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GOE 502 AIRFOIL (goe502-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 502 AIRFOIL (goe502-il)
Reynolds number: 500,000
Max Cl/Cd: 100.36 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe502-il-500000-n5.txt
Download as CSV file: xf-goe502-il-500000-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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -14.750  -0.5505   0.07311   0.06944  -0.1084   0.9826   0.0327
 -14.500  -0.5596   0.06725   0.06348  -0.1136   0.9781   0.0329
 -14.250  -0.5645   0.06230   0.05845  -0.1181   0.9729   0.0330
 -13.750  -0.5698   0.05332   0.04931  -0.1271   0.9625   0.0333
 -13.500  -0.5664   0.04926   0.04517  -0.1319   0.9577   0.0335
 -13.250  -0.5602   0.04516   0.04097  -0.1375   0.9534   0.0336
 -13.000  -0.5535   0.04139   0.03712  -0.1426   0.9466   0.0338
 -12.750  -0.5372   0.03761   0.03323  -0.1494   0.9420   0.0341
 -12.500  -0.5171   0.03388   0.02937  -0.1569   0.9368   0.0343
 -12.250  -0.4991   0.03043   0.02579  -0.1637   0.9287   0.0347
 -12.000  -0.4809   0.02696   0.02214  -0.1709   0.9202   0.0349
 -11.750  -0.4651   0.02486   0.01987  -0.1742   0.9115   0.0352
 -11.250  -0.4305   0.02248   0.01723  -0.1757   0.8981   0.0358
 -11.000  -0.4111   0.02155   0.01618  -0.1758   0.8915   0.0361
 -10.750  -0.3903   0.02072   0.01522  -0.1760   0.8851   0.0364
 -10.500  -0.3724   0.02001   0.01441  -0.1752   0.8766   0.0367
 -10.250  -0.3501   0.01928   0.01358  -0.1752   0.8685   0.0369
 -10.000  -0.3313   0.01865   0.01291  -0.1743   0.8592   0.0372
  -9.750  -0.3083   0.01808   0.01226  -0.1740   0.8499   0.0375
  -9.500  -0.2871   0.01758   0.01171  -0.1733   0.8386   0.0379
  -9.250  -0.2640   0.01711   0.01116  -0.1728   0.8274   0.0382
  -9.000  -0.2409   0.01666   0.01063  -0.1723   0.8153   0.0386
  -8.750  -0.2173   0.01625   0.01013  -0.1718   0.8035   0.0391
  -8.500  -0.1935   0.01587   0.00964  -0.1713   0.7912   0.0396
  -8.250  -0.1697   0.01551   0.00917  -0.1707   0.7786   0.0402
  -8.000  -0.1454   0.01519   0.00873  -0.1702   0.7677   0.0407
  -7.750  -0.1209   0.01490   0.00832  -0.1697   0.7586   0.0411
  -7.500  -0.0968   0.01448   0.00785  -0.1692   0.7504   0.0416
  -7.250  -0.0722   0.01416   0.00746  -0.1687   0.7424   0.0421
  -7.000  -0.0468   0.01388   0.00713  -0.1684   0.7355   0.0426
  -6.750  -0.0213   0.01362   0.00681  -0.1680   0.7290   0.0432
  -6.500   0.0044   0.01338   0.00650  -0.1676   0.7232   0.0439
  -6.250   0.0306   0.01314   0.00621  -0.1673   0.7182   0.0446
  -6.000   0.0569   0.01292   0.00594  -0.1670   0.7130   0.0453
  -5.750   0.0833   0.01274   0.00569  -0.1667   0.7074   0.0460
  -5.500   0.1090   0.01246   0.00537  -0.1663   0.7020   0.0469
  -5.250   0.1356   0.01224   0.00512  -0.1661   0.6974   0.0478
  -5.000   0.1623   0.01203   0.00490  -0.1658   0.6926   0.0487
