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GOE 585 AIRFOIL (goe585-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 585 AIRFOIL (goe585-il)
Reynolds number: 100,000
Max Cl/Cd: 51 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe585-il-100000-n5.txt
Download as CSV file: xf-goe585-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 585 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
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.4026   0.09436   0.08925  -0.0305   1.0000   0.0427
  -8.500  -0.3996   0.09120   0.08614  -0.0299   1.0000   0.0420
  -8.250  -0.4025   0.08804   0.08304  -0.0303   1.0000   0.0419
  -8.000  -0.4092   0.08501   0.08010  -0.0305   1.0000   0.0419
  -7.750  -0.4157   0.08162   0.07679  -0.0314   1.0000   0.0421
  -7.500  -0.4198   0.07771   0.07294  -0.0333   1.0000   0.0422
  -7.250  -0.4215   0.07393   0.06920  -0.0346   1.0000   0.0421
  -7.000  -0.4223   0.07004   0.06532  -0.0357   1.0000   0.0419
  -6.750  -0.4219   0.06602   0.06129  -0.0368   1.0000   0.0416
  -6.500  -0.4202   0.06153   0.05675  -0.0381   1.0000   0.0415
  -6.250  -0.4165   0.05640   0.05150  -0.0399   1.0000   0.0417
  -6.000  -0.4105   0.04940   0.04416  -0.0426   1.0000   0.0427
  -5.750  -0.4021   0.04308   0.03732  -0.0440   1.0000   0.0433
  -5.500  -0.3912   0.03898   0.03292  -0.0438   1.0000   0.0437
  -5.250  -0.3654   0.03567   0.02931  -0.0458   0.9965   0.0448
  -5.000  -0.3339   0.03429   0.02782  -0.0479   0.9917   0.0472
  -4.750  -0.3018   0.03109   0.02410  -0.0502   0.9868   0.0491
  -4.500  -0.2706   0.02802   0.02044  -0.0518   0.9818   0.0500
  -4.250  -0.2377   0.02571   0.01759  -0.0533   0.9770   0.0513
  -4.000  -0.2052   0.02410   0.01545  -0.0544   0.9718   0.0539
  -3.750  -0.1726   0.02260   0.01364  -0.0556   0.9666   0.0551
  -3.500  -0.1390   0.02142   0.01231  -0.0569   0.9619   0.0563
  -3.250  -0.1079   0.02052   0.01131  -0.0576   0.9555   0.0579
  -3.000  -0.0722   0.01971   0.01039  -0.0592   0.9510   0.0599
  -2.750  -0.0422   0.01906   0.00963  -0.0595   0.9439   0.0629
  -2.500  -0.0077   0.01846   0.00894  -0.0608   0.9385   0.0672
  -2.250   0.0253   0.01790   0.00841  -0.0619   0.9326   0.0717
  -2.000   0.0574   0.01740   0.00787  -0.0626   0.9255   0.0772
  -1.750   0.0980   0.01676   0.00726  -0.0649   0.9201   0.0891
  -1.500   0.1331   0.01616   0.00673  -0.0659   0.9083   0.1137
  -1.250   0.1689   0.01562   0.00627  -0.0670   0.8958   0.1505
  -1.000   0.2034   0.01503   0.00599  -0.0681   0.8845   0.2170
  -0.750   0.2381   0.01431   0.00580  -0.0694   0.8756   0.3618
  -0.500   0.3059   0.01254   0.00564  -0.0767   0.8701   1.0000
  -0.250   0.3374   0.01248   0.00540  -0.0770   0.8574   1.0000
   0.000   0.3672   0.01244   0.00520  -0.0770   0.8433   1.0000
   0.250   0.3957   0.01242   0.00504  -0.0767   0.8277   1.0000
   0.500   0.4235   0.01241   0.00491  -0.0762   0.8108   1.0000
   0.750   0.4515   0.01240   0.00477  -0.0758   0.7929   1.0000
   1.000   0.4800   0.01239   0.00465  -0.0754   0.7742   1.0000
   1.250   0.5079   0.01241   0.00454  -0.0749   0.7539   1.0000
   1.500   0.5347   0.01247   0.00447  -0.0742   0.7315   1.0000
   1.750   0.5614   0.01256   0.00443  -0.0735   0.7079   1.0000
   2.000   0.5868   0.01268   0.00443  -0.0725   0.6820   1.0000
   2.250   0.6112   0.01284   0.00447  -0.0714   0.6532   1.0000
   2.500   0.6351   0.01303   0.00453  -0.0703   0.6212   1.0000
   2.750   0.6584   0.01326   0.00460  -0.0690   0.5857   1.0000
   3.000   0.6811   0.01353   0.00469  -0.0677   0.5459   1.0000
