.00853   0.00227  -0.1105   0.6071   0.0563
   0.000   0.5524   0.00853   0.00223  -0.1100   0.5978   0.0569
   0.250   0.5788   0.00837   0.00205  -0.1096   0.5884   0.0578
   0.500   0.6046   0.00828   0.00192  -0.1090   0.5786   0.0591
   0.750   0.6308   0.00825   0.00186  -0.1085   0.5680   0.0604
   1.000   0.6572   0.00823   0.00183  -0.1081   0.5581   0.0617
   1.250   0.6830   0.00826   0.00181  -0.1075   0.5479   0.0631
   1.500   0.7096   0.00826   0.00180  -0.1072   0.5387   0.0645
   1.750   0.7356   0.00830   0.00181  -0.1067   0.5297   0.0661
   2.000   0.7618   0.00830   0.00180  -0.1062   0.5207   0.0705
   2.250   0.7877   0.00834   0.00183  -0.1057   0.5119   0.0748
   2.500   0.8129   0.00821   0.00191  -0.1051   0.5035   0.1594
   2.750   0.8376   0.00812   0.00200  -0.1045   0.4954   0.2433
   3.000   0.8554   0.00737   0.00221  -0.1028   0.4873   0.6517
   3.250   0.9305   0.00692   0.00244  -0.1133   0.4757   1.0000
   3.500   0.9545   0.00706   0.00253  -0.1124   0.4673   1.0000
   3.750   0.9791   0.00718   0.00261  -0.1117   0.4594   1.0000
   4.000   1.0028   0.00734   0.00271  -0.1107   0.4503   1.0000
   4.250   1.0273   0.00746   0.00282  -0.1100   0.4420   1.0000
   4.750   1.0747   0.00777   0.00305  -0.1082   0.4228   1.0000
   5.000   1.0977   0.00796   0.00318  -0.1072   0.4122   1.0000
   5.250   1.1210   0.00813   0.00332  -0.1062   0.4025   1.0000
   5.500   1.1444   0.00830   0.00346  -0.1053   0.3925   1.0000
   5.750   1.1666   0.00853   0.00362  -0.1042   0.3809   1.0000
   6.000   1.1894   0.00872   0.00379  -0.1031   0.3704   1.0000
   6.250   1.2121   0.00891   0.00395  -0.1021   0.3611   1.0000
   6.500   1.2335   0.00917   0.00415  -0.1009   0.3489   1.0000
   6.750   1.2541   0.00945   0.00437  -0.0995   0.3339   1.0000
   7.000   1.2742   0.00976   0.00460  -0.0981   0.3181   1.0000
   7.250   1.2948   0.01003   0.00482  -0.0968   0.3051   1.0000
   7.500   1.3153   0.01030   0.00506  -0.0954   0.2935   1.0000
   7.750   1.3343   0.01062   0.00533  -0.0938   0.2801   1.0000
   8.000   1.3523   0.01097   0.00561  -0.0920   0.2659   1.0000
   8.250   1.3690   0.01133   0.00592  -0.0900   0.2531   1.0000
   8.500   1.3831   0.01172   0.00624  -0.0875   0.2394   1.0000
   8.750   1.3973   0.01211   0.00658  -0.0851   0.2263   1.0000
   9.000   1.4120   0.01251   0.00693  -0.0828   0.2138   1.0000
   9.250   1.4259   0.01296   0.00733  -0.0804   0.2007   1.0000
   9.500   1.4384   0.01349   0.00779  -0.0779   0.1853   1.0000
   9.750   1.4483   0.01417   0.00836  -0.0751   0.1668   1.0000
  10.000   1.4543   0.01506   0.00910  -0.0719   0.1407   1.0000
  10.250   1.4533   0.01635   0.01018  -0.0679   0.1066   1.0000
  10.500   1.4509   0.01783   0.01148  -0.0640   0.0791   1.0000
  10.750   1.4583   0.01887   0.01247  -0.0615   0.0682   1.0000
  11.000   1.4675   0.01985   0.01343  -0.0595   0.0617   1.0000
  11.250   1.4790   0.02074   0.01433  -0.0578   0.0572   1.0000
  11.500   1.4886   0.02180   0.01539  -0.0560   0.0530   1.0000
  11.750   1.5003   0.02276   0.01638  -0.0546   0.0496   1.0000
  12.000   1.5097   0.02392   0.01754  -0.0531   0.0461   1.0000
  12.250   1.5203   0.02504   0.01869  -0.0517   0.0431   1.0000
  12.500   1.5298   0.02627   0.01994  -0.0504   0.0404   1.0000
  12.750   1.5377   0.02767   0.02135  -0.0491   0.0377   1.0000
  13.000   1.5472   0.02898   0.02271  -0.0480   0.0356   1.0000
  13.250   1.5533   0.03059   0.02433  -0.0467   0.0335   1.0000
  13.500   1.5608   0.03212   0.02592  -0.0456   0.0320   1.0000
  13.750   1.5680   0.03372   0.02754  -0.0446   0.0303   1.0000
  14.000   1.5725   0.03559   0.02946  -0.0436   0.0291   1.0000
  14.250   1.5752   0.03766   0.03157  -0.0425   0.0278   1.0000
  14.500   1.5810   0.03950   0.03348  -0.0417   0.0269   1.0000
  14.750   1.5851   0.04155   0.03559  -0.0410   0.0261   1.0000
  15.000   1.5873   0.04382   0.03791  -0.0402   0.0252   1.0000
  15.250   1.5863   0.04648   0.04062  -0.0395   0.0244   1.0000
  15.500   1.5849   0.04928   0.04349  -0.0389   0.0237   1.0000
  15.750   1.5881   0.05162   0.04591  -0.0385   0.0231   1.0000
  16.000   1.5906   0.05406   0.04842  -0.0382   0.0224   1.0000
  16.250   1.5892   0.05701   0.05144  -0.0379   0.0220   1.0000
  16.500   1.5875   0.06006   0.05456  -0.0378   0.0214   1.0000
  16.750   1.5827   0.06355   0.05811  -0.0378   0.0209   1.0000
  17.000   1.5751   0.06741   0.06204  -0.0378   0.0204   1.0000
  17.250   1.5668   0.07144   0.06617  -0.0380   0.0201   1.0000
  17.500   1.5653   0.07468   0.06949  -0.0383   0.0198   1.0000
  17.750   1.5616   0.07822   0.07312  -0.0386   0.0194   1.0000
  18.000   1.5572   0.08188   0.07687  -0.0390   0.0191   1.0000
  18.250   1.5518   0.08571   0.08078  -0.0395   0.0188   1.0000
  18.500   1.5462   0.08962   0.08477  -0.0401   0.0185   1.0000
  18.750   1.5398   0.09374   0.08896  -0.0409   0.0181   1.0000
  19.000   1.5305   0.09828   0.09358  -0.0419   0.0179   1.0000
  19.250   1.5213   0.10290   0.09829  -0.0431   0.0176   1.0000
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