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

GOE 508 AIRFOIL (goe508-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 508 AIRFOIL (goe508-il)
Reynolds number: 500,000
Max Cl/Cd: 97.84 at α=4.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe508-il-500000-n5.txt
Download as CSV file: xf-goe508-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 508 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
  ------ -------- --------- --------- -------- -------- --------
 -14.000  -0.5214   0.04172   0.03769  -0.1458   0.8954   0.0286
 -13.750  -0.5418   0.03534   0.03089  -0.1526   0.8637   0.0287
 -13.500  -0.5567   0.03236   0.02764  -0.1530   0.8426   0.0287
 -13.250  -0.5685   0.03028   0.02533  -0.1514   0.8280   0.0287
 -13.000  -0.5763   0.02871   0.02360  -0.1488   0.8160   0.0289
 -12.750  -0.5799   0.02747   0.02222  -0.1459   0.8070   0.0290
 -12.500  -0.5807   0.02643   0.02107  -0.1426   0.7988   0.0291
 -12.250  -0.5790   0.02564   0.02016  -0.1393   0.7917   0.0292
 -12.000  -0.5709   0.02484   0.01928  -0.1370   0.7858   0.0294
 -11.750  -0.5595   0.02410   0.01846  -0.1350   0.7797   0.0295
 -11.500  -0.5465   0.02341   0.01765  -0.1331   0.7742   0.0297
 -11.250  -0.5320   0.02268   0.01683  -0.1315   0.7689   0.0299
 -11.000  -0.5160   0.02202   0.01609  -0.1299   0.7634   0.0301
 -10.750  -0.4992   0.02138   0.01534  -0.1285   0.7582   0.0303
 -10.500  -0.4810   0.02079   0.01465  -0.1271   0.7538   0.0305
 -10.250  -0.4621   0.02018   0.01395  -0.1259   0.7490   0.0308
 -10.000  -0.4427   0.01958   0.01325  -0.1247   0.7438   0.0310
  -9.750  -0.4227   0.01903   0.01259  -0.1235   0.7387   0.0313
  -9.500  -0.4019   0.01852   0.01197  -0.1225   0.7341   0.0316
  -9.250  -0.3804   0.01799   0.01136  -0.1215   0.7293   0.0319
  -9.000  -0.3585   0.01751   0.01077  -0.1205   0.7245   0.0322
  -8.750  -0.3361   0.01707   0.01023  -0.1196   0.7199   0.0325
  -8.500  -0.3136   0.01662   0.00970  -0.1187   0.7155   0.0328
  -8.250  -0.2911   0.01615   0.00920  -0.1178   0.7106   0.0331
  -8.000  -0.2677   0.01579   0.00880  -0.1170   0.7052   0.0336
  -7.750  -0.2440   0.01549   0.00843  -0.1163   0.7002   0.0340
  -7.500  -0.2196   0.01518   0.00809  -0.1156   0.6954   0.0345
  -7.250  -0.1953   0.01486   0.00773  -0.1149   0.6904   0.0350
  -7.000  -0.1710   0.01456   0.00736  -0.1142   0.6853   0.0355
  -6.750  -0.1466   0.01428   0.00700  -0.1135   0.6807   0.0360
  -6.500  -0.1216   0.01399   0.00667  -0.1129   0.6757   0.0365
  -6.250  -0.0966   0.01373   0.00635  -0.1122   0.6702   0.0370
  -6.000  -0.0727   0.01343   0.00601  -0.1115   0.6647   0.0376
  -5.750  -0.0476   0.01318   0.00575  -0.1109   0.6594   0.0383
  -5.500  -0.0223   0.01297   0.00551  -0.1103   0.6536   0.0390
  -5.250   0.0028   0.01278   0.00527  -0.1097   0.6482   0.0398
  -5.000   0.0283   0.01259   0.00504  -0.1091   0.6432   0.0408
  -4.750   0.0542   0.01243   0.00484  -0.1086   0.6377   0.0417
