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GOE 176 (ALBATROS 7020) AIRFOIL (goe176-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 176 (ALBATROS 7020) AIRFOIL (goe176-il)
Reynolds number: 500,000
Max Cl/Cd: 87.04 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe176-il-500000-n5.txt
Download as CSV file: xf-goe176-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 176 (ALBATROS 7020) 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
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.3086   0.11707   0.11478  -0.0280   1.0000   0.0079
 -10.250  -0.3035   0.11439   0.11211  -0.0283   1.0000   0.0077
 -10.000  -0.2996   0.11139   0.10913  -0.0288   1.0000   0.0075
  -9.750  -0.2966   0.10825   0.10602  -0.0293   1.0000   0.0074
  -9.500  -0.2944   0.10499   0.10278  -0.0299   1.0000   0.0073
  -9.250  -0.2870   0.10101   0.09882  -0.0323   0.9987   0.0071
  -9.000  -0.2752   0.09637   0.09419  -0.0364   0.9956   0.0071
  -8.750  -0.2661   0.09187   0.08969  -0.0399   0.9903   0.0071
  -8.250  -0.2533   0.08310   0.08096  -0.0458   0.9512   0.0071
  -8.000  -0.2240   0.07535   0.07315  -0.0577   0.9250   0.0073
  -7.750  -0.2029   0.06723   0.06490  -0.0692   0.8906   0.0076
  -7.500  -0.1907   0.02352   0.01985  -0.1272   0.8613   0.0073
  -7.250  -0.1636   0.01980   0.01549  -0.1302   0.8445   0.0075
  -7.000  -0.1368   0.01777   0.01301  -0.1312   0.8293   0.0078
  -6.750  -0.1099   0.01643   0.01132  -0.1317   0.8134   0.0080
  -6.500  -0.0832   0.01515   0.00971  -0.1320   0.7959   0.0083
  -6.250  -0.0564   0.01432   0.00866  -0.1321   0.7785   0.0087
  -6.000  -0.0293   0.01377   0.00794  -0.1320   0.7623   0.0091
  -5.750  -0.0019   0.01328   0.00730  -0.1320   0.7468   0.0096
  -5.500   0.0256   0.01288   0.00674  -0.1319   0.7319   0.0104
  -5.250   0.0532   0.01249   0.00617  -0.1318   0.7163   0.0112
  -5.000   0.0809   0.01193   0.00543  -0.1318   0.7003   0.0119
  -4.750   0.1086   0.01150   0.00486  -0.1318   0.6834   0.0130
  -4.500   0.1362   0.01126   0.00447  -0.1317   0.6645   0.0141
  -4.250   0.1638   0.01105   0.00412  -0.1315   0.6463   0.0155
  -4.000   0.1917   0.01080   0.00373  -0.1314   0.6295   0.0175
  -3.750   0.2194   0.01061   0.00343  -0.1313   0.6121   0.0202
  -3.500   0.2471   0.01050   0.00318  -0.1311   0.5954   0.0229
  -3.250   0.2749   0.01033   0.00290  -0.1310   0.5802   0.0275
  -3.000   0.3028   0.01024   0.00270  -0.1309   0.5664   0.0322
  -2.750   0.3307   0.01013   0.00250  -0.1308   0.5539   0.0388
  -2.500   0.3588   0.01000   0.00231  -0.1308   0.5436   0.0523
  -2.250   0.3868   0.00962   0.00215  -0.1310   0.5334   0.1287
  -2.000   0.4147   0.00955   0.00215  -0.1309   0.5237   0.1714
  -1.750   0.4425   0.00960   0.00213  -0.1308   0.5128   0.1872
  -1.500   0.4702   0.00965   0.00213  -0.1306   0.5002   0.1989
  -1.250   0.4979   0.00971   0.00212  -0.1305   0.4851   0.2055
  -1.000   0.5252   0.00981   0.00212  -0.1303   0.4622   0.2137
  -0.750   0.5506   0.01009   0.00216  -0.1298   0.4048   0.2229
  -0.500   0.5753   0.01051   0.00227  -0.1292   0.3521   0.2293
   0.000   0.6290   0.01084   0.00242  -0.1287   0.3257   0.2370
   0.250   0.6560   0.01098   0.00250  -0.1285   0.3170   0.2420
   0.500   0.6833   0.01109   0.00257  -0.1283   0.3107   0.2481
   0.750   0.7105   0.01120   0.00266  -0.1282   0.3057   0.2556
   1.000   0.7379   0.01129   0.00273  -0.1280   0.3019   0.2616
   1.250   0.7654   0.01135   0.00281  -0.1279   0.2983   0.2670
