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GOE 499 AIRFOIL (goe499-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 499 AIRFOIL (goe499-il)
Reynolds number: 1,000,000
Max Cl/Cd: 157.76 at α=1.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe499-il-1000000.txt
Download as CSV file: xf-goe499-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.2628   0.11336   0.11168  -0.0571   0.9921   0.0117
 -10.250  -0.2509   0.10943   0.10775  -0.0603   0.9902   0.0117
 -10.000  -0.2413   0.10499   0.10331  -0.0624   0.9886   0.0121
  -9.750  -0.2264   0.10202   0.10033  -0.0651   0.9870   0.0124
  -9.500  -0.2106   0.09910   0.09742  -0.0682   0.9855   0.0130
  -9.250  -0.1956   0.09538   0.09369  -0.0719   0.9841   0.0131
  -9.000  -0.1812   0.09208   0.09038  -0.0752   0.9811   0.0151
  -8.750  -0.1684   0.08775   0.08605  -0.0806   0.9763   0.0158
  -8.500  -0.1524   0.08344   0.08174  -0.0853   0.9733   0.0158
  -8.250  -0.1335   0.07887   0.07716  -0.0908   0.9711   0.0158
  -7.750  -0.0995   0.06845   0.06671  -0.1036   0.9600   0.0166
  -7.500  -0.0717   0.06698   0.06522  -0.1070   0.9568   0.0175
  -7.250  -0.0470   0.06458   0.06278  -0.1127   0.9465   0.0212
  -7.000  -0.0280   0.06097   0.05912  -0.1178   0.9361   0.0214
  -6.750  -0.0123   0.05693   0.05503  -0.1227   0.9257   0.0215
  -6.500   0.0028   0.05256   0.05060  -0.1278   0.9150   0.0215
  -6.250   0.0194   0.04737   0.04535  -0.1343   0.9046   0.0217
  -6.000   0.0619   0.01833   0.01511  -0.1732   0.8908   0.0230
  -5.750   0.0883   0.01842   0.01524  -0.1733   0.8866   0.0240
  -5.500   0.1138   0.01919   0.01612  -0.1727   0.8823   0.0255
  -5.250   0.1428   0.01741   0.01407  -0.1743   0.8778   0.0268
  -5.000   0.1727   0.01499   0.01127  -0.1761   0.8738   0.0271
  -4.750   0.2015   0.01374   0.00978  -0.1769   0.8697   0.0279
  -4.500   0.2295   0.01333   0.00926  -0.1771   0.8653   0.0289
  -4.250   0.2582   0.01268   0.00835  -0.1776   0.8614   0.0308
  -4.000   0.2867   0.01182   0.00732  -0.1781   0.8578   0.0307
  -3.750   0.3149   0.01125   0.00666  -0.1783   0.8537   0.0305
  -3.500   0.3430   0.01073   0.00605  -0.1784   0.8495   0.0303
  -3.250   0.3712   0.01026   0.00547  -0.1785   0.8456   0.0301
  -3.000   0.3997   0.00925   0.00432  -0.1789   0.8417   0.0304
  -2.750   0.4279   0.00866   0.00366  -0.1790   0.8374   0.0304
  -2.500   0.4563   0.00785   0.00275  -0.1793   0.8331   0.0313
  -2.250   0.4847   0.00744   0.00226  -0.1794   0.8290   0.0325
  -2.000   0.5129   0.00720   0.00199  -0.1795   0.8250   0.0333
  -1.750   0.5410   0.00702   0.00177  -0.1795   0.8210   0.0339
  -1.500   0.5692   0.00689   0.00160  -0.1796   0.8170   0.0344
  -1.250   0.5973   0.00676   0.00145  -0.1796   0.8130   0.0349
  -1.000   0.6253   0.00665   0.00133  -0.1796   0.8085   0.0354
  -0.750   0.6531   0.00658   0.00122  -0.1795   0.8032   0.0366
  -0.500   0.6809   0.00650   0.00113  -0.1794   0.7972   0.0379
  -0.250   0.7086   0.00644   0.00104  -0.1793   0.7914   0.0398
   0.000   0.7365   0.00628   0.00099  -0.1793   0.7856   0.0877
   0.250   0.7642   0.00608   0.00101  -0.1794   0.7782   0.1749
   0.500   0.7916   0.00602   0.00105  -0.1793   0.7704   0.2198
   0.750   0.8187   0.00599   0.00107  -0.1791   0.7614   0.2492
