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GOE 572 AIRFOIL (goe572-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 572 AIRFOIL (goe572-il)
Reynolds number: 100,000
Max Cl/Cd: 38.41 at α=3°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe572-il-100000-n5.txt
Download as CSV file: xf-goe572-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 572 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
  ------ -------- --------- --------- -------- -------- --------
 -11.000   0.2216   0.10308   0.09689  -0.1317   0.6646   0.0536
 -10.750   0.2233   0.10060   0.09436  -0.1337   0.6567   0.0538
 -10.500   0.2233   0.09814   0.09191  -0.1352   0.6489   0.0539
 -10.250   0.2261   0.09545   0.08917  -0.1364   0.6416   0.0540
 -10.000   0.2583   0.09141   0.08502  -0.1340   0.6318   0.0563
  -9.750   0.2679   0.08933   0.08288  -0.1341   0.6244   0.0594
  -9.500   0.2706   0.08714   0.08067  -0.1347   0.6180   0.0615
  -9.250   0.2661   0.08505   0.07861  -0.1360   0.6126   0.0636
  -9.000   0.2716   0.08250   0.07601  -0.1362   0.6070   0.0631
  -8.750   0.2515   0.07640   0.06993  -0.1387   0.6046   0.0443
  -8.500   0.2594   0.07425   0.06779  -0.1378   0.5982   0.0436
  -8.250   0.2575   0.07165   0.06520  -0.1379   0.5930   0.0433
  -8.000   0.2531   0.06896   0.06248  -0.1382   0.5890   0.0431
  -7.750   0.2410   0.06615   0.05972  -0.1380   0.5841   0.0434
  -7.500   0.2315   0.06391   0.05750  -0.1364   0.5795   0.0431
  -7.250   0.2199   0.06118   0.05474  -0.1352   0.5756   0.0432
  -7.000   0.2146   0.05847   0.05194  -0.1341   0.5722   0.0430
  -6.750   0.2073   0.05558   0.04900  -0.1324   0.5679   0.0429
  -6.500   0.2021   0.05268   0.04601  -0.1304   0.5637   0.0427
  -6.250   0.1981   0.04968   0.04284  -0.1280   0.5598   0.0427
  -6.000   0.1953   0.04656   0.03945  -0.1253   0.5565   0.0429
  -5.750   0.1879   0.04291   0.03538  -0.1213   0.5533   0.0440
  -5.500   0.1876   0.04048   0.03267  -0.1176   0.5487   0.0452
  -5.250   0.1999   0.03944   0.03156  -0.1156   0.5440   0.0462
  -5.000   0.2096   0.03776   0.02961  -0.1129   0.5401   0.0470
  -4.750   0.2188   0.03619   0.02778  -0.1100   0.5358   0.0480
  -4.500   0.2284   0.03485   0.02617  -0.1069   0.5311   0.0501
  -4.250   0.2390   0.03321   0.02410  -0.1037   0.5270   0.0520
  -4.000   0.2530   0.03162   0.02202  -0.1010   0.5233   0.0530
  -3.750   0.2678   0.03046   0.02050  -0.0985   0.5192   0.0545
  -3.500   0.2839   0.02975   0.01974  -0.0965   0.5143   0.0563
  -3.250   0.3028   0.02905   0.01886  -0.0949   0.5098   0.0583
  -3.000   0.3252   0.02818   0.01768  -0.0937   0.5061   0.0597
  -2.750   0.3442   0.02754   0.01684  -0.0919   0.5016   0.0615
  -2.500   0.3638   0.02706   0.01613  -0.0902   0.4970   0.0641
  -2.250   0.3868   0.02643   0.01533  -0.0892   0.4928   0.0661
  -2.000   0.4127   0.02585   0.01463  -0.0889   0.4893   0.0682
