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GOE 358 AIRFOIL (goe358-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 358 AIRFOIL (goe358-il)
Reynolds number: 100,000
Max Cl/Cd: 58.54 at α=8.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe358-il-100000.txt
Download as CSV file: xf-goe358-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 358 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3083   0.10209   0.09701  -0.0308   1.0000   0.1328
  -8.000  -0.3393   0.10284   0.09794  -0.0306   1.0000   0.1363
  -7.750  -0.3762   0.10374   0.09904  -0.0312   1.0000   0.1371
  -7.500  -0.3243   0.09594   0.09110  -0.0271   1.0000   0.1413
  -7.250  -0.3241   0.09423   0.08943  -0.0248   1.0000   0.1462
  -7.000  -0.3457   0.09383   0.08916  -0.0222   1.0000   0.1501
  -6.750  -0.3807   0.09363   0.08918  -0.0300   1.0000   0.1529
  -6.500  -0.3611   0.08955   0.08506  -0.0200   1.0000   0.1558
  -6.250  -0.3574   0.08766   0.08321  -0.0172   1.0000   0.1597
  -6.000  -0.3732   0.08664   0.08230  -0.0227   1.0000   0.1676
  -5.750  -0.3748   0.08338   0.07909  -0.0227   1.0000   0.1699
  -5.500  -0.3713   0.08141   0.07716  -0.0178   1.0000   0.1722
  -5.250  -0.2996   0.04896   0.04389  -0.0762   1.0000   0.1225
  -5.000  -0.2907   0.04855   0.04363  -0.0724   1.0000   0.1237
  -4.750  -0.2055   0.03382   0.02758  -0.0976   1.0000   0.1171
  -4.500  -0.1623   0.03015   0.02312  -0.1038   1.0000   0.1198
  -4.250  -0.1276   0.02826   0.02060  -0.1068   1.0000   0.1217
  -4.000  -0.0880   0.02651   0.01870  -0.1102   0.9976   0.1253
  -3.750  -0.0392   0.02547   0.01747  -0.1148   0.9925   0.1309
  -3.500   0.0097   0.02445   0.01608  -0.1191   0.9863   0.1354
  -3.250   0.0582   0.02350   0.01513  -0.1234   0.9799   0.1429
  -3.000   0.1112   0.02273   0.01418  -0.1281   0.9718   0.1520
  -2.750   0.1590   0.02186   0.01344  -0.1319   0.9617   0.1643
  -2.500   0.2098   0.02101   0.01279  -0.1363   0.9535   0.1912
  -2.250   0.2546   0.02084   0.01316  -0.1391   0.9436   0.2855
  -2.000   0.2897   0.02170   0.01401  -0.1396   0.9313   0.3407
  -1.750   0.3272   0.02222   0.01463  -0.1406   0.9213   0.3672
  -1.500   0.3694   0.02232   0.01468  -0.1425   0.9126   0.3920
  -1.250   0.4038   0.02240   0.01485  -0.1430   0.9015   0.4114
  -1.000   0.4481   0.02219   0.01467  -0.1451   0.8951   0.4358
  -0.750   0.4799   0.02201   0.01449  -0.1451   0.8827   0.4563
  -0.500   0.5152   0.02158   0.01407  -0.1457   0.8719   0.4723
  -0.250   0.5566   0.02088   0.01331  -0.1474   0.8634   0.4857
   0.000   0.5881   0.02035   0.01280  -0.1474   0.8495   0.4953
   0.250   0.6209   0.01985   0.01225  -0.1475   0.8355   0.5068
   0.500   0.6540   0.01940   0.01173  -0.1478   0.8207   0.5186
   0.750   0.6850   0.01894   0.01126  -0.1475   0.8049   0.5272
   1.000   0.7170   0.01859   0.01079  -0.1476   0.7880   0.5347
   1.250   0.7471   0.01827   0.01043  -0.1473   0.7701   0.5416
   1.500   0.7778   0.01810   0.01011  -0.1471   0.7513   0.5497
   1.750   0.8052   0.01801   0.00996  -0.1465   0.7303   0.5561
   2.000   0.8329   0.01804   0.00989  -0.1460   0.7086   0.5637
   2.250   0.8601   0.01806   0.00983  -0.1453   0.6880   0.5715
   2.500   0.8881   0.01818   0.00982  -0.1449   0.6687   0.5806
   2.750   0.9151   0.01829   0.00989  -0.1444   0.6501   0.5888
   3.000   0.9421   0.01849   0.01002  -0.1440   0.6322   0.5984
   3.250   0.9689   0.01866   0.01015  -0.1435   0.6161   0.6095
