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GOE 610 B AIRFOIL (goe610b-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 610 B AIRFOIL (goe610b-il)
Reynolds number: 500,000
Max Cl/Cd: 118.04 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe610b-il-500000.txt
Download as CSV file: xf-goe610b-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 610 B 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.3116   0.11170   0.10939  -0.0346   1.0000   0.0199
  -9.750  -0.3113   0.10893   0.10665  -0.0357   1.0000   0.0200
  -9.500  -0.3112   0.10629   0.10405  -0.0366   1.0000   0.0200
  -9.250  -0.3032   0.10192   0.09970  -0.0350   1.0000   0.0203
  -9.000  -0.2984   0.09940   0.09720  -0.0343   1.0000   0.0205
  -8.750  -0.2959   0.09715   0.09498  -0.0338   1.0000   0.0208
  -8.500  -0.2957   0.09510   0.09297  -0.0330   1.0000   0.0211
  -8.250  -0.2870   0.09224   0.09013  -0.0349   0.9987   0.0215
  -8.000  -0.2677   0.08836   0.08625  -0.0399   0.9931   0.0224
  -7.500  -0.2264   0.07868   0.07656  -0.0600   0.9673   0.0248
  -7.250  -0.1964   0.07305   0.07088  -0.0702   0.9581   0.0249
  -7.000  -0.1786   0.06823   0.06605  -0.0725   0.9503   0.0254
  -6.750  -0.1504   0.06510   0.06288  -0.0767   0.9421   0.0261
  -6.500  -0.1205   0.06172   0.05942  -0.0826   0.9287   0.0277
  -6.250  -0.0827   0.05594   0.05343  -0.0956   0.9066   0.0306
  -5.250  -0.0156   0.04334   0.04039  -0.1010   0.8581   0.0329
  -5.000   0.0054   0.04104   0.03796  -0.1020   0.8492   0.0351
  -4.750   0.0273   0.02137   0.01808  -0.0958   0.8204   0.0379
  -4.500   0.0514   0.03092   0.02714  -0.1051   0.8325   0.0388
  -4.250   0.0711   0.03016   0.02637  -0.1047   0.8245   0.0398
  -4.000   0.0926   0.02907   0.02521  -0.1044   0.8165   0.0412
  -3.750   0.1227   0.02776   0.02349  -0.1040   0.8089   0.0469
  -3.500   0.1387   0.02277   0.01808  -0.1031   0.8009   0.0482
  -3.250   0.1612   0.02173   0.01701  -0.1028   0.7929   0.0493
  -3.000   0.1844   0.02085   0.01606  -0.1023   0.7834   0.0509
  -2.750   0.2088   0.01982   0.01485  -0.1016   0.7745   0.0545
  -2.500   0.2321   0.01798   0.01265  -0.1007   0.7646   0.0601
  -2.250   0.2561   0.01724   0.01185  -0.1001   0.7525   0.0620
  -2.000   0.2805   0.01653   0.01098  -0.0994   0.7377   0.0654
  -1.750   0.3042   0.01567   0.00989  -0.0985   0.7199   0.0732
  -1.500   0.3284   0.01532   0.00944  -0.0978   0.6998   0.0776
  -1.250   0.3538   0.01326   0.00689  -0.0964   0.6825   0.0659
  -1.000   0.3781   0.01333   0.00691  -0.0959   0.6659   0.0766
  -0.500   0.4309   0.01134   0.00429  -0.0940   0.6420   0.0583
  -0.250   0.4565   0.01088   0.00373  -0.0934   0.6314   0.0584
   0.000   0.4821   0.01042   0.00320  -0.0929   0.6230   0.0590
   0.250   0.5075   0.01014   0.00286  -0.0923   0.6155   0.0596
   0.500   0.5331   0.00989   0.00260  -0.0918   0.6076   0.0605
   0.750   0.5584   0.00976   0.00242  -0.0912   0.6004   0.0616
   1.000   0.5843   0.00963   0.00230  -0.0908   0.5938   0.0637
   1.250   0.6100   0.00956   0.00221  -0.0903   0.5874   0.0654
   1.500   0.6360   0.00950   0.00214  -0.0898   0.5815   0.0669
   1.750   0.6622   0.00946   0.00210  -0.0894   0.5756   0.0685
   2.250   0.7144   0.00944   0.00208  -0.0886   0.5642   0.0734
   2.500   0.7405   0.00945   0.00212  -0.0882   0.5588   0.0800
   2.750   0.7662   0.00946   0.00222  -0.0877   0.5536   0.1180
   3.000   0.8483   0.00787   0.00252  -0.1006   0.5441   1.0000
   3.250   0.8729   0.00799   0.00261  -0.0998   0.5378   1.0000
   3.500   0.8976   0.00808   0.00269  -0.0992   0.5300   1.0000
   3.750   0.9219   0.00821   0.00278  -0.0984   0.5220   1.0000
   4.000   0.9461   0.00832   0.00288  -0.0976   0.5123   1.0000
   4.250   0.9705   0.00842   0.00300  -0.0969   0.5039   1.0000
