Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

GOE 570 AIRFOIL (goe570-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 570 AIRFOIL (goe570-il)
Reynolds number: 500,000
Max Cl/Cd: 23.73 at α=7.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe570-il-500000.txt
Download as CSV file: xf-goe570-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 570 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -18.250   0.1055   0.05859   0.05320  -0.2390   0.7481   0.0651
 -18.000   0.0761   0.05385   0.04824  -0.2412   0.7444   0.0650
 -17.750   0.0563   0.05020   0.04441  -0.2425   0.7403   0.0648
 -17.500   0.0432   0.04751   0.04162  -0.2428   0.7367   0.0649
 -17.250   0.0346   0.04521   0.03921  -0.2429   0.7326   0.0649
 -17.000   0.0309   0.04324   0.03712  -0.2430   0.7288   0.0649
 -16.750   0.0310   0.04153   0.03527  -0.2432   0.7249   0.0650
 -16.500   0.0350   0.03990   0.03351  -0.2439   0.7208   0.0652
 -16.250   0.0346   0.03854   0.03211  -0.2430   0.7178   0.0652
 -16.000   0.0361   0.03734   0.03086  -0.2420   0.7138   0.0653
 -15.750   0.0383   0.03616   0.02960  -0.2411   0.7098   0.0655
 -15.500   0.0458   0.03511   0.02846  -0.2406   0.7064   0.0656
 -15.250   0.0550   0.03408   0.02730  -0.2407   0.7020   0.0658
 -15.000   0.0610   0.03319   0.02637  -0.2396   0.6986   0.0659
 -14.750   0.0663   0.03237   0.02552  -0.2381   0.6953   0.0660
 -14.500   0.0706   0.03158   0.02469  -0.2364   0.6914   0.0661
 -14.250   0.0768   0.03081   0.02385  -0.2350   0.6875   0.0663
 -14.000   0.0845   0.03006   0.02300  -0.2339   0.6836   0.0666
 -13.750   0.0956   0.02941   0.02227  -0.2332   0.6796   0.0668
 -13.500   0.0982   0.02877   0.02163  -0.2306   0.6763   0.0669
 -13.250   0.0998   0.02815   0.02097  -0.2281   0.6725   0.0671
 -13.000   0.1048   0.02758   0.02036  -0.2258   0.6685   0.0672
 -12.750   0.1148   0.02699   0.01971  -0.2241   0.6645   0.0675
 -12.500   0.1299   0.02642   0.01910  -0.2232   0.6601   0.0682
 -12.250   0.1280   0.02589   0.01860  -0.2195   0.6564   0.0683
 -12.000   0.1284   0.02536   0.01807  -0.2162   0.6523   0.0685
 -11.750   0.1293   0.02487   0.01755  -0.2130   0.6479   0.0685
 -11.500   0.1301   0.02438   0.01702  -0.2098   0.6438   0.0692
 -11.250   0.1325   0.02394   0.01653  -0.2068   0.6395   0.0693
 -11.000   0.1226   0.02351   0.01612  -0.2015   0.6354   0.0695
 -10.750   0.1163   0.02311   0.01570  -0.1967   0.6309   0.0697
 -10.500   0.1118   0.02274   0.01528  -0.1922   0.6265   0.0700
 -10.250   0.1111   0.02242   0.01488  -0.1883   0.6216   0.0702
 -10.000   0.1025   0.02211   0.01457  -0.1828   0.6174   0.0706
  -9.750   0.0931   0.02182   0.01428  -0.1772   0.6129   0.0708
  -9.500   0.0858   0.02158   0.01399  -0.1717   0.6084   0.0712
  -9.250   0.0812   0.02137   0.01370  -0.1668   0.6038   0.0713
  -9.000   0.0753   0.02116   0.01347  -0.1615   0.5997   0.0718
  -8.750   0.0659   0.02099   0.01329  -0.1554   0.5954   0.0722
  -8.500   0.0568   0.02086   0.01311  -0.1494   0.5904   0.0725
  -8.250   0.0511   0.02073   0.01291  -0.1439   0.5861   0.0728
