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GOE 528 AIRFOIL (goe528-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 528 AIRFOIL (goe528-il)
Reynolds number: 500,000
Max Cl/Cd: 106.75 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe528-il-500000-n5.txt
Download as CSV file: xf-goe528-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 528 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.0623   0.08448   0.08165  -0.0986   0.8881   0.0165
 -10.000  -0.0436   0.08240   0.07947  -0.1014   0.8696   0.0169
  -9.750  -0.0361   0.07947   0.07646  -0.1033   0.8537   0.0172
  -9.500  -0.0296   0.07693   0.07386  -0.1045   0.8392   0.0177
  -9.000  -0.0548   0.06583   0.06267  -0.1091   0.8136   0.0194
  -8.750  -0.0517   0.06367   0.06049  -0.1096   0.8024   0.0196
  -8.250  -0.1838   0.02614   0.02184  -0.1315   0.7774   0.0230
  -8.000  -0.1651   0.02486   0.02043  -0.1311   0.7698   0.0233
  -7.750  -0.1431   0.02421   0.01968  -0.1307   0.7625   0.0235
  -7.500  -0.1212   0.02340   0.01875  -0.1302   0.7544   0.0239
  -7.250  -0.0999   0.02242   0.01759  -0.1297   0.7468   0.0242
  -7.000  -0.0795   0.02097   0.01589  -0.1292   0.7390   0.0247
  -6.750  -0.0587   0.01960   0.01423  -0.1285   0.7317   0.0252
  -6.500  -0.0368   0.01826   0.01261  -0.1278   0.7237   0.0259
  -6.250  -0.0140   0.01725   0.01129  -0.1271   0.7157   0.0265
  -6.000   0.0101   0.01644   0.01024  -0.1265   0.7072   0.0269
  -5.750   0.0342   0.01570   0.00927  -0.1259   0.6990   0.0272
  -5.500   0.0586   0.01487   0.00833  -0.1254   0.6903   0.0276
  -5.250   0.0834   0.01438   0.00772  -0.1248   0.6811   0.0280
  -5.000   0.1090   0.01396   0.00722  -0.1243   0.6713   0.0284
  -4.750   0.1346   0.01363   0.00678  -0.1238   0.6620   0.0289
  -4.500   0.1602   0.01330   0.00635  -0.1233   0.6514   0.0294
  -4.250   0.1858   0.01295   0.00589  -0.1227   0.6409   0.0299
  -4.000   0.2113   0.01262   0.00545  -0.1221   0.6303   0.0304
  -3.750   0.2369   0.01231   0.00504  -0.1216   0.6192   0.0307
  -3.500   0.2626   0.01205   0.00469  -0.1210   0.6084   0.0311
  -3.250   0.2881   0.01184   0.00437  -0.1204   0.5978   0.0315
  -3.000   0.3139   0.01165   0.00410  -0.1199   0.5875   0.0319
  -2.750   0.3393   0.01140   0.00378  -0.1193   0.5779   0.0323
  -2.500   0.3646   0.01119   0.00353  -0.1188   0.5685   0.0331
  -2.250   0.3907   0.01105   0.00335  -0.1183   0.5602   0.0339
  -2.000   0.4164   0.01095   0.00320  -0.1178   0.5522   0.0347
  -1.750   0.4426   0.01085   0.00305  -0.1173   0.5448   0.0353
  -1.500   0.4687   0.01077   0.00292  -0.1169   0.5377   0.0361
  -1.250   0.4948   0.01071   0.00281  -0.1164   0.5313   0.0369
  -1.000   0.5212   0.01065   0.00272  -0.1160   0.5249   0.0376
  -0.750   0.5471   0.01059   0.00263  -0.1155   0.5189   0.0391
  -0.500   0.5735   0.01055   0.00257  -0.1151   0.5134   0.0410
  -0.250   0.6000   0.01053   0.00253  -0.1148   0.5076   0.0438
   0.000   0.6258   0.01052   0.00251  -0.1143   0.5022   0.0487
   0.250   0.6521   0.01048   0.00251  -0.1139   0.4971   0.0618
   0.500   0.6783   0.01041   0.00252  -0.1135   0.4918   0.0910
   0.750   0.7037   0.01034   0.00255  -0.1131   0.4867   0.1372
   1.000   0.7289   0.01022   0.00262  -0.1126   0.4820   0.2195
   1.250   0.7541   0.01004   0.00271  -0.1122   0.4767   0.3219
   1.500   0.7778   0.00982   0.00283  -0.1115   0.4714   0.4601
   1.750   0.8319   0.00887   0.00306  -0.1173   0.4654   1.0000
   2.000   0.8572   0.00897   0.00312  -0.1167   0.4600   1.0000
   2.250   0.8817   0.00910   0.00319  -0.1160   0.4543   1.0000
   2.500   0.9062   0.00924   0.00327  -0.1153   0.4490   1.0000
   2.750   0.9313   0.00935   0.00335  -0.1147   0.4432   1.0000
   3.000   0.9555   0.00950   0.00344  -0.1140   0.4370   1.0000
   3.250   0.9800   0.00964   0.00354  -0.1133   0.4309   1.0000
