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GOE 655 AIRFOIL (goe655-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 655 AIRFOIL (goe655-il)
Reynolds number: 100,000
Max Cl/Cd: 45.64 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe655-il-100000.txt
Download as CSV file: xf-goe655-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 655 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
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3152   0.10081   0.09630  -0.0325   1.0000   0.1449
  -8.500  -0.3682   0.10118   0.09689  -0.0316   1.0000   0.1462
  -8.250  -0.4118   0.10111   0.09699  -0.0288   1.0000   0.1465
  -8.000  -0.3343   0.09478   0.09052  -0.0252   1.0000   0.1528
  -7.750  -0.3494   0.09374   0.08959  -0.0223   1.0000   0.1560
  -7.500  -0.3774   0.09312   0.08908  -0.0193   1.0000   0.1585
  -7.250  -0.4166   0.09286   0.08897  -0.0160   1.0000   0.1600
  -7.000  -0.4288   0.08820   0.08434  -0.0231   0.9941   0.1641
  -6.750  -0.3930   0.08565   0.08177  -0.0216   0.9896   0.1699
  -6.500  -0.3835   0.07917   0.07524  -0.0346   0.9765   0.1807
  -6.250  -0.3502   0.07621   0.07226  -0.0359   0.9709   0.1865
  -6.000  -0.3676   0.05122   0.04608  -0.0623   0.9552   0.1190
  -5.750  -0.3571   0.04244   0.03605  -0.0644   0.9443   0.1020
  -5.500  -0.3243   0.03868   0.03192  -0.0669   0.9380   0.1006
  -5.250  -0.2974   0.03584   0.02864  -0.0676   0.9284   0.1002
  -5.000  -0.2616   0.03367   0.02585  -0.0694   0.9209   0.1021
  -4.750  -0.2266   0.03141   0.02320  -0.0709   0.9113   0.1035
  -4.500  -0.1889   0.02955   0.02119  -0.0726   0.9018   0.1058
  -4.250  -0.1426   0.02807   0.01957  -0.0754   0.8935   0.1110
  -4.000  -0.1083   0.02696   0.01817  -0.0761   0.8828   0.1156
  -3.750  -0.0604   0.02532   0.01657  -0.0792   0.8770   0.1220
  -3.500  -0.0276   0.02454   0.01566  -0.0795   0.8667   0.1308
  -3.250   0.0196   0.02323   0.01445  -0.0824   0.8610   0.1459
  -3.000   0.0512   0.02226   0.01368  -0.0826   0.8511   0.1663
  -2.750   0.0908   0.02090   0.01271  -0.0841   0.8442   0.2304
  -2.500   0.1163   0.02011   0.01237  -0.0832   0.8329   0.3315
  -2.250   0.1572   0.01929   0.01178  -0.0847   0.8263   0.4105
  -2.000   0.1826   0.01888   0.01151  -0.0836   0.8135   0.4661
  -1.750   0.2131   0.01826   0.01111  -0.0831   0.8028   0.5297
  -1.500   0.2480   0.01738   0.01060  -0.0831   0.7937   0.6252
  -1.250   0.2743   0.01671   0.01047  -0.0811   0.7807   0.7596
  -1.000   0.3932   0.01595   0.00978  -0.0960   0.7689   0.9625
  -0.750   0.4663   0.01561   0.00907  -0.1045   0.7527   1.0000
  -0.500   0.4871   0.01556   0.00878  -0.1031   0.7361   1.0000
  -0.250   0.5089   0.01558   0.00858  -0.1017   0.7192   1.0000
   0.000   0.5310   0.01566   0.00844  -0.1003   0.7021   1.0000
   0.250   0.5529   0.01577   0.00835  -0.0988   0.6846   1.0000
   0.500   0.5748   0.01591   0.00830  -0.0974   0.6670   1.0000
   0.750   0.5966   0.01607   0.00826  -0.0959   0.6495   1.0000
   1.000   0.6186   0.01624   0.00825  -0.0945   0.6325   1.0000
   1.250   0.6407   0.01644   0.00828  -0.0932   0.6163   1.0000
   1.500   0.6632   0.01668   0.00835  -0.0919   0.6012   1.0000
   1.750   0.6865   0.01694   0.00844  -0.0908   0.5876   1.0000
   2.000   0.7118   0.01720   0.00850  -0.0901   0.5755   1.0000
