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GOE 374 AIRFOIL (goe374-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 374 AIRFOIL (goe374-il)
Reynolds number: 1,000,000
Max Cl/Cd: 117.64 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe374-il-1000000.txt
Download as CSV file: xf-goe374-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 374 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
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.2788   0.08728   0.08580  -0.0183   1.0000   0.0067
  -8.500  -0.2752   0.08416   0.08269  -0.0186   1.0000   0.0069
  -8.250  -0.2723   0.08102   0.07957  -0.0190   1.0000   0.0069
  -8.000  -0.2695   0.07810   0.07666  -0.0193   1.0000   0.0072
  -7.750  -0.2678   0.07508   0.07366  -0.0197   1.0000   0.0074
  -7.500  -0.2670   0.07216   0.07076  -0.0198   1.0000   0.0076
  -7.250  -0.2678   0.06934   0.06796  -0.0197   1.0000   0.0078
  -7.000  -0.2719   0.06682   0.06548  -0.0190   1.0000   0.0086
  -6.750  -0.2704   0.06361   0.06229  -0.0206   0.9976   0.0088
  -6.500  -0.2503   0.05867   0.05733  -0.0287   0.9900   0.0093
  -6.250  -0.3046   0.07073   0.06930  -0.0274   0.9960   0.0090
  -6.000  -0.2677   0.06587   0.06438  -0.0369   0.9901   0.0093
  -5.750  -0.2329   0.06106   0.05950  -0.0447   0.9848   0.0094
  -5.500  -0.2002   0.05664   0.05501  -0.0508   0.9783   0.0094
  -5.250  -0.1653   0.05216   0.05044  -0.0566   0.9726   0.0094
  -5.000  -0.1391   0.04693   0.04515  -0.0612   0.9644   0.0098
  -4.750  -0.1064   0.04355   0.04168  -0.0655   0.9541   0.0100
  -4.500  -0.0762   0.04048   0.03849  -0.0685   0.9379   0.0104
  -4.250  -0.0496   0.03764   0.03550  -0.0701   0.9192   0.0109
  -4.000  -0.0245   0.03494   0.03262  -0.0707   0.9003   0.0118
  -3.750   0.0076   0.03215   0.02954  -0.0705   0.8822   0.0129
  -3.500   0.0323   0.02929   0.02645  -0.0700   0.8643   0.0129
  -3.250   0.0512   0.02545   0.02237  -0.0697   0.8461   0.0135
  -2.750   0.0976   0.02277   0.01935  -0.0688   0.8058   0.0151
  -2.500   0.1276   0.02197   0.01823  -0.0672   0.7826   0.0172
  -2.250   0.1519   0.02010   0.01606  -0.0661   0.7531   0.0173
  -0.750   0.3007   0.01346   0.00773  -0.0609   0.5932   0.0233
  -0.500   0.3250   0.01116   0.00524  -0.0603   0.5775   0.0250
  -0.250   0.3509   0.01087   0.00487  -0.0600   0.5568   0.0274
   0.000   0.3781   0.01153   0.00537  -0.0595   0.5297   0.0311
   1.250   0.5057   0.00904   0.00238  -0.0571   0.4255   0.0492
   1.500   0.5319   0.00884   0.00210  -0.0564   0.4150   0.0390
   1.750   0.5579   0.00867   0.00188  -0.0559   0.4045   0.0370
   2.000   0.5841   0.00860   0.00175  -0.0555   0.3939   0.0363
   2.250   0.6103   0.00857   0.00166  -0.0551   0.3842   0.0351
   2.500   0.6370   0.00856   0.00160  -0.0548   0.3738   0.0339
   2.750   0.6635   0.00856   0.00158  -0.0545   0.3643   0.0335
   3.000   0.6899   0.00858   0.00155  -0.0542   0.3554   0.0346
   3.250   0.7166   0.00859   0.00154  -0.0539   0.3465   0.0367
   3.500   0.7432   0.00865   0.00157  -0.0537   0.3376   0.0384
   3.750   0.7696   0.00874   0.00164  -0.0534   0.3275   0.0395
   4.000   0.7962   0.00882   0.00170  -0.0532   0.3174   0.0411
   4.250   0.8226   0.00892   0.00180  -0.0529   0.3069   0.0486
