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GOE 497 AIRFOIL (goe497-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 497 AIRFOIL (goe497-il)
Reynolds number: 200,000
Max Cl/Cd: 84.99 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe497-il-200000.txt
Download as CSV file: xf-goe497-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 497 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.2576   0.09323   0.08973  -0.0595   0.9806   0.0926
  -8.500  -0.4011   0.04270   0.03862  -0.1149   0.9500   0.0638
  -8.250  -0.3852   0.03416   0.02916  -0.1248   0.9430   0.0648
  -8.000  -0.3512   0.03036   0.02465  -0.1301   0.9404   0.0669
  -7.750  -0.3341   0.02806   0.02203  -0.1301   0.9326   0.0684
  -7.500  -0.3007   0.02673   0.02066  -0.1320   0.9290   0.0705
  -7.250  -0.2632   0.02538   0.01911  -0.1346   0.9265   0.0729
  -7.000  -0.2229   0.02410   0.01753  -0.1376   0.9248   0.0762
  -6.750  -0.2018   0.02302   0.01620  -0.1369   0.9173   0.0784
  -6.500  -0.1681   0.02196   0.01514  -0.1384   0.9138   0.0813
  -6.250  -0.1295   0.02118   0.01425  -0.1407   0.9115   0.0854
  -6.000  -0.0902   0.02021   0.01307  -0.1430   0.9095   0.0903
  -5.750  -0.0502   0.01937   0.01227  -0.1454   0.9078   0.0957
  -5.500  -0.0300   0.01902   0.01179  -0.1439   0.8985   0.1006
  -5.250   0.0071   0.01813   0.01093  -0.1457   0.8951   0.1083
  -5.000   0.0459   0.01735   0.01008  -0.1476   0.8925   0.1181
  -4.750   0.0707   0.01702   0.00976  -0.1470   0.8851   0.1276
  -4.500   0.1024   0.01647   0.00923  -0.1476   0.8799   0.1402
  -4.250   0.1385   0.01593   0.00869  -0.1490   0.8765   0.1548
  -4.000   0.1657   0.01564   0.00841  -0.1487   0.8698   0.1681
  -3.750   0.1952   0.01534   0.00811  -0.1489   0.8637   0.1823
  -3.500   0.2292   0.01497   0.00775  -0.1497   0.8598   0.1983
  -3.250   0.2555   0.01480   0.00758  -0.1493   0.8524   0.2137
  -3.000   0.2854   0.01454   0.00734  -0.1493   0.8460   0.2315
  -2.750   0.3190   0.01427   0.00707  -0.1501   0.8419   0.2528
  -2.500   0.3428   0.01426   0.00709  -0.1492   0.8336   0.2723
  -2.250   0.3731   0.01411   0.00692  -0.1493   0.8282   0.2936
  -2.000   0.4041   0.01395   0.00677  -0.1496   0.8235   0.3125
  -1.750   0.4285   0.01395   0.00680  -0.1489   0.8155   0.3294
  -1.500   0.4591   0.01380   0.00665  -0.1491   0.8104   0.3469
  -1.250   0.4864   0.01377   0.00662  -0.1487   0.8038   0.3629
  -1.000   0.5136   0.01368   0.00658  -0.1483   0.7967   0.3787
  -0.750   0.5454   0.01353   0.00641  -0.1487   0.7918   0.3961
  -0.500   0.5692   0.01355   0.00649  -0.1478   0.7832   0.4115
  -0.250   0.5991   0.01343   0.00638  -0.1478   0.7772   0.4285
   0.000   0.6257   0.01342   0.00640  -0.1474   0.7700   0.4461
   0.250   0.6534   0.01335   0.00635  -0.1470   0.7625   0.4668
   0.500   0.6812   0.01324   0.00630  -0.1467   0.7548   0.4874
   0.750   0.7079   0.01311   0.00622  -0.1462   0.7458   0.5079
   1.000   0.7349   0.01300   0.00616  -0.1457   0.7371   0.5299
   1.250   0.7624   0.01284   0.00605  -0.1453   0.7280   0.5539
   1.500   0.7878   0.01273   0.00605  -0.1445   0.7183   0.5811
   1.750   0.8159   0.01255   0.00595  -0.1442   0.7099   0.6165
   2.000   0.8388   0.01238   0.00602  -0.1430   0.6993   0.6689
   2.250   0.8661   0.01171   0.00590  -0.1420   0.6897   1.0000
   2.500   0.8938   0.01178   0.00583  -0.1417   0.6780   1.0000
   2.750   0.9195   0.01189   0.00586  -0.1411   0.6654   1.0000
   3.000   0.9459   0.01201   0.00589  -0.1406   0.6531   1.0000
   3.250   0.9726   0.01214   0.00591  -0.1402   0.6408   1.0000
