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GOE 374 AIRFOIL (goe374-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 374 AIRFOIL (goe374-il)
Reynolds number: 200,000
Max Cl/Cd: 74.55 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe374-il-200000-n5.txt
Download as CSV file: xf-goe374-il-200000-n5.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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3225   0.10317   0.09979  -0.0219   1.0000   0.0144
  -8.000  -0.3213   0.10093   0.09760  -0.0225   1.0000   0.0144
  -7.750  -0.3221   0.09874   0.09548  -0.0228   1.0000   0.0144
  -7.500  -0.3186   0.09619   0.09297  -0.0240   1.0000   0.0145
  -7.250  -0.3137   0.09346   0.09029  -0.0254   1.0000   0.0145
  -7.000  -0.3083   0.09072   0.08759  -0.0267   1.0000   0.0145
  -6.750  -0.3030   0.08795   0.08485  -0.0276   1.0000   0.0145
  -6.500  -0.2981   0.08527   0.08220  -0.0281   1.0000   0.0145
  -6.250  -0.2867   0.08208   0.07901  -0.0302   0.9986   0.0145
  -6.000  -0.2737   0.07562   0.07260  -0.0314   0.9939   0.0149
  -5.750  -0.2503   0.07104   0.06801  -0.0353   0.9880   0.0152
  -5.500  -0.2236   0.06674   0.06367  -0.0403   0.9807   0.0156
  -5.250  -0.1939   0.06256   0.05943  -0.0459   0.9730   0.0161
  -5.000  -0.1594   0.05833   0.05511  -0.0523   0.9662   0.0166
  -4.750  -0.1269   0.05434   0.05103  -0.0575   0.9562   0.0176
  -4.500  -0.0931   0.05060   0.04717  -0.0625   0.9463   0.0190
  -4.250  -0.0447   0.04747   0.04378  -0.0688   0.9385   0.0214
  -4.000  -0.0089   0.04419   0.04028  -0.0722   0.9281   0.0216
  -3.750   0.0229   0.04076   0.03666  -0.0745   0.9175   0.0217
  -3.250   0.0758   0.03344   0.02905  -0.0779   0.8943   0.0202
  -3.000   0.1059   0.03016   0.02550  -0.0789   0.8814   0.0175
  -2.750   0.1357   0.02749   0.02253  -0.0793   0.8674   0.0173
  -2.500   0.1649   0.02550   0.02023  -0.0791   0.8521   0.0198
  -2.250   0.1931   0.02323   0.01761  -0.0787   0.8358   0.0199
  -2.000   0.2213   0.02116   0.01513  -0.0779   0.8186   0.0203
  -1.750   0.2491   0.01950   0.01304  -0.0770   0.8001   0.0230
  -1.500   0.2743   0.01845   0.01178  -0.0766   0.7784   0.0259
  -1.250   0.3012   0.01709   0.01003  -0.0756   0.7555   0.0269
  -1.000   0.3277   0.01616   0.00868  -0.0746   0.7292   0.0314
  -0.750   0.3532   0.01524   0.00747  -0.0738   0.7017   0.0328
  -0.500   0.3788   0.01456   0.00650  -0.0729   0.6758   0.0342
   0.000   0.4298   0.01381   0.00521  -0.0713   0.6314   0.0380
   0.250   0.4551   0.01345   0.00468  -0.0706   0.6118   0.0385
   0.500   0.4802   0.01312   0.00421  -0.0699   0.5933   0.0391
   0.750   0.5048   0.01264   0.00370  -0.0692   0.5746   0.0417
   1.000   0.5298   0.01247   0.00347  -0.0686   0.5553   0.0435
   1.250   0.5547   0.01235   0.00325  -0.0680   0.5361   0.0430
   1.500   0.5799   0.01228   0.00309  -0.0674   0.5169   0.0426
   1.750   0.6051   0.01229   0.00297  -0.0668   0.4985   0.0423
   2.000   0.6302   0.01235   0.00290  -0.0662   0.4807   0.0422
   2.250   0.6552   0.01245   0.00286  -0.0656   0.4641   0.0422
   2.500   0.6803   0.01257   0.00288  -0.0651   0.4490   0.0426
   2.750   0.7055   0.01271   0.00292  -0.0646   0.4351   0.0432
   3.000   0.7308   0.01286   0.00299  -0.0641   0.4219   0.0446
   3.250   0.7562   0.01301   0.00309  -0.0636   0.4100   0.0474