   2.250   0.7328   0.01754   0.00876  -0.0887   0.5623   1.0000
   2.500   0.7549   0.01791   0.00903  -0.0876   0.5507   1.0000
   2.750   0.7801   0.01824   0.00920  -0.0869   0.5407   1.0000
   3.000   0.8022   0.01862   0.00951  -0.0858   0.5300   1.0000
   3.250   0.8249   0.01902   0.00984  -0.0848   0.5203   1.0000
   3.500   0.8504   0.01934   0.01001  -0.0842   0.5109   1.0000
   3.750   0.8705   0.01975   0.01042  -0.0828   0.5006   1.0000
   4.000   0.8969   0.02010   0.01060  -0.0824   0.4922   1.0000
   4.250   0.9166   0.02052   0.01106  -0.0809   0.4827   1.0000
   4.500   0.9424   0.02090   0.01133  -0.0805   0.4750   1.0000
   4.750   0.9625   0.02136   0.01184  -0.0791   0.4665   1.0000
   5.000   0.9906   0.02177   0.01209  -0.0791   0.4600   1.0000
   5.250   1.0082   0.02229   0.01275  -0.0774   0.4518   1.0000
   5.500   1.0351   0.02268   0.01302  -0.0772   0.4450   1.0000
   5.750   1.0540   0.02326   0.01370  -0.0757   0.4376   1.0000
   6.000   1.0779   0.02370   0.01413  -0.0751   0.4306   1.0000
   6.250   1.1002   0.02426   0.01470  -0.0742   0.4237   1.0000
   6.500   1.1208   0.02474   0.01523  -0.0730   0.4158   1.0000
   6.750   1.1452   0.02524   0.01569  -0.0724   0.4085   1.0000
   7.000   1.1634   0.02575   0.01629  -0.0709   0.4000   1.0000
   7.250   1.1879   0.02624   0.01672  -0.0703   0.3923   1.0000
   7.500   1.2052   0.02679   0.01738  -0.0687   0.3834   1.0000
   7.750   1.2283   0.02736   0.01792  -0.0679   0.3754   1.0000
   8.000   1.2461   0.02793   0.01856  -0.0664   0.3663   1.0000
   8.250   1.2657   0.02862   0.01928  -0.0651   0.3576   1.0000
   8.500   1.2871   0.02914   0.01979  -0.0641   0.3484   1.0000
   8.750   1.3009   0.02998   0.02075  -0.0621   0.3391   1.0000
   9.000   1.3279   0.03047   0.02111  -0.0620   0.3307   1.0000
   9.250   1.3354   0.03150   0.02236  -0.0591   0.3219   1.0000
   9.500   1.3629   0.03209   0.02284  -0.0591   0.3147   1.0000
   9.750   1.3695   0.03332   0.02431  -0.0562   0.3075   1.0000
  10.000   1.3880   0.03414   0.02518  -0.0551   0.3011   1.0000
  10.250   1.4107   0.03513   0.02617  -0.0546   0.2957   1.0000
  10.500   1.4122   0.03648   0.02779  -0.0512   0.2899   1.0000
  10.750   1.4320   0.03726   0.02860  -0.0502   0.2849   1.0000
  11.000   1.4549   0.03828   0.02964  -0.0499   0.2804   1.0000
  11.250   1.4482   0.04006   0.03174  -0.0457   0.2764   1.0000
  11.500   1.4529   0.04152   0.03337  -0.0430   0.2724   1.0000
  11.750   1.4769   0.04223   0.03409  -0.0428   0.2685   1.0000
  12.000   1.4875   0.04347   0.03542  -0.0409   0.2646   1.0000
  12.250   1.4630   0.04579   0.03803  -0.0350   0.2618   1.0000
  12.500   1.4505   0.04769   0.04011  -0.0309   0.2581   1.0000
  12.750   1.5105   0.04566   0.03783  -0.0338   0.2504   1.0000
  13.000   1.4777   0.04867   0.04116  -0.0281   0.2483   1.0000
  13.250   1.4406   0.05273   0.04550  -0.0235   0.2467   1.0000
  13.500   1.3528   0.06252   0.05564  -0.0196   0.2480   1.0000
  13.750   1.4990   0.05147   0.04416  -0.0229   0.2353   1.0000
  14.000   1.4510   0.05680   0.04981  -0.0191   0.2343   1.0000
  14.250   1.3690   0.06722   0.06056  -0.0173   0.2354   1.0000
  14.750   1.4743   0.06007   0.05329  -0.0161   0.2214   1.0000
  15.000   1.4027   0.06991   0.06342  -0.0155   0.2219   1.0000
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