  -4.750   0.1888   0.01186   0.00468  -0.1655   0.6873   0.0496
  -4.500   0.2154   0.01173   0.00448  -0.1651   0.6819   0.0506
  -4.250   0.2421   0.01157   0.00429  -0.1648   0.6770   0.0515
  -4.000   0.2687   0.01135   0.00406  -0.1645   0.6718   0.0528
  -3.750   0.2953   0.01120   0.00388  -0.1641   0.6662   0.0543
  -3.500   0.3217   0.01110   0.00372  -0.1637   0.6605   0.0558
  -3.250   0.3485   0.01097   0.00357  -0.1634   0.6547   0.0574
  -3.000   0.3748   0.01083   0.00341  -0.1629   0.6479   0.0595
  -2.750   0.4009   0.01074   0.00328  -0.1624   0.6416   0.0622
  -2.500   0.4272   0.01058   0.00314  -0.1620   0.6349   0.0680
  -2.250   0.4524   0.01031   0.00301  -0.1615   0.6267   0.1076
  -2.000   0.4778   0.01021   0.00295  -0.1609   0.6190   0.1273
  -1.750   0.5037   0.01014   0.00290  -0.1604   0.6104   0.1410
  -1.500   0.5286   0.01012   0.00287  -0.1597   0.6016   0.1534
  -1.250   0.5540   0.01009   0.00285  -0.1590   0.5917   0.1667
  -0.750   0.6034   0.01009   0.00285  -0.1575   0.5730   0.1939
  -0.500   0.6275   0.01014   0.00287  -0.1566   0.5642   0.2052
  -0.250   0.6524   0.01017   0.00290  -0.1559   0.5554   0.2166
   0.000   0.6761   0.01025   0.00295  -0.1549   0.5473   0.2287
   0.250   0.7014   0.01028   0.00300  -0.1543   0.5404   0.2396
   0.500   0.7256   0.01036   0.00306  -0.1534   0.5332   0.2502
   0.750   0.7498   0.01044   0.00314  -0.1525   0.5268   0.2609
   1.000   0.7747   0.01051   0.00320  -0.1518   0.5206   0.2704
   1.250   0.7988   0.01058   0.00329  -0.1509   0.5149   0.2798
   1.500   0.8224   0.01069   0.00337  -0.1499   0.5095   0.2896
   1.750   0.8471   0.01074   0.00346  -0.1492   0.5044   0.3010
   2.000   0.8706   0.01082   0.00355  -0.1482   0.4991   0.3113
   2.250   0.8930   0.01091   0.00365  -0.1470   0.4942   0.3211
   2.500   0.9157   0.01101   0.00375  -0.1459   0.4899   0.3322
   2.750   0.9395   0.01106   0.00386  -0.1450   0.4854   0.3435
   3.000   0.9624   0.01116   0.00397  -0.1439   0.4804   0.3543
   3.250   0.9844   0.01127   0.00411  -0.1427   0.4757   0.3666
   3.500   1.0063   0.01141   0.00425  -0.1414   0.4712   0.3793
   3.750   1.0294   0.01149   0.00440  -0.1404   0.4660   0.3939
   4.000   1.0509   0.01162   0.00456  -0.1391   0.4596   0.4095
   4.250   1.0710   0.01181   0.00474  -0.1376   0.4538   0.4253
   4.500   1.0938   0.01192   0.00491  -0.1365   0.4488   0.4415
   5.000   1.1351   0.01224   0.00530  -0.1337   0.4371   0.4787
   5.500   1.1775   0.01251   0.00570  -0.1312   0.4264   0.5228
   5.750   1.1961   0.01266   0.00595  -0.1295   0.4200   0.5639
   6.250   1.2485   0.01244   0.00653  -0.1292   0.4080   1.0000
   6.500   1.2680   0.01271   0.00678  -0.1277   0.4021   1.0000
   6.750   1.2871   0.01300   0.00705  -0.1262   0.3963   1.0000
   7.000   1.3070   0.01327   0.00731  -0.1248   0.3891   1.0000