  -4.500   0.0791   0.01222   0.00462  -0.1079   0.6322   0.0430
  -4.250   0.1045   0.01207   0.00444  -0.1074   0.6271   0.0442
  -4.000   0.1303   0.01192   0.00427  -0.1069   0.6215   0.0455
  -3.750   0.1559   0.01180   0.00410  -0.1063   0.6155   0.0469
  -3.500   0.1808   0.01165   0.00392  -0.1056   0.6102   0.0485
  -3.250   0.2067   0.01151   0.00378  -0.1051   0.6050   0.0504
  -3.000   0.2325   0.01142   0.00366  -0.1046   0.5998   0.0524
  -2.750   0.2576   0.01130   0.00352  -0.1040   0.5949   0.0551
  -2.500   0.2834   0.01120   0.00342  -0.1035   0.5903   0.0584
  -2.250   0.3088   0.01109   0.00332  -0.1029   0.5845   0.0628
  -2.000   0.3334   0.01102   0.00324  -0.1021   0.5777   0.0686
  -1.750   0.3585   0.01094   0.00319  -0.1015   0.5716   0.0797
  -1.500   0.3839   0.01089   0.00316  -0.1010   0.5657   0.0918
  -1.250   0.4092   0.01087   0.00314  -0.1004   0.5612   0.1017
  -1.000   0.4345   0.01084   0.00311  -0.0998   0.5572   0.1096
  -0.750   0.4604   0.01081   0.00309  -0.0993   0.5525   0.1168
  -0.500   0.4854   0.01077   0.00308  -0.0987   0.5472   0.1252
  -0.250   0.5101   0.01078   0.00307  -0.0980   0.5424   0.1329
   0.000   0.5352   0.01076   0.00307  -0.0974   0.5385   0.1438
   0.250   0.5603   0.01071   0.00308  -0.0968   0.5340   0.1606
   0.500   0.5845   0.01067   0.00310  -0.0961   0.5290   0.1832
   0.750   0.6079   0.01063   0.00313  -0.0952   0.5243   0.2162
   1.000   0.6317   0.01054   0.00317  -0.0944   0.5203   0.2586
   1.250   0.6550   0.01041   0.00322  -0.0936   0.5163   0.3201
   1.500   0.6755   0.01015   0.00328  -0.0922   0.5120   0.4315
   1.750   0.6924   0.00985   0.00336  -0.0901   0.5074   0.5736
   2.000   0.7083   0.00956   0.00346  -0.0876   0.5034   0.7005
   2.250   0.7255   0.00931   0.00359  -0.0852   0.4986   0.8219
   2.500   0.7903   0.00942   0.00387  -0.0929   0.4911   0.9325
   2.750   0.8500   0.00963   0.00403  -0.0998   0.4855   0.9602
   3.000   0.8979   0.00981   0.00420  -0.1040   0.4799   0.9829
   3.250   0.9529   0.01006   0.00438  -0.1099   0.4730   0.9983
   3.500   0.9816   0.01020   0.00448  -0.1103   0.4674   1.0000
   3.750   0.9996   0.01031   0.00458  -0.1083   0.4616   1.0000
   4.000   1.0159   0.01045   0.00468  -0.1061   0.4557   1.0000
   4.250   1.0330   0.01059   0.00479  -0.1040   0.4501   1.0000
   4.500   1.0498   0.01073   0.00492  -0.1019   0.4432   1.0000
   4.750   1.0631   0.01092   0.00506  -0.0990   0.4361   1.0000
   5.000   1.0767   0.01106   0.00518  -0.0962   0.4281   1.0000
   5.250   1.0858   0.01127   0.00535  -0.0926   0.4193   1.0000
   5.500   1.0980   0.01148   0.00553  -0.0897   0.4082   1.0000
   5.750   1.1085   0.01177   0.00576  -0.0865   0.3958   1.0000
   6.000   1.1169   0.01217   0.00608  -0.0830   0.3796   1.0000
   6.250   1.1233   0.01269   0.00650  -0.0794   0.3601   1.0000
   6.500   1.1262   0.01340   0.00707  -0.0754   0.3365   1.0000
   6.750   1.1312   0.01415   0.00770  -0.0720   0.3150   1.0000
