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GOE 289 (MVA 289) AIRFOIL (goe289-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 289 (MVA 289) AIRFOIL (goe289-il)
Reynolds number: 500,000
Max Cl/Cd: 87.42 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe289-il-500000-n5.txt
Download as CSV file: xf-goe289-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 289 (MVA 289) 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.000  -0.4331   0.05213   0.04878  -0.1259   0.9393   0.0248
 -12.750  -0.4353   0.04043   0.03668  -0.1458   0.9285   0.0249
 -12.500  -0.4196   0.03312   0.02897  -0.1614   0.9127   0.0250
 -12.000  -0.4122   0.02829   0.02362  -0.1658   0.8774   0.0251
 -11.750  -0.4157   0.02707   0.02222  -0.1629   0.8615   0.0252
 -11.500  -0.4127   0.02606   0.02103  -0.1604   0.8466   0.0253
 -11.250  -0.4055   0.02508   0.01988  -0.1583   0.8328   0.0253
 -11.000  -0.3955   0.02422   0.01883  -0.1564   0.8186   0.0254
 -10.750  -0.3841   0.02335   0.01778  -0.1545   0.8040   0.0255
 -10.500  -0.3724   0.02232   0.01659  -0.1527   0.7901   0.0257
 -10.250  -0.3585   0.02144   0.01558  -0.1510   0.7770   0.0258
 -10.000  -0.3428   0.02069   0.01472  -0.1495   0.7656   0.0261
  -9.750  -0.3257   0.02004   0.01395  -0.1481   0.7551   0.0262
  -9.500  -0.3070   0.01951   0.01332  -0.1468   0.7452   0.0265
  -9.250  -0.2881   0.01894   0.01265  -0.1456   0.7370   0.0267
  -9.000  -0.2680   0.01844   0.01206  -0.1445   0.7289   0.0270
  -8.750  -0.2478   0.01794   0.01145  -0.1434   0.7214   0.0272
  -8.500  -0.2269   0.01743   0.01086  -0.1424   0.7140   0.0274
  -8.250  -0.2058   0.01697   0.01029  -0.1414   0.7069   0.0276
  -8.000  -0.1839   0.01653   0.00977  -0.1404   0.7007   0.0279
  -7.750  -0.1617   0.01610   0.00926  -0.1395   0.6937   0.0281
  -7.500  -0.1397   0.01572   0.00878  -0.1386   0.6869   0.0283
  -7.250  -0.1167   0.01533   0.00833  -0.1377   0.6807   0.0286
  -7.000  -0.0939   0.01498   0.00790  -0.1369   0.6739   0.0288
  -6.750  -0.0709   0.01467   0.00750  -0.1360   0.6673   0.0290
  -6.500  -0.0474   0.01434   0.00712  -0.1352   0.6604   0.0293
  -6.250  -0.0240   0.01406   0.00676  -0.1344   0.6532   0.0295
  -6.000  -0.0002   0.01380   0.00644  -0.1336   0.6465   0.0297
  -5.750   0.0225   0.01344   0.00603  -0.1327   0.6386   0.0301
  -5.500   0.0453   0.01314   0.00567  -0.1317   0.6311   0.0305
  -5.250   0.0691   0.01287   0.00536  -0.1309   0.6231   0.0310
  -5.000   0.0925   0.01267   0.00509  -0.1300   0.6150   0.0315
  -4.750   0.1168   0.01248   0.00485  -0.1293   0.6061   0.0322
  -4.500   0.1403   0.01233   0.00463  -0.1284   0.5972   0.0328
  -4.250   0.1647   0.01218   0.00442  -0.1277   0.5881   0.0334
  -4.000   0.1884   0.01207   0.00423  -0.1268   0.5797   0.0339
  -3.750   0.2130   0.01195   0.00405  -0.1261   0.5717   0.0345
  -3.500   0.2365   0.01183   0.00386  -0.1252   0.5644   0.0354
  -3.250   0.2613   0.01170   0.00370  -0.1245   0.5572   0.0366
  -3.000   0.2852   0.01162   0.00357  -0.1237   0.5496   0.0379
  -2.750   0.3096   0.01154   0.00344  -0.1230   0.5427   0.0401
  -2.500   0.3337   0.01142   0.00332  -0.1222   0.5361   0.0449
  -2.250   0.3561   0.01122   0.00321  -0.1212   0.5301   0.0746
  -2.000   0.3807   0.01112   0.00317  -0.1205   0.5242   0.0955
  -1.750   0.4047   0.01108   0.00315  -0.1197   0.5175   0.1084
  -1.500   0.4285   0.01107   0.00313  -0.1189   0.5117   0.1174
  -1.250   0.4534   0.01106   0.00310  -0.1183   0.5058   0.1257
  -1.000   0.4773   0.01105   0.00309  -0.1175   0.5001   0.1347
  -0.750   0.5010   0.01107   0.00308  -0.1166   0.4951   0.1431
  -0.500   0.5255   0.01103   0.00307  -0.1159   0.4898   0.1545
  -0.250   0.5489   0.01102   0.00308  -0.1150   0.4840   0.1685
   0.000   0.5710   0.01101   0.00309  -0.1139   0.4785   0.1890
   0.250   0.5943   0.01091   0.00312  -0.1131   0.4732   0.2292
   0.500   0.6164   0.01084   0.00318  -0.1120   0.4676   0.2815
