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GOE 502 AIRFOIL (goe502-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 502 AIRFOIL (goe502-il)
Reynolds number: 100,000
Max Cl/Cd: 53.03 at α=7°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe502-il-100000-n5.txt
Download as CSV file: xf-goe502-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 502 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
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.1361   0.09484   0.08908  -0.0917   0.9436   0.0622
  -9.500  -0.1375   0.08744   0.08165  -0.0983   0.9397   0.0627
  -9.250  -0.1523   0.08036   0.07455  -0.1022   0.9297   0.0627
  -9.000  -0.3228   0.04666   0.04012  -0.1333   0.8997   0.0611
  -8.750  -0.3197   0.04124   0.03416  -0.1396   0.8905   0.0615
  -8.500  -0.3059   0.03811   0.03061  -0.1421   0.8827   0.0621
  -8.250  -0.2892   0.03572   0.02783  -0.1433   0.8741   0.0627
  -8.000  -0.2565   0.03395   0.02595  -0.1458   0.8704   0.0638
  -7.750  -0.2388   0.03289   0.02483  -0.1450   0.8617   0.0648
  -7.500  -0.2134   0.03161   0.02343  -0.1457   0.8553   0.0661
  -7.250  -0.1812   0.03017   0.02180  -0.1475   0.8515   0.0675
  -7.000  -0.1631   0.02921   0.02066  -0.1465   0.8434   0.0684
  -6.750  -0.1376   0.02816   0.01943  -0.1467   0.8371   0.0695
  -6.500  -0.1054   0.02718   0.01847  -0.1479   0.8333   0.0708
  -6.250  -0.0844   0.02655   0.01781  -0.1471   0.8259   0.0722
  -6.000  -0.0594   0.02584   0.01704  -0.1470   0.8193   0.0743
  -5.750  -0.0263   0.02498   0.01604  -0.1481   0.8153   0.0767
  -5.500  -0.0030   0.02443   0.01550  -0.1477   0.8085   0.0786
  -5.250   0.0222   0.02387   0.01490  -0.1474   0.8017   0.0809
  -5.000   0.0560   0.02316   0.01407  -0.1485   0.7975   0.0841
  -4.750   0.0819   0.02267   0.01358  -0.1484   0.7911   0.0878
  -4.500   0.1077   0.02222   0.01308  -0.1482   0.7843   0.0931
  -4.250   0.1421   0.02159   0.01240  -0.1494   0.7798   0.1014
  -4.000   0.1705   0.02112   0.01192  -0.1496   0.7737   0.1122
  -3.750   0.1964   0.02074   0.01160  -0.1493   0.7665   0.1287
  -3.500   0.2309   0.02032   0.01115  -0.1505   0.7617   0.1521
  -3.250   0.2609   0.02011   0.01094  -0.1508   0.7558   0.1713
  -3.000   0.2865   0.02004   0.01084  -0.1503   0.7481   0.1870
  -2.750   0.3208   0.01987   0.01061  -0.1513   0.7427   0.2047
  -2.500   0.3500   0.01982   0.01050  -0.1514   0.7363   0.2188
  -2.250   0.3758   0.01982   0.01042  -0.1508   0.7287   0.2312
  -2.000   0.4093   0.01970   0.01026  -0.1516   0.7230   0.2428
  -1.750   0.4366   0.01969   0.01018  -0.1514   0.7159   0.2547
  -1.500   0.4621   0.01973   0.01020  -0.1508   0.7081   0.2666
  -1.250   0.4950   0.01964   0.01006  -0.1515   0.7023   0.2794
  -1.000   0.5196   0.01972   0.01007  -0.1507   0.6947   0.2925
  -0.750   0.5448   0.01973   0.01012  -0.1501   0.6869   0.3032
  -0.500   0.5775   0.01963   0.00992  -0.1507   0.6811   0.3155
  -0.250   0.5982   0.01973   0.01006  -0.1493   0.6728   0.3250
   0.000   0.6244   0.01974   0.01002  -0.1488   0.6654   0.3361
   0.250   0.6572   0.01965   0.00988  -0.1495   0.6598   0.3481
   0.500   0.6750   0.01981   0.01010  -0.1476   0.6509   0.3584
   0.750   0.7020   0.01982   0.01010  -0.1472   0.6441   0.3709
   1.000   0.7292   0.01984   0.01011  -0.1469   0.6379   0.3833
   1.250   0.7493   0.01999   0.01028  -0.1454   0.6296   0.3962
   1.500   0.7771   0.01998   0.01028  -0.1452   0.6235   0.4098
   1.750   0.8000   0.02009   0.01042  -0.1442   0.6167   0.4237
   2.000   0.8228   0.02023   0.01056  -0.1432   0.6094   0.4392
   2.250   0.8525   0.02021   0.01053  -0.1433   0.6038   0.4564
   2.500   0.8735   0.02039   0.01077  -0.1420   0.5967   0.4727
   2.750   0.8978   0.02049   0.01091  -0.1413   0.5901   0.4924
   3.000   0.9281   0.02047   0.01089  -0.1415   0.5851   0.5167
   3.250   0.9474   0.02066   0.01122  -0.1400   0.5780   0.5421
   3.750   0.9996   0.02059   0.01149  -0.1389   0.5671   0.6524