   4.500   0.9942   0.00856   0.00312  -0.0960   0.4940   1.0000
   4.750   1.0180   0.00867   0.00324  -0.0952   0.4811   1.0000
   5.000   1.0411   0.00882   0.00336  -0.0942   0.4612   1.0000
   5.250   1.0618   0.00907   0.00351  -0.0928   0.4216   1.0000
   5.500   1.0748   0.00983   0.00386  -0.0901   0.3481   1.0000
   5.750   1.0918   0.01042   0.00427  -0.0882   0.3172   1.0000
   6.000   1.1110   0.01087   0.00462  -0.0866   0.2962   1.0000
   6.250   1.1309   0.01126   0.00496  -0.0852   0.2787   1.0000
   6.500   1.1516   0.01160   0.00527  -0.0840   0.2637   1.0000
   6.750   1.1712   0.01200   0.00559  -0.0825   0.2434   1.0000
   7.000   1.1900   0.01244   0.00593  -0.0810   0.2175   1.0000
   7.250   1.2057   0.01307   0.00635  -0.0790   0.1721   1.0000
   7.500   1.2153   0.01407   0.00705  -0.0760   0.1271   1.0000
   7.750   1.2311   0.01465   0.00761  -0.0740   0.1152   1.0000
   8.000   1.2472   0.01519   0.00814  -0.0721   0.1041   1.0000
   8.500   1.2636   0.01710   0.00964  -0.0657   0.0364   1.0000
   8.750   1.2710   0.01792   0.01044  -0.0622   0.0281   1.0000
   9.000   1.2809   0.01863   0.01118  -0.0592   0.0248   1.0000
   9.250   1.2871   0.01960   0.01219  -0.0558   0.0221   1.0000
   9.500   1.2977   0.02035   0.01303  -0.0533   0.0211   1.0000
   9.750   1.3072   0.02120   0.01396  -0.0507   0.0198   1.0000
  10.000   1.3152   0.02219   0.01502  -0.0482   0.0189   1.0000
  10.250   1.3212   0.02335   0.01624  -0.0456   0.0179   1.0000
  10.500   1.3219   0.02496   0.01794  -0.0426   0.0171   1.0000
  10.750   1.3162   0.02717   0.02027  -0.0393   0.0164   1.0000
  11.000   1.3273   0.02820   0.02139  -0.0378   0.0160   1.0000
  11.250   1.3353   0.02952   0.02279  -0.0362   0.0154   1.0000
  11.500   1.3399   0.03118   0.02455  -0.0344   0.0150   1.0000
  11.750   1.3450   0.03284   0.02629  -0.0328   0.0144   1.0000
  12.000   1.3482   0.03474   0.02827  -0.0312   0.0139   1.0000
  12.250   1.3519   0.03665   0.03025  -0.0298   0.0136   1.0000
  12.500   1.3551   0.03863   0.03232  -0.0285   0.0132   1.0000
  12.750   1.3566   0.04086   0.03462  -0.0271   0.0129   1.0000
  13.000   1.3571   0.04327   0.03710  -0.0256   0.0127   1.0000
  13.250   1.3563   0.04618   0.04011  -0.0233   0.0122   1.0000
  13.500   1.3614   0.04828   0.04233  -0.0223   0.0121   1.0000
  13.750   1.3651   0.05048   0.04468  -0.0215   0.0120   1.0000
  14.000   1.3676   0.05284   0.04717  -0.0209   0.0117   1.0000
  14.250   1.3695   0.05536   0.04984  -0.0203   0.0115   1.0000
  14.500   1.3699   0.05812   0.05274  -0.0198   0.0113   1.0000
  14.750   1.3694   0.06107   0.05586  -0.0195   0.0110   1.0000
  15.000   1.3683   0.06409   0.05900  -0.0196   0.0106   1.0000
  15.250   1.3655   0.06750   0.06256  -0.0196   0.0105   1.0000
  15.500   1.3605   0.07134   0.06657  -0.0197   0.0104   1.0000
  15.750   1.3553   0.07528   0.07066  -0.0202   0.0103   1.0000
  16.000   1.3479   0.07965   0.07519  -0.0210   0.0102   1.0000
  16.250   1.3395   0.08428   0.07998  -0.0222   0.0101   1.0000
  16.500   1.3311   0.08904   0.08489  -0.0236   0.0100   1.0000
  16.750   1.3183   0.09476   0.09080  -0.0255   0.0100   1.0000
  17.000   1.3092   0.09993   0.09609  -0.0275   0.0099   1.0000
  17.250   1.2904   0.10721   0.10360  -0.0307   0.0100   1.0000
  17.500   1.2694   0.11535   0.11197  -0.0348   0.0101   1.0000
  17.750   1.2557   0.12232   0.11908  -0.0385   0.0100   1.0000
  18.000   1.2332   0.13168   0.12866  -0.0440   0.0101   1.0000
  18.250   1.1998   0.14445   0.14170  -0.0518   0.0105   1.0000
  18.500   1.1759   0.15548   0.15291  -0.0587   0.0106   1.0000
  18.750   1.1447   0.16947   0.16708  -0.0676   0.0110   1.0000
  19.000   1.0979   0.19081   0.18855  -0.0802   0.0117   1.0000
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