   3.500   0.7987   0.01154   0.00339  -0.0673   0.3964   1.0000
   3.750   0.8236   0.01178   0.00354  -0.0668   0.3838   1.0000
   4.000   0.8485   0.01202   0.00371  -0.0662   0.3712   1.0000
   4.250   0.8733   0.01226   0.00392  -0.0657   0.3599   1.0000
   4.500   0.8985   0.01247   0.00413  -0.0652   0.3496   1.0000
   4.750   0.9235   0.01270   0.00436  -0.0648   0.3395   1.0000
   5.000   0.9482   0.01295   0.00463  -0.0642   0.3291   1.0000
   5.250   0.9728   0.01320   0.00490  -0.0637   0.3179   1.0000
   5.500   0.9975   0.01345   0.00518  -0.0632   0.3062   1.0000
   5.750   1.0218   0.01373   0.00549  -0.0627   0.2944   1.0000
   6.000   1.0459   0.01403   0.00585  -0.0621   0.2819   1.0000
   6.250   1.0690   0.01440   0.00619  -0.0614   0.2622   1.0000
   6.500   1.0904   0.01492   0.00657  -0.0605   0.2304   1.0000
   6.750   1.1114   0.01551   0.00703  -0.0596   0.1971   1.0000
   7.000   1.1311   0.01627   0.00762  -0.0586   0.1591   1.0000
   7.250   1.1506   0.01707   0.00827  -0.0576   0.1299   1.0000
   7.500   1.1673   0.01819   0.00910  -0.0562   0.0860   1.0000
   7.750   1.1762   0.02018   0.01058  -0.0539   0.0179   1.0000
   8.000   1.1948   0.02105   0.01164  -0.0525   0.0145   1.0000
   8.250   1.2118   0.02207   0.01285  -0.0509   0.0122   1.0000
   8.500   1.2269   0.02327   0.01436  -0.0490   0.0108   1.0000
   8.750   1.2402   0.02457   0.01590  -0.0470   0.0102   1.0000
   9.000   1.2545   0.02563   0.01715  -0.0453   0.0095   1.0000
   9.250   1.2664   0.02682   0.01851  -0.0433   0.0085   1.0000
   9.500   1.2745   0.02818   0.02005  -0.0409   0.0079   1.0000
   9.750   1.2773   0.02966   0.02167  -0.0377   0.0076   1.0000
  10.000   1.2769   0.03130   0.02345  -0.0345   0.0074   1.0000
  10.250   1.2752   0.03315   0.02543  -0.0316   0.0072   1.0000
  10.500   1.2708   0.03539   0.02777  -0.0291   0.0070   1.0000
  10.750   1.2659   0.03793   0.03041  -0.0270   0.0069   1.0000
  11.000   1.2631   0.04051   0.03309  -0.0255   0.0068   1.0000
  11.250   1.2589   0.04356   0.03621  -0.0242   0.0067   1.0000
  11.500   1.2583   0.04657   0.03926  -0.0229   0.0065   1.0000
  11.750   1.2613   0.04916   0.04204  -0.0221   0.0065   1.0000
  12.000   1.2630   0.05188   0.04494  -0.0217   0.0063   1.0000
  12.250   1.2638   0.05479   0.04803  -0.0216   0.0062   1.0000
  12.500   1.2636   0.05797   0.05139  -0.0217   0.0060   1.0000
  12.750   1.2611   0.06149   0.05513  -0.0224   0.0056   1.0000
  13.000   1.2583   0.06523   0.05905  -0.0230   0.0055   1.0000
  13.250   1.2540   0.06922   0.06321  -0.0242   0.0052   1.0000
  13.500   1.2487   0.07356   0.06774  -0.0253   0.0052   1.0000
  13.750   1.2419   0.07823   0.07258  -0.0268   0.0051   1.0000
  14.000   1.2341   0.08324   0.07779  -0.0287   0.0051   1.0000
  14.250   1.2252   0.08859   0.08333  -0.0309   0.0051   1.0000
  14.500   1.2156   0.09427   0.08919  -0.0336   0.0051   1.0000
  14.750   1.2052   0.10032   0.09543  -0.0366   0.0051   1.0000
  15.000   1.1939   0.10675   0.10203  -0.0400   0.0051   1.0000
  15.250   1.1827   0.11340   0.10886  -0.0436   0.0051   1.0000
  15.500   1.1718   0.12027   0.11588  -0.0476   0.0051   1.0000
  15.750   1.1601   0.12757   0.12335  -0.0518   0.0051   1.0000
  16.000   1.1483   0.13518   0.13112  -0.0564   0.0051   1.0000
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