   7.000   1.1382   0.01491   0.00837  -0.0690   0.2979   1.0000
   7.250   1.1430   0.01584   0.00919  -0.0660   0.2790   1.0000
   7.500   1.1526   0.01663   0.00993  -0.0637   0.2676   1.0000
   7.750   1.1626   0.01746   0.01070  -0.0616   0.2582   1.0000
   8.000   1.1761   0.01815   0.01138  -0.0600   0.2521   1.0000
   8.250   1.1884   0.01894   0.01215  -0.0584   0.2455   1.0000
   8.750   1.2144   0.02054   0.01374  -0.0555   0.2359   1.0000
   9.000   1.2264   0.02145   0.01463  -0.0541   0.2298   1.0000
   9.250   1.2375   0.02244   0.01560  -0.0527   0.2251   1.0000
   9.500   1.2506   0.02332   0.01650  -0.0515   0.2221   1.0000
   9.750   1.2657   0.02410   0.01731  -0.0505   0.2199   1.0000
  10.000   1.2800   0.02494   0.01818  -0.0495   0.2173   1.0000
  10.250   1.2933   0.02587   0.01913  -0.0485   0.2149   1.0000
  10.500   1.3057   0.02687   0.02015  -0.0474   0.2124   1.0000
  10.750   1.3170   0.02797   0.02126  -0.0463   0.2099   1.0000
  11.000   1.3275   0.02915   0.02245  -0.0452   0.2071   1.0000
  11.250   1.3409   0.03014   0.02349  -0.0443   0.2051   1.0000
  11.500   1.3548   0.03111   0.02451  -0.0436   0.2030   1.0000
  11.750   1.3678   0.03216   0.02559  -0.0428   0.2004   1.0000
  12.000   1.3793   0.03334   0.02681  -0.0419   0.1980   1.0000
  12.250   1.3902   0.03458   0.02808  -0.0411   0.1955   1.0000
  12.500   1.3988   0.03605   0.02956  -0.0402   0.1926   1.0000
  12.750   1.4097   0.03734   0.03088  -0.0394   0.1895   1.0000
  13.000   1.4218   0.03855   0.03214  -0.0388   0.1863   1.0000
  13.250   1.4315   0.03998   0.03360  -0.0381   0.1813   1.0000
  13.500   1.4382   0.04171   0.03533  -0.0373   0.1774   1.0000
  13.750   1.4488   0.04310   0.03677  -0.0367   0.1735   1.0000
  14.000   1.4587   0.04457   0.03828  -0.0362   0.1699   1.0000
  14.250   1.4646   0.04644   0.04015  -0.0355   0.1639   1.0000
  14.500   1.4720   0.04817   0.04192  -0.0349   0.1589   1.0000
  14.750   1.4766   0.05020   0.04394  -0.0343   0.1515   1.0000
  15.000   1.4807   0.05232   0.04607  -0.0338   0.1449   1.0000
  15.250   1.4812   0.05481   0.04853  -0.0332   0.1369   1.0000
  15.500   1.4837   0.05711   0.05085  -0.0327   0.1308   1.0000
  15.750   1.4837   0.05970   0.05343  -0.0322   0.1245   1.0000
  16.000   1.4837   0.06232   0.05606  -0.0318   0.1176   1.0000
  16.250   1.4835   0.06501   0.05876  -0.0314   0.1124   1.0000
  16.500   1.4844   0.06759   0.06135  -0.0311   0.1067   1.0000
  16.750   1.4835   0.07040   0.06419  -0.0308   0.1024   1.0000
  17.000   1.4866   0.07279   0.06662  -0.0307   0.0978   1.0000
  17.250   1.4824   0.07605   0.06989  -0.0306   0.0899   1.0000
  17.500   1.4805   0.07906   0.07291  -0.0305   0.0825   1.0000
  17.750   1.4674   0.08343   0.07723  -0.0305   0.0705   1.0000
  18.000   1.4611   0.08709   0.08090  -0.0307   0.0658   1.0000
<< Back to GOE 508 AIRFOIL (goe508-il)

Polar data table (+)

Polar graphs


<< Back to GOE 508 AIRFOIL (goe508-il)