   0.750   0.6376   0.01085   0.00327  -0.1107   0.4624   0.3250
   1.000   0.6604   0.01086   0.00333  -0.1097   0.4577   0.3508
   1.250   0.6823   0.01090   0.00338  -0.1085   0.4525   0.3681
   1.500   0.7028   0.01096   0.00344  -0.1070   0.4472   0.3837
   1.750   0.7239   0.01102   0.00351  -0.1057   0.4421   0.3973
   2.000   0.7457   0.01107   0.00358  -0.1045   0.4368   0.4103
   2.250   0.7656   0.01117   0.00367  -0.1030   0.4308   0.4250
   2.500   0.7856   0.01123   0.00379  -0.1015   0.4259   0.4495
   2.750   0.8059   0.01122   0.00392  -0.1001   0.4209   0.4960
   3.000   0.8221   0.01111   0.00411  -0.0979   0.4158   0.6091
   3.250   0.8308   0.01084   0.00433  -0.0940   0.4115   0.7817
   3.750   0.9697   0.01120   0.00490  -0.1125   0.3978   1.0000
   4.000   0.9882   0.01140   0.00505  -0.1107   0.3932   1.0000
   4.250   1.0084   0.01156   0.00520  -0.1093   0.3885   1.0000
   4.500   1.0272   0.01177   0.00537  -0.1077   0.3834   1.0000
   4.750   1.0449   0.01202   0.00557  -0.1060   0.3787   1.0000
   5.000   1.0658   0.01221   0.00575  -0.1048   0.3749   1.0000
   5.250   1.0858   0.01242   0.00595  -0.1035   0.3707   1.0000
   5.500   1.1050   0.01267   0.00618  -0.1021   0.3666   1.0000
   5.750   1.1230   0.01297   0.00644  -0.1005   0.3628   1.0000
   6.000   1.1435   0.01320   0.00668  -0.0994   0.3595   1.0000
   6.250   1.1639   0.01345   0.00693  -0.0983   0.3561   1.0000
   6.500   1.1833   0.01374   0.00722  -0.0970   0.3526   1.0000
   6.750   1.2016   0.01407   0.00753  -0.0956   0.3491   1.0000
   7.000   1.2194   0.01444   0.00788  -0.0942   0.3458   1.0000
   7.250   1.2399   0.01472   0.00819  -0.0933   0.3428   1.0000
   7.500   1.2596   0.01504   0.00853  -0.0922   0.3396   1.0000
   7.750   1.2784   0.01541   0.00890  -0.0910   0.3366   1.0000
   8.000   1.2964   0.01581   0.00931  -0.0898   0.3337   1.0000
   8.250   1.3137   0.01626   0.00976  -0.0885   0.3311   1.0000
   8.500   1.3321   0.01668   0.01020  -0.0874   0.3288   1.0000
   8.750   1.3518   0.01705   0.01061  -0.0865   0.3266   1.0000
   9.000   1.3699   0.01750   0.01108  -0.0855   0.3228   1.0000
   9.250   1.3864   0.01802   0.01162  -0.0843   0.3189   1.0000
   9.500   1.4007   0.01867   0.01226  -0.0828   0.3148   1.0000
   9.750   1.4179   0.01920   0.01282  -0.0818   0.3099   1.0000
  10.000   1.4341   0.01980   0.01344  -0.0806   0.3052   1.0000
  10.250   1.4467   0.02059   0.01422  -0.0792   0.2998   1.0000
  10.500   1.4617   0.02128   0.01494  -0.0780   0.2960   1.0000
  10.750   1.4782   0.02190   0.01562  -0.0771   0.2919   1.0000
  11.000   1.4913   0.02274   0.01648  -0.0758   0.2868   1.0000
  11.250   1.5018   0.02375   0.01748  -0.0744   0.2822   1.0000
  11.500   1.5174   0.02448   0.01828  -0.0735   0.2774   1.0000
  11.750   1.5299   0.02544   0.01926  -0.0724   0.2724   1.0000
  12.000   1.5381   0.02670   0.02053  -0.0710   0.2670   1.0000
  12.250   1.5509   0.02769   0.02158  -0.0700   0.2604   1.0000
  12.500   1.5566   0.02922   0.02310  -0.0686   0.2528   1.0000
  12.750   1.5647   0.03062   0.02453  -0.0674   0.2434   1.0000
  13.000   1.5660   0.03261   0.02649  -0.0659   0.2308   1.0000
  13.250   1.5644   0.03490   0.02876  -0.0644   0.2167   1.0000
  13.500   1.5495   0.03843   0.03218  -0.0623   0.1931   1.0000
  13.750   1.5220   0.04328   0.03689  -0.0600   0.1632   1.0000
  14.000   1.4903   0.04882   0.04231  -0.0579   0.1335   1.0000
  14.250   1.4623   0.05431   0.04773  -0.0565   0.1082   1.0000
  14.500   1.4375   0.05973   0.05311  -0.0555   0.0901   1.0000
  14.750   1.4225   0.06425   0.05765  -0.0549   0.0799   1.0000
  15.000   1.4075   0.06887   0.06230  -0.0545   0.0694   1.0000
  15.250   1.3890   0.07406   0.06750  -0.0543   0.0559   1.0000
  15.500   1.3642   0.08017   0.07358  -0.0543   0.0400   1.0000
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