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GOE 646 AIRFOIL (goe646-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 646 AIRFOIL (goe646-il)
Reynolds number: 100,000
Max Cl/Cd: 43.61 at α=8°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe646-il-100000.txt
Download as CSV file: xf-goe646-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 646 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.3477   0.13563   0.13049  -0.0337   1.0000   0.1778
 -11.000  -0.3269   0.13277   0.12765  -0.0310   1.0000   0.1794
 -10.750  -0.8388   0.05926   0.05351  -0.0665   1.0000   0.1130
 -10.500  -0.6024   0.07934   0.07423  -0.0565   1.0000   0.1239
 -10.250  -0.7055   0.06678   0.06165  -0.0602   1.0000   0.1214
 -10.000  -0.8247   0.05413   0.04841  -0.0634   0.9969   0.1180
  -9.750  -0.8205   0.04876   0.04248  -0.0682   0.9881   0.1213
  -9.500  -0.8043   0.04452   0.03763  -0.0723   0.9803   0.1252
  -9.250  -0.7720   0.04393   0.03719  -0.0737   0.9722   0.1292
  -9.000  -0.7467   0.04145   0.03425  -0.0765   0.9645   0.1345
  -8.750  -0.7174   0.04017   0.03296  -0.0781   0.9561   0.1395
  -8.500  -0.6876   0.03910   0.03174  -0.0797   0.9481   0.1455
  -8.250  -0.6575   0.03771   0.03020  -0.0815   0.9402   0.1518
  -8.000  -0.6281   0.03705   0.02948  -0.0826   0.9319   0.1585
  -7.750  -0.5952   0.03596   0.02827  -0.0844   0.9240   0.1659
  -7.500  -0.5655   0.03543   0.02766  -0.0853   0.9154   0.1737
  -7.250  -0.5328   0.03474   0.02697  -0.0867   0.9074   0.1816
  -7.000  -0.4985   0.03403   0.02598  -0.0885   0.9008   0.1918
  -6.750  -0.4732   0.03386   0.02605  -0.0882   0.8909   0.1988
  -6.500  -0.4315   0.03310   0.02513  -0.0910   0.8860   0.2106
  -6.250  -0.4132   0.03312   0.02524  -0.0894   0.8743   0.2182
  -6.000  -0.3736   0.03262   0.02471  -0.0915   0.8687   0.2304
  -5.750  -0.3521   0.03230   0.02415  -0.0908   0.8591   0.2422
  -5.500  -0.3197   0.03235   0.02443  -0.0913   0.8519   0.2524
  -5.250  -0.2774   0.03200   0.02406  -0.0936   0.8480   0.2663
  -5.000  -0.2664   0.03206   0.02392  -0.0912   0.8362   0.2773
  -4.750  -0.2283   0.03198   0.02400  -0.0925   0.8309   0.2886
  -4.500  -0.1832   0.03153   0.02350  -0.0951   0.8280   0.3029
  -4.250  -0.1794   0.03195   0.02389  -0.0914   0.8150   0.3110
  -4.000  -0.1413   0.03162   0.02355  -0.0929   0.8109   0.3232
  -3.750  -0.0973   0.03112   0.02290  -0.0954   0.8085   0.3380
  -3.500  -0.1002   0.03183   0.02370  -0.0908   0.7954   0.3431
  -3.250  -0.0614   0.03143   0.02312  -0.0923   0.7916   0.3576
  -3.000  -0.0157   0.03096   0.02278  -0.0946   0.7894   0.3708
  -2.750  -0.0245   0.03188   0.02354  -0.0896   0.7763   0.3780
  -2.500   0.0115   0.03158   0.02337  -0.0905   0.7727   0.3893
  -2.250   0.0548   0.03091   0.02261  -0.0927   0.7706   0.4026
  -2.000   0.0449   0.03208   0.02382  -0.0875   0.7581   0.4075
  -1.750   0.0798   0.03171   0.02327  -0.0885   0.7541   0.4201
  -1.500   0.1215   0.03107   0.02275  -0.0902   0.7519   0.4310
  -1.250   0.1118   0.03248   0.02411  -0.0854   0.7407   0.4370
  -1.000   0.1413   0.03225   0.02388  -0.0855   0.7358   0.4469
  -0.750   0.1837   0.03160   0.02317  -0.0873   0.7333   0.4601
  -0.500   0.2332   0.03063   0.02226  -0.0899   0.7317   0.4726
  -0.250   0.2124   0.03247   0.02409  -0.0835   0.7174   0.4774
   0.000   0.2639   0.03116   0.02280  -0.0860   0.7149   0.4915
   0.250   0.3244   0.02968   0.02128  -0.0899   0.7132   0.5082
   0.500   0.3876   0.02841   0.02001  -0.0947   0.7116   0.5258
   0.750   0.3492   0.03057   0.02222  -0.0852   0.6967   0.5288
   1.000   0.4033   0.02945   0.02114  -0.0884   0.6948   0.5463
   1.250   0.4631   0.02834   0.02009  -0.0926   0.6931   0.5652
   1.500   0.4241   0.03067   0.02245  -0.0832   0.6785   0.5702
   1.750   0.4797   0.02946   0.02130  -0.0864   0.6764   0.5917
   2.000   0.5430   0.02818   0.02011  -0.0910   0.6745   0.6162
   2.250   0.5036   0.03049   0.02251  -0.0814   0.6604   0.6236
   2.500   0.5588   0.02922   0.02130  -0.0845   0.6579   0.6547
   2.750   0.6230   0.02780   0.01997  -0.0891   0.6557   0.6941
   3.000   0.5915   0.02967   0.02197  -0.0804   0.6424   0.7134