   7.250   1.3235   0.01366   0.00765  -0.1229   0.3814   1.0000
   7.500   1.3429   0.01396   0.00796  -0.1215   0.3743   1.0000
   7.750   1.3600   0.01435   0.00832  -0.1198   0.3665   1.0000
   8.000   1.3774   0.01474   0.00870  -0.1182   0.3597   1.0000
   8.250   1.3928   0.01522   0.00915  -0.1163   0.3494   1.0000
   8.500   1.4083   0.01571   0.00961  -0.1144   0.3399   1.0000
   8.750   1.4217   0.01630   0.01016  -0.1123   0.3298   1.0000
   9.000   1.4371   0.01683   0.01068  -0.1106   0.3196   1.0000
   9.250   1.4495   0.01751   0.01132  -0.1085   0.3097   1.0000
   9.500   1.4611   0.01826   0.01203  -0.1063   0.2966   1.0000
   9.750   1.4704   0.01915   0.01285  -0.1040   0.2812   1.0000
  10.000   1.4802   0.02005   0.01371  -0.1018   0.2672   1.0000
  10.250   1.4879   0.02111   0.01471  -0.0994   0.2521   1.0000
  10.500   1.4934   0.02233   0.01586  -0.0969   0.2353   1.0000
  10.750   1.4963   0.02377   0.01721  -0.0943   0.2168   1.0000
  11.000   1.4955   0.02553   0.01885  -0.0915   0.1961   1.0000
  11.250   1.4970   0.02723   0.02049  -0.0891   0.1810   1.0000
  11.500   1.5008   0.02885   0.02207  -0.0871   0.1709   1.0000
  11.750   1.5076   0.03032   0.02355  -0.0854   0.1641   1.0000
  12.000   1.5136   0.03191   0.02513  -0.0838   0.1580   1.0000
  12.250   1.5205   0.03347   0.02671  -0.0824   0.1532   1.0000
  12.500   1.5285   0.03499   0.02827  -0.0811   0.1487   1.0000
  12.750   1.5344   0.03672   0.03001  -0.0798   0.1443   1.0000
  13.000   1.5399   0.03852   0.03184  -0.0785   0.1403   1.0000
  13.250   1.5478   0.04016   0.03352  -0.0775   0.1365   1.0000
  13.500   1.5541   0.04195   0.03535  -0.0764   0.1326   1.0000
  13.750   1.5576   0.04405   0.03748  -0.0753   0.1289   1.0000
  14.000   1.5638   0.04593   0.03940  -0.0744   0.1256   1.0000
  14.250   1.5689   0.04796   0.04147  -0.0735   0.1209   1.0000
  14.500   1.5714   0.05028   0.04382  -0.0726   0.1170   1.0000
  14.750   1.5756   0.05246   0.04604  -0.0719   0.1134   1.0000
  15.000   1.5789   0.05479   0.04842  -0.0712   0.1091   1.0000
  15.250   1.5794   0.05747   0.05111  -0.0705   0.1047   1.0000
  15.500   1.5825   0.05991   0.05360  -0.0700   0.1004   1.0000
  15.750   1.5816   0.06285   0.05657  -0.0696   0.0950   1.0000
  16.000   1.5819   0.06570   0.05945  -0.0692   0.0900   1.0000
  16.250   1.5794   0.06893   0.06269  -0.0689   0.0845   1.0000
  16.500   1.5779   0.07210   0.06589  -0.0687   0.0790   1.0000
  16.750   1.5745   0.07556   0.06937  -0.0687   0.0741   1.0000
  17.000   1.5720   0.07893   0.07277  -0.0687   0.0699   1.0000
  17.250   1.5687   0.08246   0.07634  -0.0688   0.0665   1.0000
  17.500   1.5662   0.08594   0.07987  -0.0690   0.0636   1.0000
  17.750   1.5630   0.08956   0.08351  -0.0694   0.0611   1.0000
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