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GOE 430 AIRFOIL (goe430-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 430 AIRFOIL (goe430-il)
Reynolds number: 200,000
Max Cl/Cd: 79.48 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe430-il-200000-n5.txt
Download as CSV file: xf-goe430-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 430 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.4030   0.09980   0.09584  -0.0556   1.0000   0.0496
 -11.250  -0.4068   0.09796   0.09404  -0.0545   1.0000   0.0501
 -11.000  -0.6194   0.04648   0.04214  -0.1019   0.9775   0.0528
 -10.750  -0.6038   0.03729   0.03239  -0.1215   0.9684   0.0535
 -10.500  -0.5812   0.03397   0.02873  -0.1273   0.9625   0.0543
 -10.250  -0.5512   0.03140   0.02585  -0.1322   0.9590   0.0553
 -10.000  -0.5246   0.02949   0.02366  -0.1350   0.9532   0.0563
  -9.750  -0.4956   0.02781   0.02169  -0.1375   0.9482   0.0571
  -9.500  -0.4640   0.02630   0.01992  -0.1401   0.9449   0.0577
  -9.250  -0.4339   0.02508   0.01847  -0.1419   0.9415   0.0582
  -9.000  -0.4090   0.02376   0.01703  -0.1426   0.9362   0.0590
  -8.750  -0.3799   0.02263   0.01582  -0.1438   0.9324   0.0598
  -8.500  -0.3489   0.02171   0.01483  -0.1452   0.9294   0.0608
  -8.250  -0.3180   0.02093   0.01398  -0.1465   0.9264   0.0620
  -8.000  -0.2920   0.02029   0.01325  -0.1467   0.9209   0.0631
  -7.750  -0.2626   0.01960   0.01247  -0.1475   0.9166   0.0642
  -7.500  -0.2317   0.01893   0.01170  -0.1485   0.9132   0.0652
  -7.250  -0.2011   0.01831   0.01098  -0.1494   0.9100   0.0663
  -7.000  -0.1744   0.01781   0.01038  -0.1494   0.9038   0.0673
  -6.750  -0.1447   0.01729   0.00976  -0.1499   0.8987   0.0684
  -6.500  -0.1136   0.01667   0.00910  -0.1508   0.8945   0.0699
  -6.250  -0.0867   0.01621   0.00862  -0.1509   0.8874   0.0718
  -6.000  -0.0572   0.01577   0.00814  -0.1513   0.8814   0.0742
  -5.750  -0.0274   0.01538   0.00768  -0.1517   0.8760   0.0769
  -5.500   0.0004   0.01505   0.00728  -0.1517   0.8685   0.0796
  -5.250   0.0303   0.01463   0.00687  -0.1522   0.8627   0.0837
  -5.000   0.0585   0.01433   0.00655  -0.1523   0.8548   0.0893
  -4.750   0.0877   0.01402   0.00625  -0.1525   0.8476   0.0980
  -4.500   0.1165   0.01379   0.00603  -0.1526   0.8403   0.1102
  -4.250   0.1453   0.01361   0.00585  -0.1527   0.8330   0.1232
  -4.000   0.1746   0.01346   0.00563  -0.1528   0.8267   0.1343
  -3.750   0.2029   0.01332   0.00547  -0.1529   0.8183   0.1436
  -3.500   0.2323   0.01315   0.00524  -0.1530   0.8113   0.1509
  -3.250   0.2606   0.01300   0.00508  -0.1530   0.8021   0.1580
  -3.000   0.2898   0.01286   0.00487  -0.1531   0.7944   0.1649
  -2.750   0.3183   0.01268   0.00472  -0.1532   0.7851   0.1733
  -2.500   0.3473   0.01254   0.00456  -0.1533   0.7764   0.1823
  -2.250   0.3761   0.01239   0.00442  -0.1534   0.7668   0.1926
  -2.000   0.4048   0.01226   0.00431  -0.1535   0.7568   0.2032
  -1.750   0.4339   0.01215   0.00421  -0.1536   0.7469   0.2189
  -1.500   0.4624   0.01206   0.00416  -0.1536   0.7355   0.2407
  -1.250   0.4910   0.01199   0.00411  -0.1536   0.7240   0.2638
  -1.000   0.5195   0.01194   0.00405  -0.1536   0.7123   0.2858
  -0.750   0.5479   0.01192   0.00400  -0.1535   0.6998   0.3054
  -0.500   0.5758   0.01191   0.00396  -0.1534   0.6855   0.3236
  -0.250   0.6036   0.01192   0.00394  -0.1532   0.6708   0.3410
   0.000   0.6313   0.01195   0.00395  -0.1531   0.6566   0.3590
   0.250   0.6590   0.01200   0.00400  -0.1529   0.6438   0.3787
   0.500   0.6866   0.01206   0.00407  -0.1527   0.6323   0.4010
   0.750   0.7141   0.01214   0.00416  -0.1525   0.6201   0.4266
   1.000   0.7415   0.01223   0.00427  -0.1523   0.6084   0.4532
   1.250   0.7686   0.01234   0.00439  -0.1520   0.5966   0.4806
   1.500   0.7955   0.01246   0.00451  -0.1517   0.5848   0.5036
   1.750   0.8224   0.01256   0.00465  -0.1514   0.5733   0.5261