   1.500   0.7926   0.01145   0.00290  -0.1277   0.2932   0.2734
   1.750   0.8196   0.01158   0.00301  -0.1275   0.2867   0.2802
   2.000   0.8469   0.01166   0.00310  -0.1274   0.2805   0.2896
   2.250   0.8739   0.01177   0.00321  -0.1272   0.2755   0.2997
   2.500   0.9010   0.01186   0.00333  -0.1271   0.2715   0.3116
   2.750   0.9283   0.01192   0.00345  -0.1270   0.2667   0.3273
   3.000   0.9552   0.01202   0.00359  -0.1268   0.2605   0.3504
   3.250   0.9822   0.01208   0.00374  -0.1267   0.2532   0.3923
   3.500   1.0087   0.01215   0.00391  -0.1266   0.2424   0.4625
   3.750   1.0349   0.01189   0.00415  -0.1266   0.2259   0.7053
   4.250   1.0699   0.01292   0.00503  -0.1228   0.1212   1.0000
   4.500   1.0949   0.01325   0.00532  -0.1223   0.1122   1.0000
   4.750   1.1197   0.01358   0.00560  -0.1218   0.1046   1.0000
   5.000   1.1447   0.01388   0.00587  -0.1213   0.0963   1.0000
   5.250   1.1665   0.01452   0.00633  -0.1204   0.0627   1.0000
   5.500   1.1908   0.01487   0.00668  -0.1199   0.0606   1.0000
   5.750   1.2149   0.01523   0.00703  -0.1193   0.0584   1.0000
   6.000   1.2390   0.01557   0.00739  -0.1187   0.0563   1.0000
   6.250   1.2627   0.01594   0.00779  -0.1180   0.0533   1.0000
   6.500   1.2866   0.01627   0.00816  -0.1174   0.0517   1.0000
   6.750   1.3101   0.01662   0.00856  -0.1167   0.0503   1.0000
   7.000   1.3329   0.01702   0.00900  -0.1160   0.0479   1.0000
   7.250   1.3546   0.01751   0.00952  -0.1151   0.0451   1.0000
   7.500   1.3767   0.01793   0.00999  -0.1142   0.0429   1.0000
   7.750   1.3997   0.01824   0.01033  -0.1135   0.0397   1.0000
   8.000   1.4195   0.01881   0.01078  -0.1124   0.0200   1.0000
   8.250   1.4371   0.01955   0.01151  -0.1108   0.0131   1.0000
   8.500   1.4551   0.02022   0.01226  -0.1093   0.0111   1.0000
   8.750   1.4709   0.02100   0.01314  -0.1075   0.0094   1.0000
   9.000   1.4879   0.02162   0.01384  -0.1059   0.0086   1.0000
   9.250   1.5017   0.02231   0.01461  -0.1037   0.0079   1.0000
   9.500   1.5136   0.02310   0.01547  -0.1013   0.0073   1.0000
   9.750   1.5232   0.02405   0.01651  -0.0987   0.0068   1.0000
  10.000   1.5326   0.02504   0.01760  -0.0962   0.0064   1.0000
  10.250   1.5429   0.02599   0.01864  -0.0940   0.0061   1.0000
  10.500   1.5518   0.02707   0.01981  -0.0917   0.0057   1.0000
  10.750   1.5597   0.02829   0.02111  -0.0896   0.0054   1.0000
  11.000   1.5663   0.02968   0.02261  -0.0876   0.0051   1.0000
  11.250   1.5706   0.03135   0.02438  -0.0856   0.0049   1.0000
  11.500   1.5717   0.03343   0.02657  -0.0838   0.0047   1.0000
  11.750   1.5694   0.03601   0.02927  -0.0821   0.0046   1.0000
  12.000   1.5708   0.03837   0.03175  -0.0810   0.0045   1.0000
  12.250   1.5704   0.04104   0.03455  -0.0800   0.0043   1.0000
  12.500   1.5685   0.04403   0.03767  -0.0793   0.0042   1.0000
  12.750   1.5644   0.04739   0.04116  -0.0789   0.0041   1.0000
  13.000   1.5592   0.05105   0.04495  -0.0787   0.0040   1.0000
  13.250   1.5521   0.05509   0.04912  -0.0788   0.0040   1.0000
  13.500   1.5439   0.05937   0.05354  -0.0790   0.0039   1.0000
  13.750   1.5344   0.06397   0.05827  -0.0795   0.0038   1.0000
  14.000   1.5241   0.06881   0.06324  -0.0802   0.0038   1.0000
  14.250   1.5135   0.07378   0.06833  -0.0811   0.0037   1.0000
  14.500   1.5017   0.07906   0.07374  -0.0821   0.0037   1.0000
  14.750   1.4908   0.08432   0.07912  -0.0833   0.0036   1.0000
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