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GOE 81 AIRFOIL (goe81-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 81 AIRFOIL (goe81-il)
Reynolds number: 1,000,000
Max Cl/Cd: 133.74 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe81-il-1000000.txt
Download as CSV file: xf-goe81-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 81 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.1311   0.08814   0.08654  -0.0498   0.9392   0.0136
  -9.000  -0.1245   0.08538   0.08369  -0.0504   0.9183   0.0139
  -8.750  -0.1187   0.08264   0.08089  -0.0509   0.9046   0.0142
  -8.500  -0.1129   0.07981   0.07802  -0.0515   0.8935   0.0147
  -8.250  -0.1071   0.07688   0.07504  -0.0522   0.8836   0.0153
  -8.000  -0.1017   0.07367   0.07181  -0.0538   0.8742   0.0159
  -7.750  -0.1749   0.08584   0.08399  -0.0492   0.9004   0.0148
  -7.500  -0.1652   0.08303   0.08115  -0.0512   0.8881   0.0157
  -7.250  -0.1489   0.07952   0.07758  -0.0577   0.8771   0.0160
  -7.000  -0.1293   0.07565   0.07364  -0.0649   0.8672   0.0160
  -6.750  -0.1110   0.07150   0.06947  -0.0698   0.8578   0.0161
  -6.500  -0.0991   0.06862   0.06655  -0.0695   0.8490   0.0162
  -6.250  -0.0817   0.06600   0.06389  -0.0717   0.8387   0.0164
  -6.000  -0.0614   0.06335   0.06120  -0.0748   0.8282   0.0167
  -5.750  -0.0390   0.06062   0.05840  -0.0784   0.8173   0.0170
  -5.500  -0.0146   0.05779   0.05550  -0.0823   0.8051   0.0178
  -5.250   0.0277   0.05359   0.05116  -0.0918   0.7921   0.0192
  -5.000   0.0626   0.04972   0.04715  -0.0980   0.7789   0.0193
  -4.750   0.0928   0.04640   0.04370  -0.1019   0.7652   0.0193
  -4.500   0.1130   0.04290   0.04011  -0.1038   0.7516   0.0196
  -4.250   0.1360   0.04093   0.03806  -0.1051   0.7377   0.0198
  -4.000   0.1625   0.03890   0.03592  -0.1071   0.7246   0.0201
  -3.500   0.2215   0.03455   0.03133  -0.1116   0.7013   0.0216
  -3.250   0.2631   0.03181   0.02834  -0.1148   0.6912   0.0229
  -2.750   0.3270   0.02557   0.02169  -0.1186   0.6731   0.0233
  -2.500   0.3528   0.02410   0.02013  -0.1195   0.6653   0.0235
  -2.250   0.3804   0.02284   0.01879  -0.1203   0.6589   0.0239
  -2.000   0.4087   0.02160   0.01743  -0.1210   0.6521   0.0244
  -1.750   0.4382   0.02024   0.01595  -0.1216   0.6461   0.0251
  -1.500   0.4690   0.01874   0.01428  -0.1221   0.6399   0.0265
  -1.250   0.5017   0.01760   0.01281  -0.1219   0.6339   0.0275
  -1.000   0.5320   0.01496   0.00990  -0.1228   0.6284   0.0280
  -0.750   0.5598   0.01413   0.00899  -0.1231   0.6211   0.0284
  -0.500   0.5879   0.01349   0.00828  -0.1234   0.6134   0.0290
  -0.250   0.6162   0.01290   0.00757  -0.1235   0.6052   0.0301
   0.000   0.6453   0.01296   0.00745  -0.1232   0.5971   0.0328
   0.250   0.6742   0.01146   0.00572  -0.1235   0.5884   0.0340
   0.500   0.7022   0.01100   0.00525  -0.1236   0.5792   0.0349
   0.750   0.7301   0.01069   0.00485  -0.1236   0.5691   0.0363
   1.000   0.7580   0.01062   0.00469  -0.1235   0.5563   0.0388
   1.250   0.7858   0.01006   0.00402  -0.1235   0.5406   0.0422
   1.500   0.8131   0.00988   0.00377  -0.1234   0.5188   0.0443
   1.750   0.8396   0.01006   0.00380  -0.1231   0.4891   0.0478
   2.000   0.8663   0.00983   0.00334  -0.1226   0.4600   0.0396
   2.250   0.8931   0.00944   0.00276  -0.1222   0.4377   0.0332
   2.500   0.9198   0.00939   0.00264  -0.1220   0.4217   0.0333
   2.750   0.9468   0.00936   0.00257  -0.1219   0.4091   0.0334
   3.000   0.9740   0.00932   0.00250  -0.1218   0.3985   0.0343
   3.250   1.0011   0.00937   0.00251  -0.1217   0.3885   0.0350
   3.500   1.0284   0.00940   0.00253  -0.1216   0.3800   0.0356
