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GOE 499 AIRFOIL (goe499-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 499 AIRFOIL (goe499-il)
Reynolds number: 500,000
Max Cl/Cd: 149.41 at α=2.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe499-il-500000.txt
Download as CSV file: xf-goe499-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 499 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
  ------ -------- --------- --------- -------- -------- --------
 -12.000  -0.3395   0.14044   0.13810  -0.0350   1.0000   0.0154
 -11.750  -0.3410   0.13849   0.13618  -0.0343   1.0000   0.0156
 -11.500  -0.3466   0.13699   0.13471  -0.0334   1.0000   0.0158
 -11.250  -0.3454   0.13447   0.13222  -0.0343   0.9996   0.0158
 -11.000  -0.3341   0.13064   0.12839  -0.0386   0.9982   0.0159
 -10.750  -0.3216   0.12663   0.12438  -0.0424   0.9968   0.0160
 -10.500  -0.3088   0.12092   0.11866  -0.0431   0.9959   0.0164
 -10.250  -0.2938   0.11736   0.11509  -0.0457   0.9947   0.0167
 -10.000  -0.2801   0.11399   0.11171  -0.0483   0.9930   0.0171
  -9.750  -0.2662   0.11055   0.10827  -0.0513   0.9908   0.0178
  -9.500  -0.2518   0.10704   0.10475  -0.0546   0.9887   0.0187
  -9.250  -0.2368   0.10334   0.10104  -0.0584   0.9868   0.0193
  -9.000  -0.2199   0.09960   0.09729  -0.0651   0.9846   0.0212
  -8.500  -0.0921   0.07038   0.06815  -0.0856   0.9716   0.0226
  -8.250  -0.0744   0.06707   0.06484  -0.0877   0.9708   0.0234
  -8.000  -0.0618   0.06390   0.06166  -0.0898   0.9673   0.0243
  -7.750  -0.0493   0.06047   0.05822  -0.0925   0.9635   0.0256
  -7.500  -0.0354   0.05657   0.05431  -0.0969   0.9602   0.0283
  -7.250  -0.0200   0.05305   0.05077  -0.1034   0.9556   0.0297
  -7.000  -0.0129   0.04991   0.04761  -0.1057   0.9474   0.0299
  -6.750   0.0020   0.04554   0.04322  -0.1106   0.9428   0.0300
  -6.500   0.0104   0.04176   0.03942  -0.1138   0.9348   0.0300
  -6.250   0.0143   0.03481   0.03245  -0.1185   0.9291   0.0315
  -6.000   0.0274   0.03295   0.03057  -0.1191   0.9223   0.0325
  -5.750   0.0457   0.03050   0.02808  -0.1217   0.9171   0.0340
  -5.500   0.0660   0.02744   0.02498  -0.1262   0.9117   0.0371
  -5.250   0.1157   0.01359   0.01070  -0.1542   0.9066   0.0428
  -5.000   0.1382   0.01276   0.00986  -0.1543   0.9026   0.0442
  -4.750   0.1643   0.01143   0.00843  -0.1563   0.8988   0.0464
  -4.500   0.2044   0.00711   0.00347  -0.1654   0.8953   0.0565
  -4.250   0.2287   0.00677   0.00318  -0.1653   0.8913   0.0590
  -4.000   0.2851   0.01472   0.00968  -0.1798   0.8996   0.0427
  -3.750   0.3122   0.01443   0.00929  -0.1796   0.8948   0.0418
  -3.250   0.3704   0.01225   0.00674  -0.1804   0.8875   0.0409
  -3.000   0.3983   0.01129   0.00563  -0.1805   0.8834   0.0406
  -2.750   0.4262   0.01067   0.00492  -0.1805   0.8791   0.0407
  -2.500   0.4548   0.01021   0.00436  -0.1806   0.8752   0.0411
  -2.250   0.4831   0.00984   0.00392  -0.1806   0.8712   0.0415
  -2.000   0.5105   0.00934   0.00337  -0.1805   0.8659   0.0422
  -1.750   0.5389   0.00899   0.00297  -0.1806   0.8615   0.0430
  -1.500   0.5678   0.00876   0.00268  -0.1807   0.8583   0.0440
  -1.250   0.5951   0.00859   0.00250  -0.1806   0.8538   0.0463
  -1.000   0.6231   0.00845   0.00234  -0.1805   0.8496   0.0483
  -0.750   0.6515   0.00834   0.00219  -0.1805   0.8458   0.0513
  -0.500   0.6794   0.00813   0.00212  -0.1805   0.8415   0.0954
  -0.250   0.7070   0.00788   0.00215  -0.1806   0.8364   0.1902
   0.000   0.7350   0.00779   0.00214  -0.1805   0.8316   0.2327