   2.000   0.8491   0.01268   0.00480  -0.1511   0.5630   0.5485
   2.250   0.8756   0.01282   0.00496  -0.1507   0.5521   0.5710
   2.500   0.9020   0.01295   0.00513  -0.1503   0.5401   0.5949
   2.750   0.9280   0.01311   0.00531  -0.1498   0.5277   0.6189
   3.000   0.9535   0.01329   0.00548  -0.1493   0.5146   0.6428
   3.500   1.0045   0.01363   0.00584  -0.1481   0.4913   0.6869
   3.750   1.0299   0.01379   0.00603  -0.1476   0.4825   0.7081
   4.250   1.0796   0.01408   0.00642  -0.1462   0.4645   0.7544
   4.500   1.1015   0.01417   0.00662  -0.1449   0.4542   0.8018
   4.750   1.1218   0.01415   0.00674  -0.1431   0.4442   1.0000
   5.000   1.1468   0.01447   0.00700  -0.1426   0.4349   1.0000
   5.250   1.1723   0.01475   0.00727  -0.1422   0.4254   1.0000
   5.500   1.1966   0.01507   0.00756  -0.1416   0.4148   1.0000
   5.750   1.2206   0.01541   0.00787  -0.1409   0.4040   1.0000
   6.000   1.2448   0.01571   0.00819  -0.1402   0.3926   1.0000
   6.250   1.2678   0.01606   0.00852  -0.1394   0.3782   1.0000
   6.500   1.2902   0.01643   0.00888  -0.1384   0.3609   1.0000
   6.750   1.3108   0.01686   0.00926  -0.1372   0.3375   1.0000
   7.000   1.3258   0.01756   0.00975  -0.1352   0.2909   1.0000
   7.250   1.3359   0.01857   0.01048  -0.1325   0.2547   1.0000
   7.500   1.3493   0.01938   0.01118  -0.1302   0.2387   1.0000
   7.750   1.3627   0.02010   0.01188  -0.1280   0.2292   1.0000
   8.000   1.3780   0.02077   0.01256  -0.1261   0.2216   1.0000
   8.500   1.4069   0.02226   0.01407  -0.1222   0.2072   1.0000
   8.750   1.4190   0.02316   0.01496  -0.1200   0.1995   1.0000
   9.000   1.4342   0.02390   0.01575  -0.1184   0.1912   1.0000
   9.250   1.4457   0.02487   0.01671  -0.1163   0.1822   1.0000
   9.500   1.4610   0.02563   0.01753  -0.1148   0.1726   1.0000
   9.750   1.4735   0.02659   0.01849  -0.1130   0.1630   1.0000
  10.000   1.4855   0.02760   0.01951  -0.1112   0.1517   1.0000
  10.250   1.4973   0.02865   0.02057  -0.1095   0.1396   1.0000
  10.500   1.5070   0.02987   0.02178  -0.1077   0.1278   1.0000
  10.750   1.5151   0.03126   0.02313  -0.1059   0.1164   1.0000
  11.000   1.5220   0.03277   0.02462  -0.1040   0.1071   1.0000
  11.250   1.5282   0.03439   0.02623  -0.1022   0.0998   1.0000
  11.500   1.5348   0.03602   0.02790  -0.1005   0.0942   1.0000
  11.750   1.5391   0.03789   0.02978  -0.0987   0.0885   1.0000
  12.000   1.5446   0.03969   0.03165  -0.0972   0.0839   1.0000
  12.250   1.5497   0.04159   0.03361  -0.0957   0.0790   1.0000
  12.500   1.5513   0.04387   0.03592  -0.0942   0.0741   1.0000
  12.750   1.5581   0.04570   0.03785  -0.0931   0.0657   1.0000
  13.250   1.5488   0.05189   0.04385  -0.0904   0.0324   1.0000
  13.500   1.5429   0.05532   0.04731  -0.0894   0.0282   1.0000
  13.750   1.5402   0.05852   0.05059  -0.0886   0.0260   1.0000
  14.000   1.5369   0.06188   0.05406  -0.0879   0.0244   1.0000
  14.250   1.5328   0.06545   0.05772  -0.0875   0.0232   1.0000
  14.500   1.5312   0.06878   0.06118  -0.0872   0.0222   1.0000
  14.750   1.5284   0.07233   0.06487  -0.0870   0.0214   1.0000
  15.000   1.5244   0.07613   0.06878  -0.0871   0.0206   1.0000
  15.250   1.5188   0.08023   0.07301  -0.0873   0.0199   1.0000
  15.500   1.5113   0.08466   0.07756  -0.0877   0.0194   1.0000
  15.750   1.5039   0.08919   0.08223  -0.0883   0.0189   1.0000
  16.000   1.4988   0.09347   0.08665  -0.0890   0.0185   1.0000
  16.250   1.4928   0.09796   0.09128  -0.0899   0.0181   1.0000
  16.500   1.4859   0.10266   0.09612  -0.0910   0.0178   1.0000
  16.750   1.4784   0.10751   0.10111  -0.0922   0.0175   1.0000
  17.000   1.4706   0.11249   0.10622  -0.0937   0.0172   1.0000
  17.250   1.4624   0.11763   0.11149  -0.0954   0.0170   1.0000
  17.500   1.4540   0.12287   0.11686  -0.0972   0.0167   1.0000
  17.750   1.4457   0.12817   0.12228  -0.0993   0.0165   1.0000
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