   3.500   0.9958   0.01883   0.01027  -0.1430   0.6012   0.6220
   3.750   1.0223   0.01900   0.01045  -0.1425   0.5867   0.6362
   4.000   1.0482   0.01920   0.01071  -0.1420   0.5729   0.6529
   4.250   1.0741   0.01943   0.01104  -0.1415   0.5611   0.6766
   4.500   1.1000   0.01950   0.01130  -0.1409   0.5517   0.7212
   4.750   1.1242   0.01955   0.01165  -0.1400   0.5416   1.0000
   5.000   1.1524   0.02010   0.01213  -0.1401   0.5325   1.0000
   5.250   1.1802   0.02060   0.01258  -0.1400   0.5236   1.0000
   5.500   1.2062   0.02117   0.01318  -0.1397   0.5145   1.0000
   5.750   1.2339   0.02160   0.01350  -0.1394   0.5052   1.0000
   6.000   1.2575   0.02207   0.01408  -0.1385   0.4936   1.0000
   6.250   1.2822   0.02249   0.01450  -0.1377   0.4820   1.0000
   6.500   1.3076   0.02283   0.01478  -0.1370   0.4702   1.0000
   6.750   1.3315   0.02318   0.01518  -0.1360   0.4578   1.0000
   7.000   1.3539   0.02354   0.01563  -0.1348   0.4445   1.0000
   7.250   1.3764   0.02388   0.01604  -0.1336   0.4311   1.0000
   7.500   1.3986   0.02418   0.01638  -0.1323   0.4169   1.0000
   7.750   1.4197   0.02445   0.01673  -0.1309   0.4015   1.0000
   8.000   1.4390   0.02468   0.01703  -0.1291   0.3838   1.0000
   8.250   1.4564   0.02488   0.01729  -0.1270   0.3634   1.0000
   8.500   1.4708   0.02514   0.01761  -0.1244   0.3393   1.0000
   8.750   1.4809   0.02548   0.01806  -0.1212   0.3059   1.0000
   9.000   1.4838   0.02620   0.01870  -0.1171   0.2415   1.0000
   9.250   1.4743   0.02841   0.02019  -0.1118   0.1808   1.0000
   9.500   1.4654   0.03089   0.02238  -0.1067   0.1550   1.0000
   9.750   1.4609   0.03309   0.02446  -0.1024   0.1381   1.0000
  10.000   1.4609   0.03508   0.02642  -0.0988   0.1249   1.0000
  10.250   1.4625   0.03704   0.02835  -0.0957   0.1147   1.0000
  10.500   1.4646   0.03906   0.03026  -0.0929   0.1067   1.0000
  10.750   1.4704   0.04090   0.03221  -0.0904   0.0989   1.0000
  11.000   1.4775   0.04298   0.03415  -0.0882   0.0927   1.0000
  11.250   1.4867   0.04489   0.03619  -0.0862   0.0871   1.0000
  11.500   1.5045   0.04703   0.03809  -0.0849   0.0814   1.0000
  11.750   1.5130   0.04910   0.04043  -0.0829   0.0775   1.0000
  12.000   1.5282   0.05119   0.04258  -0.0815   0.0737   1.0000
  12.250   1.5574   0.05399   0.04530  -0.0813   0.0695   1.0000
  12.500   1.5593   0.05645   0.04809  -0.0790   0.0674   1.0000
  12.750   1.5647   0.05912   0.05099  -0.0771   0.0652   1.0000
  13.000   1.5716   0.06197   0.05403  -0.0755   0.0634   1.0000
  13.250   1.5794   0.06492   0.05711  -0.0741   0.0617   1.0000
  13.500   1.5969   0.06965   0.06191  -0.0738   0.0595   1.0000
  13.750   1.5797   0.07294   0.06555  -0.0711   0.0591   1.0000
  14.000   1.5615   0.07675   0.06969  -0.0692   0.0587   1.0000
  14.250   1.5427   0.08106   0.07432  -0.0680   0.0584   1.0000
  14.500   1.5221   0.08589   0.07945  -0.0676   0.0582   1.0000
  14.750   1.5003   0.09123   0.08510  -0.0679   0.0581   1.0000
  15.000   1.4768   0.09715   0.09129  -0.0691   0.0581   1.0000
  15.250   1.4522   0.10362   0.09803  -0.0710   0.0582   1.0000
  15.500   1.4268   0.11071   0.10536  -0.0739   0.0585   1.0000
  15.750   1.4007   0.11847   0.11334  -0.0778   0.0588   1.0000
  16.000   1.3747   0.12698   0.12205  -0.0825   0.0591   1.0000
  16.250   1.3502   0.13606   0.13127  -0.0879   0.0595   1.0000
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