  -8.000   0.0452   0.02063   0.01276  -0.1384   0.5818   0.0731
  -7.750   0.0364   0.02058   0.01270  -0.1322   0.5775   0.0735
  -7.500   0.0296   0.02052   0.01259  -0.1265   0.5732   0.0738
  -7.250   0.0243   0.02050   0.01250  -0.1209   0.5691   0.0741
  -7.000   0.0186   0.02032   0.01226  -0.1152   0.5648   0.0748
  -6.750   0.0095   0.02028   0.01223  -0.1090   0.5615   0.0753
  -6.500   0.0036   0.02024   0.01220  -0.1033   0.5577   0.0759
  -6.250   0.0003   0.02025   0.01218  -0.0981   0.5537   0.0765
  -6.000  -0.0005   0.02027   0.01214  -0.0933   0.5497   0.0774
  -5.750   0.0077   0.02025   0.01204  -0.0900   0.5456   0.0782
  -5.500   0.0023   0.02035   0.01216  -0.0844   0.5424   0.0785
  -5.250   0.0021   0.02044   0.01224  -0.0798   0.5389   0.0798
  -5.000   0.0049   0.02051   0.01227  -0.0756   0.5353   0.0807
  -4.750   0.0094   0.02057   0.01227  -0.0718   0.5319   0.0817
  -4.500   0.0189   0.02050   0.01215  -0.0688   0.5283   0.0829
  -4.250   0.0217   0.02056   0.01223  -0.0647   0.5252   0.0853
  -4.000   0.0245   0.02071   0.01240  -0.0607   0.5219   0.0871
  -3.750   0.0301   0.02087   0.01253  -0.0573   0.5188   0.0891
  -3.500   0.0366   0.02091   0.01258  -0.0540   0.5153   0.0927
  -3.250   0.0498   0.02094   0.01256  -0.0518   0.5120   0.0970
  -3.000   0.0722   0.02076   0.01237  -0.0512   0.5086   0.1052
  -2.750   0.0785   0.02087   0.01257  -0.0482   0.5062   0.1147
  -2.500   0.0877   0.02087   0.01278  -0.0458   0.5033   0.1422
  -2.250   0.1007   0.02103   0.01312  -0.0440   0.5003   0.1845
  -2.000   0.1157   0.02128   0.01337  -0.0424   0.4973   0.1963
  -1.750   0.1334   0.02143   0.01349  -0.0413   0.4941   0.2046
  -1.500   0.1596   0.02145   0.01346  -0.0415   0.4909   0.2128
  -1.250   0.1700   0.02189   0.01388  -0.0393   0.4884   0.2163
  -1.000   0.1805   0.02222   0.01428  -0.0373   0.4857   0.2224
  -0.750   0.1947   0.02253   0.01462  -0.0359   0.4829   0.2276
  -0.500   0.2094   0.02288   0.01495  -0.0345   0.4801   0.2330
  -0.250   0.2269   0.02315   0.01518  -0.0336   0.4774   0.2369
   0.000   0.2497   0.02323   0.01525  -0.0335   0.4744   0.2452
   0.250   0.2739   0.02333   0.01534  -0.0336   0.4716   0.2511
   0.500   0.2816   0.02395   0.01601  -0.0314   0.4691   0.2563
   0.750   0.2950   0.02438   0.01652  -0.0302   0.4666   0.2659
   1.000   0.3100   0.02477   0.01700  -0.0293   0.4639   0.2831
   1.250   0.3281   0.02492   0.01746  -0.0290   0.4613   0.3547
   1.500   0.3477   0.02510   0.01779  -0.0286   0.4589   0.4052
   1.750   0.3709   0.02515   0.01794  -0.0286   0.4564   0.4451
   2.000   0.3929   0.02532   0.01818  -0.0285   0.4536   0.4731
   2.250   0.3995   0.02610   0.01908  -0.0265   0.4515   0.4930
   2.500   0.4092   0.02680   0.01988  -0.0249   0.4488   0.5141
   2.750   0.4231   0.02737   0.02049  -0.0238   0.4462   0.5312
   3.500   0.4748   0.02831   0.02173  -0.0218   0.4391   0.6222
   3.750   0.4985   0.02797   0.02164  -0.0214   0.4367   0.6909
   4.000   0.7178   0.03195   0.02652  -0.0637   0.4335   0.9093