   3.500   1.0043   0.00978   0.00364  -0.1126   0.4237   1.0000
   3.750   1.0279   0.00995   0.00376  -0.1118   0.4172   1.0000
   4.000   1.0524   0.01009   0.00388  -0.1111   0.4105   1.0000
   4.250   1.0759   0.01027   0.00402  -0.1103   0.4042   1.0000
   4.500   1.0998   0.01043   0.00416  -0.1096   0.3977   1.0000
   4.750   1.1232   0.01060   0.00431  -0.1088   0.3909   1.0000
   5.000   1.1462   0.01080   0.00448  -0.1079   0.3851   1.0000
   5.250   1.1698   0.01097   0.00464  -0.1071   0.3788   1.0000
   5.500   1.1920   0.01118   0.00483  -0.1062   0.3725   1.0000
   5.750   1.2148   0.01138   0.00502  -0.1053   0.3662   1.0000
   6.000   1.2360   0.01162   0.00523  -0.1041   0.3578   1.0000
   6.250   1.2574   0.01185   0.00545  -0.1030   0.3496   1.0000
   6.500   1.2770   0.01214   0.00570  -0.1016   0.3406   1.0000
   6.750   1.2976   0.01238   0.00594  -0.1004   0.3331   1.0000
   7.250   1.3337   0.01294   0.00647  -0.0970   0.3169   1.0000
   7.500   1.3501   0.01328   0.00679  -0.0951   0.3093   1.0000
   7.750   1.3684   0.01358   0.00709  -0.0935   0.3012   1.0000
   8.000   1.3840   0.01397   0.00745  -0.0915   0.2934   1.0000
   8.250   1.4013   0.01432   0.00781  -0.0899   0.2844   1.0000
   8.500   1.4168   0.01475   0.00822  -0.0880   0.2773   1.0000
   8.750   1.4337   0.01513   0.00862  -0.0864   0.2698   1.0000
   9.000   1.4478   0.01564   0.00910  -0.0844   0.2616   1.0000
   9.250   1.4633   0.01610   0.00958  -0.0827   0.2538   1.0000
   9.500   1.4769   0.01666   0.01014  -0.0808   0.2472   1.0000
   9.750   1.4921   0.01718   0.01068  -0.0792   0.2403   1.0000
  10.000   1.5039   0.01786   0.01136  -0.0772   0.2328   1.0000
  10.250   1.5178   0.01848   0.01201  -0.0756   0.2255   1.0000
  10.750   1.5420   0.01998   0.01354  -0.0721   0.2122   1.0000
  11.000   1.5519   0.02090   0.01446  -0.0703   0.2053   1.0000
  11.250   1.5622   0.02184   0.01542  -0.0686   0.1963   1.0000
  11.500   1.5696   0.02300   0.01657  -0.0667   0.1871   1.0000
  11.750   1.5741   0.02441   0.01794  -0.0648   0.1751   1.0000
  12.000   1.5808   0.02572   0.01926  -0.0631   0.1649   1.0000
  12.250   1.5848   0.02729   0.02081  -0.0614   0.1532   1.0000
  12.500   1.5853   0.02918   0.02267  -0.0595   0.1386   1.0000
  12.750   1.5725   0.03225   0.02557  -0.0571   0.1089   1.0000
  13.250   1.5577   0.03796   0.03121  -0.0538   0.0834   1.0000
  13.500   1.5545   0.04064   0.03392  -0.0526   0.0779   1.0000
  13.750   1.5574   0.04282   0.03617  -0.0519   0.0751   1.0000
  14.000   1.5563   0.04548   0.03889  -0.0512   0.0712   1.0000
  14.250   1.5532   0.04844   0.04190  -0.0505   0.0678   1.0000
  14.500   1.5547   0.05097   0.04452  -0.0501   0.0656   1.0000
  14.750   1.5557   0.05363   0.04725  -0.0498   0.0628   1.0000
  15.000   1.5539   0.05666   0.05035  -0.0496   0.0599   1.0000
  15.250   1.5502   0.06001   0.05376  -0.0495   0.0575   1.0000
  15.500   1.5501   0.06295   0.05678  -0.0495   0.0553   1.0000
  15.750   1.5487   0.06610   0.06002  -0.0496   0.0529   1.0000
  16.000   1.5446   0.06966   0.06363  -0.0498   0.0501   1.0000
  16.250   1.5401   0.07333   0.06737  -0.0501   0.0478   1.0000
  16.500   1.5356   0.07704   0.07115  -0.0505   0.0442   1.0000
  16.750   1.5300   0.08095   0.07512  -0.0510   0.0419   1.0000
  17.000   1.5252   0.08483   0.07906  -0.0516   0.0388   1.0000
  17.250   1.5189   0.08900   0.08330  -0.0524   0.0361   1.0000
  17.500   1.5116   0.09334   0.08770  -0.0533   0.0332   1.0000
  17.750   1.5037   0.09786   0.09228  -0.0544   0.0301   1.0000
  18.000   1.4962   0.10238   0.09686  -0.0555   0.0271   1.0000
  18.250   1.4877   0.10713   0.10167  -0.0569   0.0243   1.0000
  18.500   1.4791   0.11195   0.10655  -0.0584   0.0218   1.0000
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