   1.000   0.8460   0.00596   0.00111  -0.1790   0.7522   0.2798
   1.250   0.8730   0.00593   0.00115  -0.1788   0.7423   0.3184
   1.500   0.8993   0.00580   0.00126  -0.1785   0.7241   0.4382
   1.750   0.9229   0.00585   0.00139  -0.1777   0.6832   0.5541
   2.000   0.9434   0.00616   0.00158  -0.1762   0.6176   0.6344
   2.250   0.9605   0.00611   0.00186  -0.1740   0.5500   1.0000
   2.500   0.9825   0.00660   0.00211  -0.1729   0.5019   1.0000
   2.750   1.0047   0.00710   0.00235  -0.1719   0.4535   1.0000
   3.000   1.0278   0.00752   0.00257  -0.1710   0.4150   1.0000
   3.250   1.0482   0.00817   0.00286  -0.1697   0.3428   1.0000
   3.500   1.0514   0.01060   0.00403  -0.1657   0.0898   1.0000
   3.750   1.0710   0.01148   0.00459  -0.1642   0.0190   1.0000
   4.000   1.0957   0.01177   0.00490  -0.1636   0.0172   1.0000
   4.250   1.1199   0.01212   0.00528  -0.1628   0.0155   1.0000
   4.500   1.1433   0.01256   0.00573  -0.1619   0.0141   1.0000
   4.750   1.1638   0.01331   0.00659  -0.1605   0.0128   1.0000
   5.000   1.1869   0.01372   0.00703  -0.1596   0.0122   1.0000
   5.250   1.2101   0.01412   0.00744  -0.1587   0.0114   1.0000
   5.500   1.2316   0.01467   0.00803  -0.1575   0.0107   1.0000
   5.750   1.2523   0.01526   0.00866  -0.1562   0.0102   1.0000
   6.000   1.2722   0.01591   0.00936  -0.1548   0.0097   1.0000
   6.250   1.2906   0.01666   0.01014  -0.1531   0.0093   1.0000
   6.500   1.3044   0.01785   0.01138  -0.1507   0.0089   1.0000
   6.750   1.3129   0.01994   0.01356  -0.1473   0.0084   1.0000
   7.000   1.3334   0.02050   0.01417  -0.1460   0.0081   1.0000
   7.250   1.3523   0.02153   0.01526  -0.1444   0.0079   1.0000
   7.500   1.3719   0.02246   0.01627  -0.1430   0.0076   1.0000
   7.750   1.3920   0.02359   0.01747  -0.1417   0.0073   1.0000
   8.000   1.4148   0.02525   0.01922  -0.1408   0.0072   1.0000
   8.250   1.4396   0.02718   0.02127  -0.1403   0.0071   1.0000
   8.500   1.4647   0.02940   0.02364  -0.1398   0.0070   1.0000
   8.750   1.4874   0.03185   0.02629  -0.1389   0.0069   1.0000
   9.000   1.5079   0.03590   0.03068  -0.1373   0.0071   1.0000
   9.500   1.5151   0.05046   0.04605  -0.1310   0.0084   1.0000
   9.750   1.5161   0.05338   0.04924  -0.1274   0.0083   1.0000
  10.000   1.5148   0.05587   0.05197  -0.1235   0.0083   1.0000
  10.250   1.5251   0.05532   0.05163  -0.1200   0.0076   1.0000
  10.500   1.5169   0.05809   0.05462  -0.1152   0.0073   1.0000
  10.750   1.5036   0.06088   0.05759  -0.1102   0.0071   1.0000
  11.000   1.4888   0.06401   0.06091  -0.1059   0.0070   1.0000
  11.250   1.4726   0.06750   0.06457  -0.1022   0.0069   1.0000
  11.500   1.4551   0.07134   0.06859  -0.0993   0.0068   1.0000
  11.750   1.4368   0.07557   0.07299  -0.0971   0.0068   1.0000
  12.000   1.4163   0.08041   0.07799  -0.0957   0.0067   1.0000
  12.250   1.3943   0.08589   0.08363  -0.0952   0.0067   1.0000
  12.500   1.3729   0.09172   0.08963  -0.0957   0.0067   1.0000
  12.750   1.3498   0.09835   0.09641  -0.0973   0.0067   1.0000
  13.000   1.3249   0.10605   0.10426  -0.1004   0.0068   1.0000
  13.250   1.3012   0.11439   0.11274  -0.1048   0.0068   1.0000
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