   4.250   0.7017   0.03288   0.02746  -0.0570   0.4311   0.9431
   4.500   0.7124   0.03404   0.02861  -0.0556   0.4285   0.9577
   4.750   0.7421   0.03526   0.02979  -0.0580   0.4261   0.9653
   5.000   0.7676   0.03635   0.03082  -0.0592   0.4239   0.9732
   5.250   0.8268   0.03696   0.03133  -0.0668   0.4213   0.9772
   5.500   0.8722   0.03759   0.03191  -0.0718   0.4191   0.9814
   5.750   0.8932   0.03937   0.03374  -0.0737   0.4171   0.9859
   6.000   0.9167   0.04094   0.03532  -0.0757   0.4147   0.9899
   6.250   0.9551   0.04222   0.03659  -0.0807   0.4121   0.9943
   6.500   0.9930   0.04336   0.03771  -0.0853   0.4099   0.9985
   6.750   1.0183   0.04425   0.03856  -0.0872   0.4077   1.0000
   7.000   1.0343   0.04469   0.03894  -0.0866   0.4056   1.0000
   7.250   1.0583   0.04460   0.03876  -0.0869   0.4032   1.0000
   7.500   1.0600   0.04606   0.04026  -0.0850   0.4013   1.0000
   7.750   1.0576   0.04785   0.04211  -0.0828   0.3991   1.0000
   8.000   1.0615   0.04922   0.04351  -0.0813   0.3970   1.0000
   8.250   1.0686   0.05039   0.04469  -0.0801   0.3948   1.0000
   8.500   1.0768   0.05150   0.04579  -0.0790   0.3928   1.0000
   8.750   1.0878   0.05240   0.04667  -0.0782   0.3908   1.0000
   9.000   1.1052   0.05283   0.04705  -0.0780   0.3890   1.0000
   9.250   1.1291   0.05277   0.04691  -0.0784   0.3872   1.0000
   9.500   1.1356   0.05404   0.04820  -0.0773   0.3853   1.0000
   9.750   1.1253   0.05664   0.05090  -0.0748   0.3831   1.0000
  10.000   1.1216   0.05878   0.05309  -0.0729   0.3805   1.0000
  10.250   1.1260   0.06030   0.05463  -0.0718   0.3780   1.0000
  10.500   1.1335   0.06160   0.05593  -0.0710   0.3759   1.0000
  10.750   1.1450   0.06256   0.05687  -0.0705   0.3742   1.0000
  11.000   1.1637   0.06292   0.05718  -0.0706   0.3726   1.0000
  11.250   1.1885   0.06276   0.05697  -0.0712   0.3710   1.0000
  11.500   1.1889   0.06464   0.05889  -0.0699   0.3690   1.0000
  11.750   1.1603   0.06906   0.06347  -0.0664   0.3660   1.0000
  12.000   1.1515   0.07186   0.06633  -0.0645   0.3633   1.0000
  12.250   1.1537   0.07369   0.06819  -0.0636   0.3611   1.0000
  12.500   1.1647   0.07478   0.06926  -0.0633   0.3595   1.0000
  12.750   1.1784   0.07559   0.07006  -0.0632   0.3581   1.0000
  13.000   1.1975   0.07591   0.07035  -0.0635   0.3567   1.0000
  13.250   1.2210   0.07580   0.07019  -0.0641   0.3553   1.0000
  13.500   1.1105   0.08824   0.08300  -0.0556   0.3479   1.0000
  13.750   1.1021   0.09126   0.08605  -0.0542   0.3449   1.0000
  14.000   1.1196   0.09172   0.08650  -0.0545   0.3436   1.0000
  14.250   1.1359   0.09230   0.08706  -0.0548   0.3425   1.0000
  14.500   1.1538   0.09270   0.08744  -0.0551   0.3415   1.0000
  14.750   1.1755   0.09271   0.08742  -0.0557   0.3404   1.0000
  15.000   1.2005   0.09237   0.08704  -0.0564   0.3394   1.0000
  15.250   0.6127   0.16390   0.15961  -0.0296   0.2827   1.0000
  15.500   0.6408   0.16254   0.15821  -0.0302   0.2823   1.0000
<< Back to GOE 570 AIRFOIL (goe570-il)

Polar data table (+)

Polar graphs


<< Back to GOE 570 AIRFOIL (goe570-il)