   0.250   0.7619   0.00771   0.00216  -0.1803   0.8252   0.2698
   0.500   0.7892   0.00762   0.00215  -0.1801   0.8188   0.3042
   0.750   0.8166   0.00747   0.00220  -0.1801   0.8130   0.3740
   1.000   0.8433   0.00726   0.00234  -0.1799   0.8062   0.5198
   1.250   0.8698   0.00706   0.00242  -0.1795   0.7993   0.6329
   1.500   0.8931   0.00643   0.00241  -0.1783   0.7905   1.0000
   1.750   0.9197   0.00647   0.00242  -0.1779   0.7805   1.0000
   2.000   0.9458   0.00650   0.00241  -0.1773   0.7662   1.0000
   2.250   0.9708   0.00656   0.00237  -0.1764   0.7441   1.0000
   2.500   0.9951   0.00666   0.00239  -0.1755   0.7137   1.0000
   2.750   1.0180   0.00688   0.00244  -0.1743   0.6723   1.0000
   3.000   1.0348   0.00752   0.00263  -0.1719   0.5898   1.0000
   3.250   1.0511   0.00833   0.00301  -0.1696   0.5161   1.0000
   3.500   1.0691   0.00907   0.00340  -0.1678   0.4543   1.0000
   3.750   1.0847   0.01004   0.00388  -0.1656   0.3610   1.0000
   4.000   1.0811   0.01311   0.00535  -0.1607   0.0603   1.0000
   4.250   1.1014   0.01388   0.00597  -0.1592   0.0258   1.0000
   4.500   1.1242   0.01436   0.00649  -0.1582   0.0223   1.0000
   4.750   1.1456   0.01498   0.00718  -0.1569   0.0200   1.0000
   5.000   1.1641   0.01590   0.00822  -0.1551   0.0186   1.0000
   5.250   1.1845   0.01655   0.00893  -0.1537   0.0181   1.0000
   5.500   1.2031   0.01735   0.00980  -0.1519   0.0175   1.0000
   5.750   1.2216   0.01811   0.01061  -0.1502   0.0164   1.0000
   6.000   1.2387   0.01898   0.01152  -0.1483   0.0155   1.0000
   6.250   1.2543   0.02000   0.01262  -0.1461   0.0150   1.0000
   6.500   1.2694   0.02114   0.01380  -0.1438   0.0146   1.0000
   6.750   1.2845   0.02239   0.01510  -0.1416   0.0142   1.0000
   7.000   1.3026   0.02392   0.01667  -0.1399   0.0139   1.0000
   7.250   1.3305   0.02605   0.01893  -0.1395   0.0146   1.0000
   7.500   1.3881   0.03172   0.02502  -0.1419   0.0244   1.0000
   7.750   1.4094   0.03316   0.02662  -0.1407   0.0224   1.0000
   8.000   1.4311   0.03512   0.02865  -0.1399   0.0210   1.0000
   8.250   1.4084   0.03633   0.03056  -0.1329   0.0186   1.0000
   8.500   1.4190   0.03510   0.02958  -0.1295   0.0178   1.0000
   8.750   1.4312   0.03643   0.03114  -0.1268   0.0165   1.0000
   9.000   1.4401   0.03922   0.03416  -0.1241   0.0155   1.0000
   9.250   1.4455   0.04235   0.03750  -0.1212   0.0148   1.0000
   9.500   1.4478   0.04566   0.04101  -0.1181   0.0144   1.0000
   9.750   1.4476   0.04908   0.04461  -0.1150   0.0140   1.0000
  10.000   1.4446   0.05256   0.04824  -0.1116   0.0138   1.0000
  10.250   1.4339   0.05582   0.05166  -0.1071   0.0136   1.0000
  10.500   1.4243   0.05948   0.05545  -0.1034   0.0135   1.0000
  10.750   1.4092   0.06371   0.05983  -0.0996   0.0133   1.0000
  11.000   1.3871   0.06846   0.06477  -0.0958   0.0132   1.0000
  11.250   1.3635   0.07327   0.06978  -0.0925   0.0131   1.0000
  11.500   1.3362   0.07891   0.07561  -0.0899   0.0131   1.0000
  11.750   1.3117   0.08289   0.07980  -0.0879   0.0132   1.0000
  12.000   1.2774   0.08920   0.08630  -0.0869   0.0131   1.0000
  12.250   1.2356   0.09378   0.09110  -0.0862   0.0132   1.0000
  12.500   1.1872   0.10054   0.09820  -0.0883   0.0136   1.0000
  12.750   1.1649   0.10645   0.10423  -0.0906   0.0135   1.0000
  13.000   1.1153   0.11773   0.11582  -0.0977   0.0140   1.0000
  13.250   1.0789   0.12884   0.12712  -0.1051   0.0142   1.0000
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