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GOE 372 AIRFOIL (goe372-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 372 AIRFOIL (goe372-il)
Reynolds number: 1,000,000
Max Cl/Cd: 126.47 at α=1.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe372-il-1000000.txt
Download as CSV file: xf-goe372-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 372 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
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.2822   0.09826   0.09673  -0.0297   1.0000   0.0102
  -9.500  -0.2803   0.09488   0.09336  -0.0301   1.0000   0.0108
  -7.000  -0.3249   0.07114   0.06968  -0.0436   0.9912   0.0110
  -6.750  -0.2945   0.01264   0.00876  -0.1012   0.9729   0.0087
  -6.500  -0.2609   0.01179   0.00777  -0.1028   0.9702   0.0099
  -6.250  -0.2322   0.01117   0.00703  -0.1031   0.9635   0.0109
  -6.000  -0.2005   0.01056   0.00629  -0.1040   0.9578   0.0119
  -5.750  -0.1717   0.00962   0.00512  -0.1042   0.9492   0.0132
  -5.500  -0.1411   0.00929   0.00477  -0.1048   0.9399   0.0159
  -5.250  -0.1115   0.00926   0.00468  -0.1050   0.9283   0.0180
  -5.000  -0.0844   0.00882   0.00414  -0.1049   0.9144   0.0212
  -4.750  -0.0566   0.00892   0.00423  -0.1047   0.9005   0.0239
  -4.500  -0.0293   0.00895   0.00418  -0.1045   0.8870   0.0260
  -4.250  -0.0021   0.00906   0.00423  -0.1042   0.8741   0.0270
  -4.000   0.0232   0.00839   0.00335  -0.1037   0.8616   0.0293
  -3.750   0.0492   0.00803   0.00290  -0.1033   0.8501   0.0317
  -3.500   0.0757   0.00784   0.00263  -0.1029   0.8395   0.0335
  -3.250   0.1024   0.00770   0.00241  -0.1026   0.8299   0.0357
  -3.000   0.1292   0.00758   0.00222  -0.1023   0.8205   0.0375
  -2.750   0.1560   0.00746   0.00202  -0.1020   0.8117   0.0382
  -2.500   0.1825   0.00723   0.00169  -0.1016   0.8033   0.0395
  -2.250   0.2092   0.00702   0.00141  -0.1013   0.7952   0.0417
  -2.000   0.2361   0.00689   0.00123  -0.1009   0.7875   0.0447
  -1.750   0.2630   0.00678   0.00110  -0.1007   0.7794   0.0491
  -1.500   0.2900   0.00667   0.00103  -0.1004   0.7718   0.0664
  -1.250   0.3170   0.00667   0.00101  -0.1002   0.7639   0.0759
  -1.000   0.3440   0.00660   0.00095  -0.0999   0.7552   0.0839
  -0.750   0.3709   0.00659   0.00090  -0.0996   0.7456   0.0889
  -0.500   0.3977   0.00656   0.00085  -0.0993   0.7358   0.0949
  -0.250   0.4247   0.00652   0.00082  -0.0991   0.7260   0.1018
   0.000   0.4515   0.00649   0.00079  -0.0988   0.7162   0.1119
   0.250   0.4782   0.00646   0.00078  -0.0985   0.7056   0.1283
   0.500   0.5046   0.00642   0.00078  -0.0982   0.6930   0.1570
   0.750   0.5309   0.00636   0.00080  -0.0979   0.6789   0.1988
   1.000   0.5563   0.00615   0.00086  -0.0975   0.6625   0.3207
   1.250   0.6013   0.00478   0.00101  -0.1019   0.6389   1.0000
   1.500   0.6260   0.00495   0.00104  -0.1012   0.6088   1.0000
   1.750   0.6490   0.00524   0.00110  -0.1002   0.5627   1.0000
   2.000   0.6725   0.00553   0.00120  -0.0992   0.5255   1.0000
