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GOE 400 AIRFOIL (goe400-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 400 AIRFOIL (goe400-il)
Reynolds number: 500,000
Max Cl/Cd: 109.77 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe400-il-500000.txt
Download as CSV file: xf-goe400-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 400 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.4333   0.11319   0.11096   0.0057   1.0000   0.0215
  -9.000  -0.4302   0.11006   0.10784   0.0024   1.0000   0.0216
  -8.750  -0.4250   0.10670   0.10450  -0.0001   1.0000   0.0217
  -8.500  -0.4190   0.10318   0.10100  -0.0023   1.0000   0.0217
  -8.250  -0.4119   0.09828   0.09612  -0.0011   1.0000   0.0222
  -8.000  -0.4024   0.09553   0.09338  -0.0016   1.0000   0.0226
  -7.750  -0.3936   0.09285   0.09072  -0.0026   1.0000   0.0230
  -7.500  -0.3852   0.09008   0.08797  -0.0042   1.0000   0.0236
  -7.250  -0.3758   0.08712   0.08503  -0.0064   1.0000   0.0245
  -7.000  -0.3629   0.08367   0.08158  -0.0102   1.0000   0.0258
  -6.750  -0.3378   0.07898   0.07688  -0.0228   1.0000   0.0275
  -6.500  -0.3180   0.07467   0.07255  -0.0283   1.0000   0.0276
  -6.250  -0.3098   0.06883   0.06673  -0.0311   1.0000   0.0283
  -6.000  -0.2961   0.06657   0.06449  -0.0310   1.0000   0.0288
  -5.750  -0.2775   0.06407   0.06200  -0.0328   0.9978   0.0295
  -5.500  -0.2411   0.06032   0.05820  -0.0397   0.9834   0.0312
  -5.250  -0.1802   0.05451   0.05220  -0.0548   0.9619   0.0351
  -5.000  -0.1548   0.04766   0.04522  -0.0608   0.9349   0.0363
  -4.750  -0.1352   0.04593   0.04339  -0.0608   0.8999   0.0371
  -4.500  -0.1142   0.04414   0.04144  -0.0611   0.8645   0.0383
  -4.250  -0.0881   0.04183   0.03892  -0.0630   0.8332   0.0407
  -4.000  -0.0438   0.03463   0.03127  -0.0709   0.8102   0.0458
  -3.750  -0.0210   0.03331   0.02980  -0.0710   0.7880   0.0468
  -3.500   0.0041   0.03199   0.02834  -0.0714   0.7692   0.0481
  -3.250   0.0460   0.02088   0.01630  -0.0771   0.7583   0.0461
  -3.000   0.0753   0.01416   0.00859  -0.0784   0.7462   0.0401
  -2.750   0.1029   0.01282   0.00689  -0.0782   0.7330   0.0403
  -2.500   0.1306   0.01206   0.00589  -0.0780   0.7208   0.0410
  -2.250   0.1582   0.01148   0.00511  -0.0778   0.7097   0.0420
  -2.000   0.1859   0.01092   0.00436  -0.0775   0.6991   0.0427
  -1.750   0.2138   0.01048   0.00380  -0.0773   0.6887   0.0434
  -1.500   0.2415   0.01015   0.00336  -0.0770   0.6793   0.0441
  -1.250   0.2692   0.00990   0.00301  -0.0768   0.6699   0.0447
  -1.000   0.2970   0.00945   0.00249  -0.0765   0.6607   0.0463
  -0.750   0.3246   0.00922   0.00221  -0.0763   0.6521   0.0488
  -0.500   0.3526   0.00905   0.00202  -0.0761   0.6429   0.0526
  -0.250   0.3804   0.00891   0.00185  -0.0758   0.6344   0.0584
   0.000   0.4084   0.00895   0.00200  -0.0756   0.6254   0.0862
   0.250   0.4367   0.00921   0.00222  -0.0754   0.6166   0.1010
   0.500   0.4644   0.00928   0.00223  -0.0752   0.6081   0.1080
   0.750   0.4923   0.00931   0.00227  -0.0751   0.5986   0.1138
   1.000   0.5199   0.00932   0.00224  -0.0749   0.5882   0.1188
   1.250   0.5473   0.00929   0.00220  -0.0747   0.5775   0.1250
   1.500   0.5751   0.00928   0.00219  -0.0745   0.5667   0.1290
   1.750   0.6027   0.00924   0.00214  -0.0743   0.5566   0.1327
   2.000   0.6301   0.00919   0.00210  -0.0741   0.5455   0.1380
   2.250   0.6575   0.00920   0.00208  -0.0739   0.5325   0.1409
   2.500   0.6850   0.00920   0.00207  -0.0737   0.5190   0.1424
