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GOE 373 AIRFOIL (goe373-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 373 AIRFOIL (goe373-il)
Reynolds number: 200,000
Max Cl/Cd: 80.13 at α=6.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe373-il-200000.txt
Download as CSV file: xf-goe373-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 373 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
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.2431   0.10419   0.10082  -0.0261   1.0000   0.0236
  -9.250  -0.2450   0.10221   0.09887  -0.0274   1.0000   0.0236
  -7.750  -0.2990   0.09497   0.09161  -0.0237   1.0000   0.0240
  -7.500  -0.2946   0.09190   0.08858  -0.0226   1.0000   0.0243
  -7.250  -0.2949   0.08963   0.08636  -0.0215   1.0000   0.0246
  -7.000  -0.2947   0.08734   0.08413  -0.0208   1.0000   0.0250
  -6.750  -0.2939   0.08511   0.08195  -0.0206   1.0000   0.0253
  -6.500  -0.2941   0.08302   0.07992  -0.0203   1.0000   0.0259
  -6.250  -0.2960   0.08112   0.07808  -0.0197   1.0000   0.0264
  -6.000  -0.3009   0.07954   0.07656  -0.0186   1.0000   0.0269
  -5.750  -0.2935   0.07715   0.07420  -0.0208   0.9983   0.0276
  -5.500  -0.2205   0.07207   0.06889  -0.0435   0.9900   0.0289
  -5.250  -0.1957   0.06659   0.06342  -0.0470   0.9851   0.0293
  -5.000  -0.1720   0.06255   0.05938  -0.0493   0.9797   0.0300
  -4.750  -0.1372   0.05865   0.05542  -0.0551   0.9732   0.0313
  -4.500  -0.0928   0.05461   0.05127  -0.0632   0.9678   0.0336
  -4.250  -0.0255   0.05061   0.04684  -0.0761   0.9598   0.0356
  -4.000   0.0007   0.04603   0.04235  -0.0790   0.9560   0.0366
  -3.750   0.0333   0.04296   0.03922  -0.0824   0.9470   0.0382
  -3.500   0.0808   0.03962   0.03569  -0.0886   0.9417   0.0414
  -3.250   0.1237   0.03625   0.03205  -0.0931   0.9304   0.0452
  -3.000   0.1556   0.03377   0.02951  -0.0955   0.9191   0.0477
  -2.500   0.2285   0.02909   0.02435  -0.1002   0.8965   0.0567
  -2.250   0.2570   0.02748   0.02262  -0.1010   0.8821   0.0616
  -2.000   0.2883   0.02574   0.02057  -0.1017   0.8673   0.0687
  -1.750   0.3145   0.02439   0.01910  -0.1017   0.8519   0.0749
  -1.500   0.3417   0.02298   0.01746  -0.1018   0.8365   0.0843
  -1.250   0.3682   0.02186   0.01612  -0.1016   0.8202   0.0968
  -1.000   0.3938   0.02084   0.01490  -0.1012   0.8033   0.1109
  -0.750   0.4184   0.01982   0.01376  -0.1008   0.7861   0.1276
  -0.500   0.4428   0.01898   0.01279  -0.1004   0.7689   0.1563
  -0.250   0.2464   0.03800   0.03440  -0.0437   0.7539   0.4523
   0.750   0.5718   0.01485   0.00796  -0.0976   0.6860   0.2602
   1.000   0.6103   0.01471   0.00696  -0.0955   0.6709   0.1045
   1.250   0.6377   0.01409   0.00614  -0.0944   0.6553   0.0854
   1.500   0.6643   0.01380   0.00569  -0.0935   0.6389   0.0762
   1.750   0.6902   0.01340   0.00519  -0.0927   0.6222   0.0702
   2.000   0.7162   0.01338   0.00505  -0.0919   0.6051   0.0665
   2.250   0.7412   0.01307   0.00471  -0.0911   0.5881   0.0650
   2.500   0.7662   0.01291   0.00451  -0.0903   0.5713   0.0639
   2.750   0.7914   0.01286   0.00439  -0.0896   0.5556   0.0635
   3.000   0.8169   0.01292   0.00435  -0.0890   0.5408   0.0639
   3.250   0.8424   0.01303   0.00438  -0.0884   0.5263   0.0668
   3.500   0.8678   0.01316   0.00445  -0.0878   0.5120   0.0746
   3.750   0.8934   0.01330   0.00457  -0.0872   0.4982   0.0907
   4.000   0.9244   0.01205   0.00482  -0.0881   0.4840   1.0000