   3.250   0.7032   0.01387   0.00483  -0.0663   0.5056   1.0000
   3.500   0.7249   0.01428   0.00501  -0.0650   0.4698   1.0000
   3.750   0.7468   0.01471   0.00525  -0.0637   0.4402   1.0000
   4.000   0.7691   0.01514   0.00556  -0.0626   0.4163   1.0000
   4.250   0.7916   0.01558   0.00589  -0.0615   0.3963   1.0000
   4.500   0.8143   0.01603   0.00625  -0.0605   0.3787   1.0000
   4.750   0.8371   0.01647   0.00665  -0.0595   0.3629   1.0000
   5.000   0.8602   0.01690   0.00705  -0.0586   0.3487   1.0000
   5.250   0.8835   0.01734   0.00748  -0.0578   0.3361   1.0000
   5.500   0.9068   0.01778   0.00794  -0.0569   0.3243   1.0000
   5.750   0.9299   0.01826   0.00843  -0.0561   0.3134   1.0000
   6.000   0.9529   0.01874   0.00892  -0.0552   0.3032   1.0000
   6.250   0.9764   0.01921   0.00947  -0.0544   0.2934   1.0000
   6.500   0.9992   0.01972   0.01000  -0.0535   0.2838   1.0000
   6.750   1.0209   0.02020   0.01051  -0.0525   0.2718   1.0000
   7.000   1.0422   0.02063   0.01101  -0.0514   0.2582   1.0000
   7.250   1.0635   0.02108   0.01155  -0.0504   0.2454   1.0000
   7.500   1.0851   0.02157   0.01214  -0.0494   0.2347   1.0000
   7.750   1.1059   0.02209   0.01276  -0.0483   0.2248   1.0000
   8.000   1.1265   0.02261   0.01339  -0.0471   0.2141   1.0000
   8.250   1.1468   0.02314   0.01407  -0.0459   0.2024   1.0000
   8.500   1.1661   0.02369   0.01475  -0.0446   0.1898   1.0000
   8.750   1.1836   0.02426   0.01540  -0.0431   0.1732   1.0000
   9.000   1.1998   0.02488   0.01609  -0.0415   0.1512   1.0000
   9.250   1.2149   0.02567   0.01685  -0.0399   0.1242   1.0000
   9.500   1.2279   0.02672   0.01782  -0.0381   0.1006   1.0000
   9.750   1.2387   0.02801   0.01904  -0.0360   0.0817   1.0000
  10.000   1.2469   0.02949   0.02050  -0.0337   0.0678   1.0000
  10.250   1.2524   0.03101   0.02208  -0.0309   0.0571   1.0000
  10.500   1.2545   0.03267   0.02378  -0.0279   0.0490   1.0000
  10.750   1.2556   0.03438   0.02563  -0.0249   0.0436   1.0000
  11.000   1.2548   0.03626   0.02762  -0.0220   0.0395   1.0000
  11.250   1.2548   0.03815   0.02965  -0.0196   0.0360   1.0000
  11.500   1.2513   0.04038   0.03196  -0.0175   0.0339   1.0000
  11.750   1.2488   0.04271   0.03445  -0.0156   0.0319   1.0000
  12.000   1.2457   0.04523   0.03715  -0.0143   0.0300   1.0000
  12.250   1.2412   0.04806   0.04013  -0.0133   0.0288   1.0000
  12.500   1.2359   0.05119   0.04339  -0.0128   0.0279   1.0000
  12.750   1.2294   0.05465   0.04699  -0.0128   0.0273   1.0000
  13.000   1.2209   0.05857   0.05100  -0.0132   0.0265   1.0000
  13.250   1.2154   0.06239   0.05499  -0.0137   0.0258   1.0000
  13.500   1.2097   0.06645   0.05925  -0.0146   0.0251   1.0000
  13.750   1.2031   0.07080   0.06379  -0.0158   0.0245   1.0000
  14.000   1.1955   0.07553   0.06870  -0.0174   0.0238   1.0000
  14.250   1.1876   0.08043   0.07378  -0.0193   0.0233   1.0000
  14.500   1.1782   0.08584   0.07935  -0.0217   0.0227   1.0000
  14.750   1.1692   0.09137   0.08503  -0.0243   0.0223   1.0000
  15.000   1.1600   0.09705   0.09090  -0.0269   0.0220   1.0000
  15.250   1.1499   0.10311   0.09710  -0.0299   0.0216   1.0000
  15.500   1.1398   0.10936   0.10351  -0.0331   0.0215   1.0000
  15.750   1.1285   0.11602   0.11032  -0.0366   0.0214   1.0000
  16.000   1.1157   0.12332   0.11778  -0.0406   0.0213   1.0000
  16.250   1.0997   0.13172   0.12632  -0.0455   0.0213   1.0000
  16.500   1.0767   0.14250   0.13730  -0.0519   0.0215   1.0000
  16.750   1.0279   0.16253   0.15757  -0.0636   0.0227   1.0000
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