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GOE 392 AIRFOIL (goe392-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 392 AIRFOIL (goe392-il)
Reynolds number: 500,000
Max Cl/Cd: 105.31 at α=2.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe392-il-500000.txt
Download as CSV file: xf-goe392-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 392 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
  ------ -------- --------- --------- -------- -------- --------
  -7.250  -0.2207   0.07260   0.07062  -0.0699   0.9752   0.0128
  -7.000  -0.1952   0.06788   0.06589  -0.0776   0.9710   0.0135
  -6.750  -0.1755   0.06290   0.06087  -0.0850   0.9618   0.0139
  -6.500  -0.1450   0.05681   0.05473  -0.0957   0.9572   0.0144
  -6.250  -0.1201   0.05098   0.04882  -0.1039   0.9461   0.0150
  -6.000  -0.0888   0.04440   0.04207  -0.1129   0.9357   0.0157
  -5.750  -0.0547   0.03856   0.03597  -0.1200   0.9260   0.0168
  -5.500  -0.0139   0.03575   0.03279  -0.1242   0.9162   0.0187
  -5.250   0.0170   0.03264   0.02930  -0.1271   0.9025   0.0189
  -5.000   0.0442   0.02963   0.02592  -0.1289   0.8874   0.0190
  -4.750   0.0691   0.02678   0.02267  -0.1295   0.8721   0.0191
  -4.500   0.0844   0.02059   0.01593  -0.1295   0.8577   0.0205
  -4.250   0.1080   0.01853   0.01360  -0.1293   0.8451   0.0215
  -3.750   0.1579   0.01532   0.00977  -0.1280   0.8235   0.0231
  -3.500   0.1842   0.01387   0.00791  -0.1267   0.8133   0.0203
  -3.250   0.2107   0.01336   0.00722  -0.1261   0.8037   0.0194
  -3.000   0.2352   0.01176   0.00544  -0.1253   0.7950   0.0199
  -2.750   0.2584   0.01065   0.00426  -0.1244   0.7853   0.0224
  -2.500   0.2835   0.01025   0.00378  -0.1239   0.7757   0.0256
  -2.250   0.3086   0.00990   0.00332  -0.1232   0.7656   0.0289
  -1.750   0.3576   0.00909   0.00227  -0.1218   0.7438   0.0400
  -1.500   0.3833   0.00892   0.00199  -0.1214   0.7338   0.0458
  -1.250   0.4056   0.00811   0.00176  -0.1207   0.7246   0.2604
  -1.000   0.4300   0.00788   0.00181  -0.1202   0.7150   0.3918
  -0.750   0.4554   0.00781   0.00177  -0.1197   0.7048   0.4282
  -0.500   0.4807   0.00773   0.00174  -0.1193   0.6951   0.4574
  -0.250   0.5045   0.00752   0.00172  -0.1186   0.6855   0.5294
   0.000   0.5224   0.00698   0.00181  -0.1166   0.6754   0.7496
   0.250   0.5857   0.00662   0.00182  -0.1244   0.6640   1.0000
   0.500   0.6103   0.00671   0.00182  -0.1238   0.6536   1.0000
   0.750   0.6349   0.00681   0.00184  -0.1232   0.6436   1.0000
   1.000   0.6596   0.00692   0.00186  -0.1226   0.6332   1.0000
   1.250   0.6844   0.00702   0.00190  -0.1221   0.6227   1.0000
   1.500   0.7092   0.00713   0.00195  -0.1215   0.6125   1.0000
   1.750   0.7339   0.00726   0.00201  -0.1210   0.6026   1.0000
   2.000   0.7588   0.00738   0.00211  -0.1205   0.5929   1.0000
   2.250   0.7839   0.00750   0.00220  -0.1200   0.5836   1.0000
   2.500   0.8067   0.00766   0.00227  -0.1190   0.5657   1.0000
   2.750   0.8274   0.00790   0.00235  -0.1176   0.5366   1.0000
   3.000   0.8504   0.00808   0.00247  -0.1167   0.5159   1.0000
   3.250   0.8717   0.00834   0.00263  -0.1155   0.4864   1.0000
   3.500   0.8854   0.00899   0.00285  -0.1129   0.4039   1.0000
   3.750   0.8877   0.01063   0.00355  -0.1085   0.2429   1.0000
   4.000   0.8862   0.01272   0.00473  -0.1035   0.0253   1.0000
   4.250   0.9085   0.01306   0.00516  -0.1024   0.0218   1.0000
   4.500   0.9297   0.01347   0.00566  -0.1012   0.0195   1.0000
   4.750   0.9487   0.01403   0.00636  -0.0995   0.0168   1.0000
   5.000   0.9636   0.01486   0.00732  -0.0971   0.0157   1.0000
   5.250   0.9720   0.01601   0.00861  -0.0935   0.0151   1.0000
   5.500   0.9844   0.01679   0.00946  -0.0907   0.0149   1.0000
   5.750   0.9875   0.01793   0.01067  -0.0861   0.0153   1.0000
   6.000   1.0011   0.01854   0.01132  -0.0835   0.0158   1.0000
   6.250   1.0009   0.02014   0.01298  -0.0788   0.0149   1.0000
   6.500   1.0110   0.02201   0.01485  -0.0759   0.0151   1.0000
   6.750   1.0293   0.02228   0.01518  -0.0742   0.0158   1.0000
  10.250   1.3050   0.06270   0.05762  -0.0635   0.0081   1.0000
  10.500   1.2983   0.06545   0.06060  -0.0596   0.0081   1.0000
  10.750   1.2874   0.06801   0.06337  -0.0554   0.0081   1.0000
  11.000   1.2739   0.07030   0.06584  -0.0508   0.0081   1.0000
  11.250   1.2564   0.07263   0.06834  -0.0463   0.0081   1.0000
  11.500   1.2396   0.07521   0.07108  -0.0427   0.0081   1.0000
  11.750   1.2198   0.07804   0.07408  -0.0397   0.0081   1.0000
  12.000   1.2018   0.08120   0.07740  -0.0376   0.0081   1.0000
  12.250   1.1829   0.08471   0.08106  -0.0363   0.0081   1.0000
  12.500   1.1658   0.08861   0.08509  -0.0358   0.0081   1.0000
  12.750   1.1462   0.09281   0.08945  -0.0358   0.0081   1.0000
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