   2.750   0.7126   0.00922   0.00208  -0.0735   0.5068   0.1439
   3.000   0.7401   0.00926   0.00212  -0.0734   0.4951   0.1454
   3.250   0.7675   0.00929   0.00215  -0.0732   0.4830   0.1484
   3.500   0.7949   0.00935   0.00222  -0.0730   0.4701   0.1522
   3.750   0.8221   0.00944   0.00231  -0.0728   0.4560   0.1574
   4.000   0.8493   0.00952   0.00242  -0.0726   0.4429   0.1696
   4.250   0.8686   0.00824   0.00267  -0.0711   0.4309   0.8867
   4.500   0.9020   0.00833   0.00278  -0.0722   0.4162   1.0000
   4.750   0.9289   0.00852   0.00293  -0.0720   0.4015   1.0000
   5.000   0.9557   0.00873   0.00310  -0.0717   0.3870   1.0000
   5.250   0.9824   0.00895   0.00328  -0.0715   0.3716   1.0000
   5.500   1.0087   0.00922   0.00347  -0.0712   0.3499   1.0000
   5.750   1.0346   0.00955   0.00371  -0.0709   0.3258   1.0000
   6.000   1.0604   0.00989   0.00397  -0.0706   0.2999   1.0000
   6.250   1.0856   0.01032   0.00427  -0.0703   0.2692   1.0000
   6.500   1.1103   0.01083   0.00462  -0.0699   0.2321   1.0000
   6.750   1.1339   0.01152   0.00509  -0.0694   0.1880   1.0000
   7.000   1.1563   0.01240   0.00568  -0.0689   0.1383   1.0000
   7.250   1.1786   0.01326   0.00631  -0.0684   0.1005   1.0000
   7.500   1.2022   0.01388   0.00687  -0.0679   0.0849   1.0000
   7.750   1.2243   0.01472   0.00755  -0.0672   0.0513   1.0000
   8.000   1.2437   0.01597   0.00859  -0.0663   0.0269   1.0000
   8.250   1.2662   0.01672   0.00942  -0.0655   0.0236   1.0000
   8.500   1.2881   0.01748   0.01025  -0.0647   0.0216   1.0000
   8.750   1.3072   0.01861   0.01146  -0.0637   0.0196   1.0000
   9.000   1.3267   0.01959   0.01254  -0.0626   0.0185   1.0000
   9.250   1.3470   0.02041   0.01344  -0.0617   0.0175   1.0000
   9.500   1.3654   0.02139   0.01450  -0.0606   0.0166   1.0000
   9.750   1.3822   0.02249   0.01567  -0.0594   0.0158   1.0000
  10.000   1.3960   0.02384   0.01709  -0.0579   0.0152   1.0000
  10.250   1.4029   0.02582   0.01919  -0.0556   0.0146   1.0000
  10.500   1.4099   0.02773   0.02121  -0.0534   0.0142   1.0000
  10.750   1.4216   0.02887   0.02246  -0.0515   0.0139   1.0000
  11.000   1.4305   0.03015   0.02385  -0.0495   0.0136   1.0000
  11.250   1.4380   0.03158   0.02539  -0.0477   0.0131   1.0000
  11.500   1.4444   0.03319   0.02709  -0.0460   0.0127   1.0000
  11.750   1.4501   0.03497   0.02897  -0.0446   0.0123   1.0000
  12.000   1.4545   0.03699   0.03112  -0.0434   0.0120   1.0000
  12.250   1.4584   0.03918   0.03340  -0.0424   0.0118   1.0000
  12.500   1.4615   0.04154   0.03587  -0.0416   0.0116   1.0000
  12.750   1.4636   0.04409   0.03852  -0.0409   0.0114   1.0000
  13.000   1.4645   0.04686   0.04139  -0.0402   0.0112   1.0000
  13.250   1.4638   0.04992   0.04456  -0.0394   0.0110   1.0000
  13.500   1.4608   0.05343   0.04821  -0.0385   0.0108   1.0000
  13.750   1.4551   0.05739   0.05235  -0.0378   0.0107   1.0000
  14.000   1.4452   0.06205   0.05722  -0.0374   0.0106   1.0000
  14.250   1.4337   0.06682   0.06218  -0.0379   0.0106   1.0000
  14.500   1.4233   0.07142   0.06697  -0.0392   0.0105   1.0000
  14.750   1.4115   0.07632   0.07205  -0.0408   0.0105   1.0000
  15.000   1.3980   0.08169   0.07760  -0.0427   0.0105   1.0000
  15.250   1.3834   0.08747   0.08355  -0.0450   0.0105   1.0000
  15.500   1.3679   0.09369   0.08996  -0.0478   0.0105   1.0000
  15.750   1.3513   0.10047   0.09691  -0.0509   0.0105   1.0000
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