   4.250   0.9496   0.01230   0.00497  -0.0875   0.4709   1.0000
   4.500   0.9749   0.01258   0.00517  -0.0869   0.4596   1.0000
   4.750   1.0002   0.01282   0.00539  -0.0863   0.4480   1.0000
   5.000   1.0254   0.01307   0.00563  -0.0858   0.4370   1.0000
   5.250   1.0500   0.01330   0.00583  -0.0851   0.4242   1.0000
   5.500   1.0736   0.01347   0.00598  -0.0843   0.4061   1.0000
   5.750   1.0968   0.01370   0.00613  -0.0834   0.3878   1.0000
   6.000   1.1203   0.01399   0.00638  -0.0827   0.3720   1.0000
   6.250   1.1435   0.01427   0.00665  -0.0819   0.3539   1.0000
   6.500   1.1657   0.01460   0.00694  -0.0809   0.3306   1.0000
   6.750   1.1878   0.01497   0.00726  -0.0800   0.3075   1.0000
   7.000   1.2098   0.01537   0.00760  -0.0791   0.2839   1.0000
   7.250   1.2320   0.01577   0.00797  -0.0782   0.2567   1.0000
   7.500   1.2522   0.01635   0.00841  -0.0771   0.2168   1.0000
   7.750   1.2684   0.01736   0.00908  -0.0756   0.1728   1.0000
   8.000   1.2873   0.01816   0.00978  -0.0744   0.1518   1.0000
   8.250   1.3071   0.01885   0.01045  -0.0732   0.1330   1.0000
   8.500   1.3249   0.01973   0.01120  -0.0719   0.1019   1.0000
   8.750   1.3360   0.02121   0.01237  -0.0697   0.0570   1.0000
   9.000   1.3461   0.02273   0.01370  -0.0674   0.0315   1.0000
   9.250   1.3592   0.02390   0.01486  -0.0654   0.0266   1.0000
   9.500   1.3731   0.02492   0.01604  -0.0634   0.0252   1.0000
   9.750   1.3850   0.02602   0.01730  -0.0612   0.0243   1.0000
  10.000   1.3935   0.02717   0.01860  -0.0586   0.0238   1.0000
  10.250   1.3982   0.02847   0.02008  -0.0555   0.0233   1.0000
  10.500   1.4005   0.02995   0.02171  -0.0525   0.0229   1.0000
  10.750   1.4012   0.03160   0.02351  -0.0497   0.0226   1.0000
  11.000   1.3996   0.03356   0.02560  -0.0471   0.0224   1.0000
  11.250   1.3972   0.03577   0.02794  -0.0449   0.0222   1.0000
  11.500   1.3950   0.03818   0.03047  -0.0432   0.0221   1.0000
  11.750   1.3920   0.04087   0.03327  -0.0419   0.0218   1.0000
  12.000   1.3891   0.04375   0.03624  -0.0408   0.0216   1.0000
  12.250   1.3861   0.04684   0.03941  -0.0397   0.0211   1.0000
  12.500   1.3861   0.04986   0.04253  -0.0385   0.0207   1.0000
  12.750   1.3916   0.05242   0.04518  -0.0374   0.0206   1.0000
  13.000   1.3992   0.05490   0.04777  -0.0363   0.0206   1.0000
  13.250   1.4099   0.05743   0.05041  -0.0351   0.0206   1.0000
  13.500   1.4173   0.06007   0.05323  -0.0344   0.0207   1.0000
  13.750   1.4221   0.06282   0.05614  -0.0340   0.0209   1.0000
  14.000   1.4244   0.06585   0.05937  -0.0337   0.0210   1.0000
  14.250   1.4234   0.06919   0.06293  -0.0339   0.0213   1.0000
  14.500   1.4188   0.07316   0.06717  -0.0345   0.0216   1.0000
  14.750   1.4104   0.07784   0.07216  -0.0355   0.0221   1.0000
  15.000   1.3993   0.08326   0.07790  -0.0370   0.0227   1.0000
  15.250   1.3817   0.08978   0.08474  -0.0395   0.0232   1.0000
  15.500   1.3641   0.09661   0.09185  -0.0426   0.0236   1.0000
  15.750   1.3455   0.10393   0.09941  -0.0463   0.0240   1.0000
  16.000   1.3262   0.11171   0.10742  -0.0506   0.0243   1.0000
  16.250   1.3068   0.11993   0.11585  -0.0556   0.0246   1.0000
  16.500   1.2869   0.12865   0.12476  -0.0612   0.0248   1.0000
  16.750   1.2658   0.13819   0.13447  -0.0676   0.0250   1.0000
  17.000   1.2443   0.14842   0.14486  -0.0746   0.0252   1.0000
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