   3.250   0.6518   0.02807   0.02059  -0.0841   0.6393   0.7704
   3.500   0.7337   0.02621   0.01908  -0.0914   0.6365   0.8822
   3.750   0.7789   0.02667   0.01955  -0.0959   0.6262   1.0000
   4.000   0.8268   0.02616   0.01886  -0.0989   0.6195   1.0000
   4.250   0.8964   0.02520   0.01767  -0.1052   0.6148   1.0000
   4.500   0.8801   0.02646   0.01898  -0.0983   0.6023   1.0000
   4.750   0.9445   0.02558   0.01790  -0.1036   0.5962   1.0000
   5.000   0.9386   0.02654   0.01890  -0.0982   0.5842   1.0000
   5.250   0.9982   0.02577   0.01795  -0.1027   0.5768   1.0000
   5.500   0.9963   0.02655   0.01877  -0.0978   0.5646   1.0000
   5.750   1.0582   0.02574   0.01773  -0.1027   0.5563   1.0000
   6.000   1.0516   0.02653   0.01860  -0.0969   0.5436   1.0000
   6.250   1.0953   0.02621   0.01814  -0.0990   0.5344   1.0000
   6.500   1.1019   0.02670   0.01865  -0.0954   0.5228   1.0000
   6.750   1.1304   0.02680   0.01869  -0.0952   0.5131   1.0000
   7.000   1.1475   0.02707   0.01893  -0.0932   0.5025   1.0000
   7.250   1.1667   0.02741   0.01924  -0.0916   0.4926   1.0000
   7.500   1.1899   0.02755   0.01933  -0.0906   0.4827   1.0000
   7.750   1.2017   0.02804   0.01983  -0.0879   0.4729   1.0000
   8.000   1.2272   0.02814   0.01985  -0.0873   0.4635   1.0000
   8.250   1.2343   0.02874   0.02048  -0.0839   0.4544   1.0000
   8.500   1.2563   0.02897   0.02066  -0.0828   0.4455   1.0000
   8.750   1.2681   0.02956   0.02126  -0.0803   0.4371   1.0000
   9.000   1.2824   0.02999   0.02169  -0.0781   0.4283   1.0000
   9.250   1.3027   0.03042   0.02208  -0.0769   0.4201   1.0000
   9.500   1.3087   0.03108   0.02278  -0.0736   0.4114   1.0000
   9.750   1.3341   0.03132   0.02294  -0.0732   0.4028   1.0000
  10.000   1.3358   0.03214   0.02381  -0.0695   0.3941   1.0000
  10.250   1.3640   0.03233   0.02390  -0.0694   0.3854   1.0000
  10.500   1.3620   0.03335   0.02500  -0.0655   0.3771   1.0000
  10.750   1.3930   0.03349   0.02499  -0.0658   0.3681   1.0000
  11.000   1.3867   0.03474   0.02637  -0.0615   0.3602   1.0000
  11.250   1.4252   0.03477   0.02621  -0.0628   0.3513   1.0000
  11.500   1.4108   0.03640   0.02803  -0.0579   0.3444   1.0000
  11.750   1.4561   0.03628   0.02768  -0.0599   0.3354   1.0000
  12.000   1.4379   0.03816   0.02977  -0.0548   0.3292   1.0000
  12.250   1.4508   0.03894   0.03055  -0.0532   0.3214   1.0000
  12.500   1.4675   0.03981   0.03138  -0.0522   0.3140   1.0000
  12.750   1.4557   0.04167   0.03341  -0.0484   0.3077   1.0000
  13.000   1.5085   0.04124   0.03271  -0.0509   0.2992   1.0000
  13.250   1.4773   0.04391   0.03569  -0.0455   0.2946   1.0000
  13.500   1.4718   0.04572   0.03763  -0.0428   0.2884   1.0000
  13.750   1.5130   0.04546   0.03717  -0.0438   0.2807   1.0000
  14.000   1.4799   0.04874   0.04076  -0.0394   0.2762   1.0000
  14.250   1.4768   0.05058   0.04268  -0.0373   0.2699   1.0000
  14.500   1.5044   0.05070   0.04270  -0.0371   0.2627   1.0000
  14.750   1.4682   0.05483   0.04713  -0.0337   0.2579   1.0000
  15.000   1.4829   0.05545   0.04770  -0.0328   0.2506   1.0000
  15.250   1.4772   0.05781   0.05014  -0.0313   0.2444   1.0000
  15.500   1.4434   0.06258   0.05516  -0.0294   0.2389   1.0000
  15.750   1.4820   0.06110   0.05345  -0.0291   0.2299   1.0000
  16.000   1.4304   0.06797   0.06068  -0.0277   0.2248   1.0000
  16.250   1.4751   0.06557   0.05799  -0.0271   0.2148   1.0000
  16.500   1.4158   0.07395   0.06677  -0.0267   0.2097   1.0000
  16.750   1.4580   0.07155   0.06406  -0.0257   0.1994   1.0000
  17.000   1.3975   0.08093   0.07384  -0.0265   0.1942   1.0000
  17.250   1.4466   0.07764   0.07020  -0.0251   0.1846   1.0000
  17.500   1.3839   0.08800   0.08098  -0.0268   0.1802   1.0000
  17.750   1.4033   0.08825   0.08112  -0.0262   0.1733   1.0000
  18.000   1.3926   0.09264   0.08559  -0.0268   0.1684   1.0000
  18.750   1.3580   0.10667   0.09990  -0.0300   0.1558   1.0000
  19.000   0.8743   0.21559   0.20930  -0.0892   0.1924   1.0000
  19.250   0.8859   0.21804   0.21177  -0.0900   0.1890   1.0000
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