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GOE 376 AIRFOIL (goe376-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 376 AIRFOIL (goe376-il)
Reynolds number: 50,000
Max Cl/Cd: 33.79 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe376-il-50000.txt
Download as CSV file: xf-goe376-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 376 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3310   0.11218   0.10523  -0.0206   1.0000   0.0990
  -8.500  -0.3357   0.11152   0.10469  -0.0219   1.0000   0.1013
  -8.250  -0.3459   0.11170   0.10501  -0.0230   1.0000   0.1021
  -8.000  -0.3271   0.10472   0.09801  -0.0215   1.0000   0.1056
  -7.750  -0.3224   0.10169   0.09505  -0.0208   1.0000   0.1105
  -7.500  -0.3264   0.10025   0.09373  -0.0208   1.0000   0.1139
  -7.250  -0.3323   0.10000   0.09361  -0.0237   1.0000   0.1161
  -7.000  -0.3232   0.09484   0.08851  -0.0211   1.0000   0.1209
  -6.750  -0.3198   0.09234   0.08609  -0.0210   1.0000   0.1268
  -6.500  -0.3221   0.09239   0.08623  -0.0262   1.0000   0.1309
  -6.250  -0.3151   0.08723   0.08116  -0.0221   1.0000   0.1356
  -6.000  -0.3114   0.08490   0.07890  -0.0223   1.0000   0.1424
  -5.750  -0.3084   0.08348   0.07754  -0.0261   1.0000   0.1470
  -5.500  -0.3042   0.07957   0.07371  -0.0219   1.0000   0.1537
  -5.000  -0.2961   0.07464   0.06890  -0.0219   1.0000   0.1689
  -4.750  -0.2899   0.07247   0.06672  -0.0236   1.0000   0.1780
  -4.500  -0.2814   0.07068   0.06491  -0.0254   1.0000   0.1911
  -4.250  -0.2748   0.06832   0.06256  -0.0251   1.0000   0.2057
  -4.000  -0.2705   0.06545   0.05975  -0.0234   1.0000   0.2211
  -3.750  -0.2671   0.06257   0.05695  -0.0210   1.0000   0.2381
  -3.500  -0.2580   0.06065   0.05501  -0.0215   1.0000   0.2655
  -3.250  -0.2557   0.05772   0.05219  -0.0179   1.0000   0.2859
  -3.000  -0.2497   0.05565   0.05014  -0.0168   1.0000   0.3265
  -2.750  -0.2497   0.05307   0.04767  -0.0123   1.0000   0.3619
  -2.250  -0.2552   0.04877   0.04360  -0.0020   1.0000   0.4760
  -2.000  -0.2588   0.04633   0.04130   0.0044   1.0000   0.5229
  -1.750  -0.2609   0.04412   0.03922   0.0102   1.0000   0.5690
  -1.500  -0.2612   0.04204   0.03724   0.0155   1.0000   0.6137
  -1.250  -0.2613   0.03992   0.03523   0.0208   1.0000   0.6520
  -1.000  -0.2527   0.03793   0.03328   0.0230   1.0000   0.6837
  -0.750  -0.2320   0.03612   0.03144   0.0213   1.0000   0.7041
  -0.500  -0.1436   0.03411   0.02914   0.0040   0.9850   0.7013
  -0.250   0.0963   0.03582   0.02817  -0.0517   0.9615   0.3378
   0.000   0.1711   0.03530   0.02672  -0.0598   0.9452   0.2448
   0.250   0.2316   0.03463   0.02540  -0.0650   0.9289   0.2012
   0.500   0.2810   0.03395   0.02427  -0.0683   0.9110   0.1794
   0.750   0.3289   0.03332   0.02332  -0.0715   0.8935   0.1672
   1.000   0.3818   0.03276   0.02240  -0.0753   0.8763   0.1637
   1.250   0.4376   0.03218   0.02151  -0.0794   0.8596   0.1615
   1.500   0.4943   0.03136   0.02054  -0.0835   0.8434   0.1605
   1.750   0.5490   0.03044   0.01961  -0.0871   0.8274   0.1638
   2.000   0.5995   0.02962   0.01876  -0.0897   0.8111   0.1733
   2.250   0.6347   0.02923   0.01849  -0.0901   0.7916   0.1979