   4.000   1.0213   0.02034   0.01175  -0.1376   0.5607   1.0000
   4.250   1.0444   0.02066   0.01199  -0.1367   0.5544   1.0000
   4.500   1.0736   0.02086   0.01207  -0.1369   0.5495   1.0000
   4.750   1.0958   0.02124   0.01240  -0.1359   0.5439   1.0000
   5.000   1.1157   0.02165   0.01280  -0.1346   0.5378   1.0000
   5.250   1.1422   0.02192   0.01300  -0.1343   0.5325   1.0000
   5.500   1.1703   0.02221   0.01320  -0.1343   0.5277   1.0000
   5.750   1.1850   0.02275   0.01379  -0.1321   0.5216   1.0000
   6.000   1.2075   0.02313   0.01416  -0.1312   0.5162   1.0000
   6.250   1.2377   0.02336   0.01429  -0.1316   0.5112   1.0000
   6.500   1.2498   0.02389   0.01489  -0.1290   0.5045   1.0000
   6.750   1.2661   0.02430   0.01530  -0.1270   0.4975   1.0000
   7.000   1.2972   0.02446   0.01535  -0.1274   0.4914   1.0000
   7.250   1.3002   0.02512   0.01611  -0.1233   0.4839   1.0000
   7.500   1.3170   0.02552   0.01651  -0.1215   0.4769   1.0000
   7.750   1.3405   0.02580   0.01673  -0.1207   0.4705   1.0000
   8.000   1.3434   0.02654   0.01758  -0.1169   0.4628   1.0000
   8.250   1.3621   0.02688   0.01790  -0.1154   0.4557   1.0000
   8.500   1.3725   0.02750   0.01857  -0.1128   0.4486   1.0000
   8.750   1.3807   0.02822   0.01936  -0.1101   0.4414   1.0000
   9.000   1.4023   0.02854   0.01965  -0.1091   0.4356   1.0000
   9.250   1.4056   0.02952   0.02075  -0.1059   0.4286   1.0000
   9.500   1.4146   0.03030   0.02159  -0.1035   0.4216   1.0000
   9.750   1.4346   0.03067   0.02193  -0.1024   0.4156   1.0000
  10.000   1.4315   0.03205   0.02348  -0.0988   0.4078   1.0000
  10.250   1.4438   0.03275   0.02420  -0.0969   0.4009   1.0000
  10.500   1.4484   0.03391   0.02544  -0.0944   0.3934   1.0000
  10.750   1.4523   0.03512   0.02673  -0.0920   0.3853   1.0000
  11.000   1.4607   0.03612   0.02777  -0.0900   0.3776   1.0000
  11.250   1.4596   0.03778   0.02954  -0.0874   0.3687   1.0000
  11.500   1.4672   0.03892   0.03069  -0.0856   0.3604   1.0000
  11.750   1.4645   0.04083   0.03270  -0.0832   0.3503   1.0000
  12.000   1.4645   0.04267   0.03459  -0.0812   0.3403   1.0000
  12.250   1.4682   0.04417   0.03607  -0.0795   0.3291   1.0000
  12.500   1.4597   0.04697   0.03898  -0.0775   0.3172   1.0000
  12.750   1.4557   0.04945   0.04149  -0.0759   0.3048   1.0000
  13.000   1.4529   0.05191   0.04393  -0.0744   0.2918   1.0000
  13.250   1.4495   0.05452   0.04652  -0.0731   0.2782   1.0000
  13.500   1.4418   0.05781   0.04984  -0.0721   0.2643   1.0000
  13.750   1.4358   0.06104   0.05307  -0.0712   0.2510   1.0000
  14.000   1.4316   0.06417   0.05619  -0.0705   0.2388   1.0000
  14.250   1.4293   0.06713   0.05912  -0.0698   0.2280   1.0000
  14.500   1.4259   0.07037   0.06236  -0.0694   0.2177   1.0000
  14.750   1.4242   0.07348   0.06547  -0.0691   0.2087   1.0000
  15.000   1.4237   0.07642   0.06838  -0.0688   0.2004   1.0000
  15.250   1.4229   0.07956   0.07157  -0.0687   0.1928   1.0000
  15.500   1.4238   0.08242   0.07440  -0.0685   0.1859   1.0000
  15.750   1.4240   0.08550   0.07753  -0.0686   0.1792   1.0000
  16.000   1.4248   0.08848   0.08053  -0.0686   0.1730   1.0000
  16.250   1.4274   0.09120   0.08325  -0.0686   0.1672   1.0000
  16.500   1.4270   0.09449   0.08665  -0.0690   0.1613   1.0000
  16.750   1.4310   0.09700   0.08910  -0.0690   0.1559   1.0000
  17.000   1.4307   0.10035   0.09256  -0.0695   0.1505   1.0000
  17.250   1.4306   0.10362   0.09591  -0.0701   0.1449   1.0000
  17.500   1.4344   0.10620   0.09846  -0.0703   0.1399   1.0000
  17.750   1.4314   0.11008   0.10251  -0.0713   0.1345   1.0000
  18.000   1.4327   0.11314   0.10559  -0.0720   0.1296   1.0000
  18.250   1.4323   0.11656   0.10909  -0.0729   0.1247   1.0000
  18.500   1.4304   0.12028   0.11292  -0.0740   0.1197   1.0000
  18.750   1.4338   0.12293   0.11550  -0.0747   0.1155   1.0000
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