   4.500   0.8729   0.00742   0.00215  -0.0588   0.2908   1.0000
   4.750   0.8975   0.00766   0.00230  -0.0583   0.2711   1.0000
   5.000   0.9225   0.00787   0.00245  -0.0577   0.2563   1.0000
   5.250   0.9469   0.00814   0.00263  -0.0572   0.2345   1.0000
   5.500   0.9710   0.00844   0.00283  -0.0566   0.2141   1.0000
   5.750   0.9947   0.00880   0.00306  -0.0559   0.1893   1.0000
   6.000   1.0170   0.00931   0.00339  -0.0551   0.1523   1.0000
   6.250   1.0394   0.00982   0.00373  -0.0542   0.1256   1.0000
   6.500   1.0626   0.01023   0.00405  -0.0535   0.1089   1.0000
   6.750   1.0847   0.01076   0.00441  -0.0527   0.0815   1.0000
   7.000   1.0998   0.01217   0.00542  -0.0508   0.0147   1.0000
   7.250   1.1233   0.01254   0.00587  -0.0501   0.0130   1.0000
   7.500   1.1461   0.01300   0.00640  -0.0493   0.0116   1.0000
   7.750   1.1678   0.01360   0.00709  -0.0482   0.0102   1.0000
   8.000   1.1875   0.01443   0.00807  -0.0469   0.0092   1.0000
   8.250   1.2105   0.01480   0.00848  -0.0462   0.0086   1.0000
   8.500   1.2319   0.01535   0.00910  -0.0452   0.0079   1.0000
   8.750   1.2523   0.01601   0.00983  -0.0441   0.0074   1.0000
   9.000   1.2716   0.01673   0.01063  -0.0429   0.0070   1.0000
   9.250   1.2893   0.01760   0.01159  -0.0414   0.0067   1.0000
   9.500   1.3037   0.01871   0.01281  -0.0396   0.0062   1.0000
   9.750   1.3036   0.02103   0.01531  -0.0357   0.0058   1.0000
  10.000   1.3192   0.02184   0.01621  -0.0341   0.0057   1.0000
  10.250   1.3337   0.02270   0.01714  -0.0323   0.0055   1.0000
  10.500   1.3457   0.02367   0.01821  -0.0302   0.0052   1.0000
  10.750   1.3529   0.02474   0.01937  -0.0273   0.0050   1.0000
  11.000   1.3583   0.02577   0.02048  -0.0243   0.0048   1.0000
  11.250   1.3589   0.02725   0.02205  -0.0210   0.0047   1.0000
  11.500   1.3644   0.02843   0.02333  -0.0187   0.0045   1.0000
  11.750   1.3659   0.03005   0.02504  -0.0165   0.0044   1.0000
  12.000   1.3654   0.03202   0.02713  -0.0144   0.0043   1.0000
  12.250   1.3663   0.03402   0.02923  -0.0130   0.0043   1.0000
  12.500   1.3631   0.03667   0.03199  -0.0117   0.0042   1.0000
  12.750   1.3615   0.03931   0.03474  -0.0110   0.0041   1.0000
  13.000   1.3617   0.04188   0.03742  -0.0109   0.0041   1.0000
  13.250   1.3574   0.04522   0.04089  -0.0109   0.0040   1.0000
  13.500   1.3532   0.04875   0.04454  -0.0113   0.0040   1.0000
  13.750   1.3488   0.05245   0.04834  -0.0123   0.0039   1.0000
  14.000   1.3426   0.05649   0.05251  -0.0133   0.0039   1.0000
  14.250   1.3386   0.06038   0.05648  -0.0150   0.0038   1.0000
  14.500   1.3277   0.06529   0.06156  -0.0160   0.0039   1.0000
  14.750   1.3200   0.06991   0.06626  -0.0181   0.0038   1.0000
  15.000   1.3080   0.07522   0.07169  -0.0200   0.0037   1.0000
  15.250   1.2986   0.08056   0.07718  -0.0223   0.0037   1.0000
  15.500   1.2821   0.08688   0.08362  -0.0247   0.0036   1.0000
  15.750   1.2704   0.09291   0.08977  -0.0276   0.0036   1.0000
  16.000   1.2586   0.09917   0.09615  -0.0307   0.0036   1.0000
  16.250   1.2505   0.10509   0.10220  -0.0341   0.0037   1.0000
  16.500   1.2380   0.11198   0.10922  -0.0377   0.0037   1.0000
  16.750   1.2210   0.11965   0.11700  -0.0417   0.0036   1.0000
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