   3.750   1.0553   0.00950   0.00259  -0.1215   0.3706   0.0369
   4.000   1.0825   0.00957   0.00265  -0.1214   0.3621   0.0389
   4.250   1.1091   0.00970   0.00273  -0.1212   0.3506   0.0415
   4.500   1.1359   0.00973   0.00293  -0.1211   0.3379   0.1958
   4.750   1.1582   0.00866   0.00325  -0.1205   0.3251   1.0000
   5.000   1.1841   0.00890   0.00340  -0.1202   0.3095   1.0000
   5.250   1.2098   0.00916   0.00358  -0.1199   0.2937   1.0000
   5.500   1.2351   0.00944   0.00378  -0.1196   0.2762   1.0000
   5.750   1.2589   0.00987   0.00406  -0.1190   0.2498   1.0000
   6.000   1.2818   0.01039   0.00439  -0.1183   0.2191   1.0000
   6.250   1.3037   0.01099   0.00479  -0.1175   0.1841   1.0000
   6.500   1.3231   0.01183   0.00535  -0.1163   0.1392   1.0000
   6.750   1.3464   0.01225   0.00570  -0.1157   0.1276   1.0000
   7.000   1.3705   0.01258   0.00601  -0.1152   0.1211   1.0000
   7.250   1.3943   0.01292   0.00632  -0.1146   0.1160   1.0000
   7.500   1.4176   0.01330   0.00668  -0.1140   0.1093   1.0000
   7.750   1.4420   0.01355   0.00695  -0.1136   0.1060   1.0000
   8.000   1.4651   0.01391   0.00729  -0.1129   0.1002   1.0000
   8.250   1.4882   0.01425   0.00763  -0.1123   0.0942   1.0000
   8.500   1.5053   0.01510   0.00824  -0.1108   0.0617   1.0000
   8.750   1.5248   0.01570   0.00880  -0.1097   0.0536   1.0000
   9.000   1.5458   0.01614   0.00926  -0.1087   0.0493   1.0000
   9.250   1.5643   0.01676   0.00987  -0.1074   0.0423   1.0000
   9.500   1.5773   0.01776   0.01070  -0.1053   0.0212   1.0000
   9.750   1.5914   0.01860   0.01153  -0.1032   0.0160   1.0000
  10.000   1.6052   0.01933   0.01231  -0.1011   0.0141   1.0000
  10.250   1.6189   0.01994   0.01298  -0.0990   0.0135   1.0000
  10.500   1.6312   0.02066   0.01376  -0.0967   0.0129   1.0000
  10.750   1.6420   0.02149   0.01466  -0.0943   0.0123   1.0000
  11.000   1.6507   0.02251   0.01575  -0.0918   0.0117   1.0000
  11.250   1.6557   0.02383   0.01717  -0.0890   0.0111   1.0000
  11.500   1.6649   0.02493   0.01834  -0.0870   0.0108   1.0000
  11.750   1.6744   0.02605   0.01954  -0.0852   0.0106   1.0000
  12.000   1.6826   0.02734   0.02091  -0.0833   0.0103   1.0000
  12.250   1.6899   0.02875   0.02240  -0.0816   0.0100   1.0000
  12.500   1.6961   0.03031   0.02403  -0.0799   0.0096   1.0000
  12.750   1.7012   0.03202   0.02582  -0.0783   0.0093   1.0000
  13.000   1.7044   0.03397   0.02785  -0.0768   0.0091   1.0000
  13.250   1.7040   0.03637   0.03035  -0.0753   0.0088   1.0000
  13.500   1.6987   0.03937   0.03347  -0.0738   0.0086   1.0000
  13.750   1.6869   0.04323   0.03747  -0.0724   0.0084   1.0000
  14.000   1.6832   0.04638   0.04073  -0.0716   0.0083   1.0000
  14.250   1.6842   0.04904   0.04348  -0.0711   0.0082   1.0000
  14.500   1.6830   0.05205   0.04659  -0.0706   0.0081   1.0000
  14.750   1.6797   0.05542   0.05006  -0.0704   0.0080   1.0000
  15.000   1.6756   0.05896   0.05371  -0.0702   0.0079   1.0000
  15.250   1.6697   0.06283   0.05769  -0.0703   0.0078   1.0000
  15.500   1.6635   0.06687   0.06183  -0.0705   0.0076   1.0000
  15.750   1.6553   0.07127   0.06634  -0.0709   0.0076   1.0000
  16.000   1.6467   0.07582   0.07100  -0.0715   0.0075   1.0000
  16.250   1.6377   0.08058   0.07587  -0.0723   0.0074   1.0000
  16.500   1.6278   0.08558   0.08098  -0.0733   0.0073   1.0000
  16.750   1.6179   0.09067   0.08617  -0.0744   0.0072   1.0000
  17.000   1.6076   0.09588   0.09148  -0.0757   0.0071   1.0000
  17.250   1.5972   0.10120   0.09691  -0.0771   0.0071   1.0000
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