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GOE 456 AIRFOIL (goe456-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 456 AIRFOIL (goe456-il)
Reynolds number: 200,000
Max Cl/Cd: 86.35 at α=4°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe456-il-200000-n5.txt
Download as CSV file: xf-goe456-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 456 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.2927   0.10872   0.10536  -0.0349   1.0000   0.0145
  -8.750  -0.2938   0.10661   0.10330  -0.0339   1.0000   0.0150
  -8.500  -0.2970   0.10468   0.10142  -0.0326   1.0000   0.0153
  -8.250  -0.2870   0.10141   0.09817  -0.0350   0.9976   0.0157
  -8.000  -0.2705   0.09738   0.09415  -0.0394   0.9930   0.0164
  -7.750  -0.2543   0.09352   0.09028  -0.0438   0.9882   0.0172
  -7.500  -0.2398   0.08979   0.08657  -0.0478   0.9823   0.0181
  -7.250  -0.2242   0.08602   0.08281  -0.0523   0.9761   0.0190
  -7.000  -0.2081   0.08236   0.07915  -0.0575   0.9688   0.0201
  -6.750  -0.1863   0.07838   0.07517  -0.0660   0.9594   0.0213
  -6.500  -0.1581   0.07381   0.07059  -0.0749   0.9537   0.0217
  -6.250  -0.1344   0.06947   0.06619  -0.0813   0.9460   0.0218
  -6.000  -0.1045   0.06466   0.06133  -0.0889   0.9416   0.0218
  -5.750  -0.0807   0.06020   0.05683  -0.0944   0.9328   0.0219
  -5.500  -0.0493   0.05517   0.05170  -0.1015   0.9279   0.0219
  -5.250  -0.0246   0.05051   0.04696  -0.1062   0.9192   0.0219
  -5.000  -0.0022   0.04403   0.04037  -0.1100   0.9132   0.0114
  -4.750   0.0266   0.03862   0.03477  -0.1154   0.9049   0.0109
  -4.500   0.0605   0.03227   0.02811  -0.1209   0.8988   0.0104
  -4.250   0.0904   0.02665   0.02198  -0.1241   0.8911   0.0102
  -4.000   0.1214   0.02309   0.01782  -0.1258   0.8852   0.0110
  -3.750   0.1495   0.02128   0.01549  -0.1260   0.8776   0.0120
  -3.500   0.1789   0.01893   0.01258  -0.1265   0.8716   0.0121
  -3.250   0.2057   0.01679   0.00996  -0.1262   0.8640   0.0123
  -3.000   0.2338   0.01490   0.00771  -0.1261   0.8575   0.0130
  -2.750   0.2606   0.01381   0.00646  -0.1258   0.8495   0.0151
  -2.500   0.2881   0.01314   0.00565  -0.1256   0.8420   0.0184
  -2.250   0.3161   0.01253   0.00481  -0.1254   0.8344   0.0211
  -2.000   0.3432   0.01199   0.00413  -0.1251   0.8259   0.0302
  -1.750   0.3706   0.01118   0.00361  -0.1250   0.8183   0.1261
  -1.500   0.3971   0.01109   0.00353  -0.1247   0.8086   0.1773
  -1.250   0.4241   0.01100   0.00338  -0.1245   0.7997   0.2016
  -1.000   0.4515   0.01089   0.00319  -0.1244   0.7909   0.2150
  -0.750   0.4779   0.01080   0.00304  -0.1240   0.7808   0.2264
  -0.500   0.5046   0.01071   0.00291  -0.1237   0.7709   0.2426
  -0.250   0.5315   0.01063   0.00281  -0.1235   0.7612   0.2671
   0.000   0.5577   0.01054   0.00275  -0.1232   0.7506   0.2999
   0.250   0.5837   0.01042   0.00271  -0.1229   0.7402   0.3474
   0.500   0.6089   0.01012   0.00270  -0.1224   0.7300   0.4648
   1.000   0.6721   0.00925   0.00267  -0.1238   0.7094   1.0000
   1.250   0.6981   0.00937   0.00267  -0.1234   0.6972   1.0000
   1.500   0.7238   0.00949   0.00269  -0.1229   0.6835   1.0000
   1.750   0.7493   0.00963   0.00272  -0.1223   0.6692   1.0000
   2.000   0.7747   0.00978   0.00280  -0.1218   0.6561   1.0000
   2.250   0.8001   0.00994   0.00289  -0.1213   0.6433   1.0000
   2.500   0.8254   0.01012   0.00300  -0.1207   0.6309   1.0000
   2.750   0.8504   0.01030   0.00316  -0.1202   0.6174   1.0000
   3.000   0.8753   0.01050   0.00331  -0.1196   0.6041   1.0000
   3.250   0.9004   0.01068   0.00350  -0.1190   0.5928   1.0000
   3.500   0.9257   0.01086   0.00372  -0.1186   0.5830   1.0000
   3.750   0.9509   0.01105   0.00399  -0.1181   0.5728   1.0000
   4.000   0.9740   0.01128   0.00421  -0.1171   0.5515   1.0000
   4.250   0.9926   0.01165   0.00440  -0.1152   0.5018   1.0000
   4.500   1.0069   0.01232   0.00468  -0.1126   0.4130   1.0000
   4.750   1.0046   0.01446   0.00568  -0.1079   0.2270   1.0000
   5.250   1.0205   0.01782   0.00793  -0.1017   0.0176   1.0000
   5.500   1.0397   0.01854   0.00882  -0.1001   0.0147   1.0000
   5.750   1.0563   0.01949   0.00998  -0.0981   0.0118   1.0000
   6.000   1.0736   0.02032   0.01098  -0.0963   0.0109   1.0000
   6.250   1.0882   0.02133   0.01216  -0.0941   0.0102   1.0000
   6.500   1.0991   0.02251   0.01352  -0.0913   0.0096   1.0000
   6.750   1.1072   0.02375   0.01485  -0.0881   0.0091   1.0000
   7.000   1.1161   0.02498   0.01613  -0.0852   0.0083   1.0000
   7.250   1.1217   0.02671   0.01787  -0.0821   0.0074   1.0000
   7.500   1.1330   0.02904   0.02018  -0.0799   0.0070   1.0000
   7.750   1.1538   0.03071   0.02194  -0.0787   0.0068   1.0000
   8.000   1.1806   0.03278   0.02413  -0.0785   0.0067   1.0000
   8.250   1.2127   0.03539   0.02691  -0.0792   0.0066   1.0000
   8.500   1.2415   0.03840   0.03012  -0.0793   0.0067   1.0000
   9.000   1.2897   0.04493   0.03716  -0.0784   0.0072   1.0000
   9.500   1.2962   0.04921   0.04221  -0.0715   0.0064   1.0000
   9.750   1.2979   0.05108   0.04440  -0.0679   0.0060   1.0000
  10.000   1.2964   0.05328   0.04688  -0.0642   0.0057   1.0000
  10.250   1.2912   0.05607   0.04995  -0.0606   0.0057   1.0000
  10.500   1.2832   0.05921   0.05336  -0.0573   0.0058   1.0000
  10.750   1.2727   0.06251   0.05690  -0.0544   0.0060   1.0000
  11.000   1.2608   0.06604   0.06066  -0.0520   0.0061   1.0000
  11.250   1.2467   0.06989   0.06474  -0.0501   0.0062   1.0000
  11.500   1.2316   0.07403   0.06909  -0.0489   0.0063   1.0000
  11.750   1.2154   0.07855   0.07380  -0.0483   0.0064   1.0000
  12.000   1.1987   0.08344   0.07888  -0.0485   0.0065   1.0000
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