  -1.750   0.4319   0.02553   0.01429  -0.0873   0.4848   0.0702
  -1.500   0.4512   0.02530   0.01401  -0.0857   0.4800   0.0737
  -1.250   0.4738   0.02504   0.01361  -0.0847   0.4760   0.0774
  -1.000   0.4983   0.02463   0.01313  -0.0841   0.4727   0.0811
  -0.750   0.5146   0.02451   0.01304  -0.0820   0.4683   0.0849
  -0.500   0.5318   0.02443   0.01293  -0.0800   0.4637   0.0899
  -0.250   0.5534   0.02428   0.01272  -0.0789   0.4599   0.0978
   0.000   0.5800   0.02412   0.01246  -0.0787   0.4565   0.1123
   0.250   0.6031   0.02409   0.01254  -0.0782   0.4522   0.1376
   0.500   0.6458   0.02349   0.01277  -0.0823   0.4471   0.3680
   1.000   0.8787   0.02358   0.01354  -0.1198   0.4339   1.0000
   1.250   0.8945   0.02388   0.01374  -0.1177   0.4298   1.0000
   1.500   0.9125   0.02414   0.01384  -0.1161   0.4265   1.0000
   1.750   0.9334   0.02436   0.01387  -0.1150   0.4237   1.0000
   2.000   0.9444   0.02482   0.01433  -0.1122   0.4197   1.0000
   2.250   0.9567   0.02522   0.01468  -0.1096   0.4156   1.0000
   2.500   0.9720   0.02553   0.01490  -0.1076   0.4119   1.0000
   2.750   0.9905   0.02580   0.01503  -0.1061   0.4091   1.0000
   3.000   1.0056   0.02618   0.01532  -0.1041   0.4059   1.0000
   3.250   1.0120   0.02672   0.01590  -0.1006   0.4020   1.0000
   3.500   1.0211   0.02715   0.01629  -0.0976   0.3986   1.0000
   3.750   1.0340   0.02749   0.01654  -0.0952   0.3955   1.0000
   4.000   1.0515   0.02778   0.01672  -0.0937   0.3929   1.0000
   4.250   1.0591   0.02830   0.01723  -0.0906   0.3896   1.0000
   4.500   1.0617   0.02900   0.01798  -0.0868   0.3858   1.0000
   4.750   1.0703   0.02957   0.01853  -0.0841   0.3824   1.0000
   5.000   1.0842   0.03003   0.01893  -0.0822   0.3796   1.0000
   5.250   1.1026   0.03036   0.01916  -0.0811   0.3771   1.0000
   5.500   1.1086   0.03118   0.02000  -0.0783   0.3741   1.0000
   5.750   1.1075   0.03229   0.02120  -0.0748   0.3704   1.0000
   6.000   1.1136   0.03319   0.02212  -0.0723   0.3671   1.0000
   6.250   1.1259   0.03385   0.02275  -0.0707   0.3644   1.0000
   6.500   1.1444   0.03426   0.02307  -0.0698   0.3620   1.0000
   6.750   1.1500   0.03536   0.02420  -0.0677   0.3593   1.0000
   7.000   1.1375   0.03747   0.02647  -0.0639   0.3553   1.0000
   7.250   1.1377   0.03906   0.02811  -0.0618   0.3521   1.0000
   7.500   1.1471   0.04012   0.02917  -0.0604   0.3495   1.0000
   7.750   1.1654   0.04064   0.02964  -0.0598   0.3473   1.0000
   8.000   1.1876   0.04097   0.02990  -0.0595   0.3456   1.0000
   8.250   1.1279   0.04738   0.03668  -0.0544   0.3400   1.0000
   8.500   1.1101   0.05116   0.04057  -0.0525   0.3361   1.0000
   8.750   1.1230   0.05220   0.04161  -0.0518   0.3337   1.0000
   9.000   1.1440   0.05252   0.04188  -0.0515   0.3322   1.0000
   9.250   1.1741   0.05201   0.04129  -0.0515   0.3308   1.0000
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