   3.500   0.9985   0.01229   0.00598  -0.1396   0.6279   1.0000
   3.750   1.0230   0.01248   0.00614  -0.1388   0.6148   1.0000
   4.000   1.0482   0.01268   0.00629  -0.1381   0.6022   1.0000
   4.250   1.0738   0.01290   0.00643  -0.1376   0.5904   1.0000
   4.500   1.0988   0.01311   0.00660  -0.1369   0.5784   1.0000
   4.750   1.1226   0.01334   0.00682  -0.1360   0.5659   1.0000
   5.000   1.1469   0.01358   0.00702  -0.1352   0.5541   1.0000
   5.250   1.1716   0.01383   0.00721  -0.1345   0.5429   1.0000
   5.500   1.1948   0.01407   0.00745  -0.1336   0.5306   1.0000
   5.750   1.2171   0.01432   0.00768  -0.1324   0.5171   1.0000
   6.000   1.2386   0.01459   0.00791  -0.1311   0.5023   1.0000
   6.250   1.2597   0.01489   0.00816  -0.1298   0.4877   1.0000
   6.500   1.2808   0.01524   0.00845  -0.1285   0.4739   1.0000
   6.750   1.3015   0.01563   0.00878  -0.1272   0.4603   1.0000
   7.000   1.3221   0.01606   0.00913  -0.1259   0.4468   1.0000
   7.250   1.3408   0.01646   0.00954  -0.1242   0.4324   1.0000
   7.500   1.3591   0.01688   0.00996  -0.1225   0.4184   1.0000
   7.750   1.3768   0.01731   0.01041  -0.1207   0.4046   1.0000
   8.000   1.3935   0.01776   0.01086  -0.1188   0.3908   1.0000
   8.250   1.4084   0.01821   0.01131  -0.1165   0.3766   1.0000
   8.500   1.4203   0.01866   0.01175  -0.1137   0.3620   1.0000
   8.750   1.4311   0.01914   0.01225  -0.1108   0.3470   1.0000
   9.000   1.4414   0.01967   0.01280  -0.1079   0.3315   1.0000
   9.250   1.4512   0.02028   0.01340  -0.1051   0.3156   1.0000
   9.500   1.4600   0.02099   0.01410  -0.1023   0.2995   1.0000
   9.750   1.4676   0.02183   0.01490  -0.0994   0.2836   1.0000
  10.000   1.4740   0.02281   0.01583  -0.0966   0.2680   1.0000
  10.250   1.4796   0.02392   0.01689  -0.0938   0.2526   1.0000
  10.500   1.4843   0.02515   0.01808  -0.0910   0.2367   1.0000
  10.750   1.4879   0.02651   0.01941  -0.0883   0.2192   1.0000
  11.000   1.4902   0.02801   0.02089  -0.0857   0.1994   1.0000
  11.250   1.4905   0.02973   0.02255  -0.0831   0.1784   1.0000
  11.500   1.4918   0.03152   0.02426  -0.0808   0.1573   1.0000
  11.750   1.4918   0.03350   0.02616  -0.0786   0.1423   1.0000
  12.000   1.4913   0.03563   0.02823  -0.0766   0.1320   1.0000
  12.250   1.4910   0.03785   0.03040  -0.0747   0.1239   1.0000
  12.500   1.4934   0.03992   0.03251  -0.0732   0.1173   1.0000
  12.750   1.4944   0.04219   0.03479  -0.0717   0.1119   1.0000
  13.000   1.4951   0.04456   0.03717  -0.0703   0.1072   1.0000
  13.250   1.5002   0.04659   0.03932  -0.0693   0.1026   1.0000
  13.500   1.5014   0.04904   0.04178  -0.0683   0.0984   1.0000
  13.750   1.5039   0.05144   0.04422  -0.0673   0.0945   1.0000
  14.000   1.5084   0.05371   0.04662  -0.0667   0.0904   1.0000
  14.250   1.5100   0.05632   0.04928  -0.0661   0.0865   1.0000
  14.500   1.5115   0.05901   0.05201  -0.0655   0.0827   1.0000
  14.750   1.5141   0.06170   0.05486  -0.0652   0.0786   1.0000
  15.000   1.5135   0.06480   0.05799  -0.0651   0.0747   1.0000
  15.250   1.5129   0.06798   0.06127  -0.0650   0.0705   1.0000
  15.500   1.5113   0.07145   0.06486  -0.0653   0.0661   1.0000
  15.750   1.5070   0.07527   0.06867  -0.0655   0.0619   1.0000
  16.000   1.5037   0.07922   0.07279  -0.0662   0.0573   1.0000
  16.250   1.4983   0.08332   0.07683  -0.0668   0.0536   1.0000
  16.500   1.4948   0.08752   0.08124  -0.0677   0.0498   1.0000
  16.750   1.4910   0.09169   0.08544  -0.0687   0.0472   1.0000
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