   2.250   0.6971   0.00576   0.00130  -0.0986   0.4998   1.0000
   2.500   0.7218   0.00598   0.00141  -0.0979   0.4706   1.0000
   2.750   0.7433   0.00648   0.00155  -0.0968   0.3923   1.0000
   3.000   0.7541   0.00812   0.00216  -0.0940   0.1776   1.0000
   3.250   0.7698   0.00940   0.00277  -0.0919   0.0207   1.0000
   3.500   0.7951   0.00963   0.00301  -0.0913   0.0163   1.0000
   3.750   0.8200   0.00990   0.00337  -0.0907   0.0138   1.0000
   4.000   0.8447   0.01018   0.00367  -0.0900   0.0131   1.0000
   4.250   0.8690   0.01051   0.00405  -0.0893   0.0123   1.0000
   4.500   0.8928   0.01091   0.00449  -0.0884   0.0113   1.0000
   4.750   0.9157   0.01140   0.00503  -0.0874   0.0102   1.0000
   5.000   0.9375   0.01201   0.00571  -0.0862   0.0098   1.0000
   5.250   0.9580   0.01275   0.00650  -0.0847   0.0093   1.0000
   5.500   0.9749   0.01385   0.00767  -0.0827   0.0087   1.0000
   5.750   0.9900   0.01526   0.00913  -0.0804   0.0085   1.0000
   6.000   1.0069   0.01690   0.01080  -0.0785   0.0083   1.0000
   6.250   1.0318   0.01688   0.01085  -0.0778   0.0078   1.0000
   6.500   1.0546   0.01740   0.01145  -0.0768   0.0072   1.0000
   6.750   1.0755   0.01863   0.01274  -0.0754   0.0068   1.0000
   7.000   1.1045   0.02563   0.01976  -0.0754   0.0083   1.0000
   7.250   1.1264   0.02775   0.02204  -0.0743   0.0083   1.0000
   7.500   1.1464   0.02997   0.02443  -0.0729   0.0082   1.0000
   7.750   1.1647   0.03220   0.02686  -0.0713   0.0082   1.0000
   8.000   1.1812   0.03445   0.02932  -0.0695   0.0082   1.0000
   8.250   1.1956   0.03666   0.03176  -0.0675   0.0082   1.0000
   8.500   1.2080   0.03865   0.03400  -0.0652   0.0082   1.0000
   8.750   1.2201   0.03976   0.03533  -0.0628   0.0080   1.0000
   9.000   1.2411   0.03867   0.03436  -0.0611   0.0072   1.0000
   9.250   1.2524   0.04054   0.03644  -0.0587   0.0067   1.0000
   9.500   1.2599   0.04278   0.03890  -0.0562   0.0063   1.0000
   9.750   1.2646   0.04509   0.04139  -0.0535   0.0061   1.0000
  10.000   1.2659   0.04753   0.04401  -0.0507   0.0059   1.0000
  10.250   1.2646   0.04987   0.04650  -0.0477   0.0057   1.0000
  10.500   1.2562   0.05221   0.04900  -0.0438   0.0056   1.0000
  10.750   1.2445   0.05432   0.05123  -0.0398   0.0055   1.0000
  11.000   1.2306   0.05686   0.05391  -0.0364   0.0055   1.0000
  11.250   1.2161   0.05974   0.05692  -0.0340   0.0054   1.0000
  11.500   1.2001   0.06313   0.06045  -0.0325   0.0054   1.0000
  11.750   1.1858   0.06666   0.06409  -0.0319   0.0054   1.0000
  12.000   1.1659   0.07140   0.06899  -0.0322   0.0054   1.0000
  12.250   1.1463   0.07670   0.07443  -0.0335   0.0054   1.0000
  12.500   1.1268   0.08255   0.08042  -0.0359   0.0054   1.0000
  12.750   1.1034   0.09006   0.08808  -0.0398   0.0054   1.0000
  13.000   1.0822   0.09798   0.09613  -0.0447   0.0055   1.0000
  13.250   1.0579   0.10794   0.10623  -0.0513   0.0055   1.0000
  13.500   1.0275   0.12257   0.12101  -0.0613   0.0057   1.0000
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