   2.500   0.6922   0.02707   0.01782  -0.0940   0.7735   1.0000
   2.750   0.7285   0.02702   0.01739  -0.0937   0.7556   1.0000
   3.000   0.7636   0.02694   0.01704  -0.0934   0.7381   1.0000
   3.250   0.7972   0.02689   0.01680  -0.0929   0.7209   1.0000
   3.500   0.8184   0.02746   0.01732  -0.0912   0.7006   1.0000
   3.750   0.8452   0.02772   0.01750  -0.0900   0.6818   1.0000
   4.000   0.8736   0.02789   0.01758  -0.0888   0.6635   1.0000
   4.250   0.9020   0.02804   0.01764  -0.0876   0.6453   1.0000
   4.500   0.9217   0.02874   0.01839  -0.0859   0.6246   1.0000
   4.750   0.9473   0.02904   0.01865  -0.0844   0.6051   1.0000
   5.000   0.9753   0.02922   0.01875  -0.0831   0.5867   1.0000
   5.250   0.9946   0.02999   0.01957  -0.0814   0.5658   1.0000
   5.500   1.0183   0.03052   0.02013  -0.0799   0.5464   1.0000
   5.750   1.0445   0.03091   0.02047  -0.0786   0.5281   1.0000
   6.000   1.0661   0.03172   0.02132  -0.0771   0.5097   1.0000
   6.250   1.0856   0.03274   0.02242  -0.0755   0.4915   1.0000
   6.500   1.1065   0.03373   0.02352  -0.0741   0.4747   1.0000
   6.750   1.1271   0.03484   0.02471  -0.0727   0.4589   1.0000
   7.000   1.1468   0.03609   0.02607  -0.0713   0.4440   1.0000
   7.250   1.1650   0.03757   0.02770  -0.0700   0.4304   1.0000
   7.500   1.1836   0.03906   0.02933  -0.0686   0.4175   1.0000
   7.750   1.2045   0.04039   0.03082  -0.0674   0.4052   1.0000
   8.000   1.2229   0.04199   0.03260  -0.0661   0.3936   1.0000
   8.250   1.2242   0.04513   0.03611  -0.0640   0.3837   1.0000
   8.500   1.2405   0.04710   0.03825  -0.0627   0.3743   1.0000
   8.750   1.2565   0.04889   0.04025  -0.0613   0.3640   1.0000
   9.000   1.2426   0.05337   0.04506  -0.0587   0.3562   1.0000
   9.250   1.2605   0.05440   0.04631  -0.0570   0.3437   1.0000
   9.500   1.2311   0.06058   0.05267  -0.0546   0.3392   1.0000
   9.750   1.3497   0.04584   0.03756  -0.0531   0.2869   1.0000
  10.000   1.3667   0.04308   0.03474  -0.0497   0.2564   1.0000
  10.250   1.3713   0.04194   0.03357  -0.0457   0.2283   1.0000
  10.500   1.3646   0.04229   0.03394  -0.0410   0.1998   1.0000
  10.750   1.3476   0.04380   0.03541  -0.0357   0.1707   1.0000
  11.000   1.3284   0.04592   0.03725  -0.0307   0.1463   1.0000
  11.250   1.3150   0.04893   0.04025  -0.0273   0.1282   1.0000
  11.500   1.3067   0.05200   0.04325  -0.0250   0.1148   1.0000
  11.750   1.3033   0.05497   0.04611  -0.0232   0.1050   1.0000
  12.000   1.2990   0.05822   0.04950  -0.0219   0.0975   1.0000
  12.250   1.2986   0.06154   0.05289  -0.0208   0.0915   1.0000
  12.500   1.2952   0.06533   0.05693  -0.0201   0.0871   1.0000
  12.750   1.3097   0.06801   0.05945  -0.0187   0.0821   1.0000
  13.000   1.2990   0.07284   0.06467  -0.0186   0.0810   1.0000
  13.250   1.2848   0.07817   0.07032  -0.0193   0.0804   1.0000
  13.500   1.2663   0.08419   0.07664  -0.0209   0.0803   1.0000
  13.750   1.2446   0.09101   0.08370  -0.0234   0.0806   1.0000
  14.000   1.2213   0.09852   0.09142  -0.0269   0.0812   1.0000
  14.250   1.1966   0.10687   0.09992  -0.0312   0.0818   1.0000
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