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GOE 371 AIRFOIL (goe371-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 371 AIRFOIL (goe371-il)
Reynolds number: 200,000
Max Cl/Cd: 79.97 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe371-il-200000-n5.txt
Download as CSV file: xf-goe371-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 371 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
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3223   0.09638   0.09304  -0.0312   1.0000   0.0204
  -7.750  -0.3281   0.09438   0.09112  -0.0297   1.0000   0.0204
  -7.500  -0.3348   0.09250   0.08932  -0.0281   1.0000   0.0204
  -7.250  -0.3172   0.08792   0.08474  -0.0333   0.9953   0.0204
  -7.000  -0.2963   0.08314   0.07995  -0.0388   0.9892   0.0203
  -6.750  -0.2823   0.07907   0.07589  -0.0385   0.9861   0.0194
  -6.500  -0.2607   0.07452   0.07133  -0.0443   0.9787   0.0186
  -6.250  -0.2326   0.06944   0.06620  -0.0530   0.9703   0.0194
  -6.000  -0.1987   0.06367   0.06036  -0.0631   0.9629   0.0198
  -5.750  -0.1702   0.05891   0.05554  -0.0693   0.9547   0.0193
  -5.500  -0.1381   0.05365   0.05017  -0.0767   0.9451   0.0191
  -5.250  -0.0990   0.04746   0.04378  -0.0855   0.9376   0.0195
  -5.000  -0.0681   0.04302   0.03918  -0.0906   0.9269   0.0217
  -4.750  -0.0391   0.04018   0.03620  -0.0936   0.9181   0.0232
  -4.500  -0.0050   0.03539   0.03111  -0.0978   0.9097   0.0236
  -4.250   0.0251   0.03137   0.02676  -0.1001   0.8994   0.0250
  -4.000   0.0575   0.02687   0.02169  -0.1019   0.8905   0.0275
  -3.750   0.0864   0.02318   0.01737  -0.1027   0.8818   0.0290
  -3.500   0.1116   0.02202   0.01615  -0.1031   0.8723   0.0313
  -3.250   0.1395   0.02046   0.01427  -0.1033   0.8635   0.0332
  -3.000   0.1672   0.01869   0.01209  -0.1031   0.8540   0.0341
  -2.750   0.1945   0.01752   0.01059  -0.1028   0.8439   0.0361
  -2.500   0.2222   0.01653   0.00926  -0.1025   0.8353   0.0373
  -2.250   0.2495   0.01560   0.00806  -0.1022   0.8270   0.0378
  -2.000   0.2768   0.01488   0.00713  -0.1018   0.8190   0.0382
  -1.750   0.3041   0.01429   0.00636  -0.1015   0.8107   0.0386
  -1.500   0.3304   0.01344   0.00540  -0.1011   0.8020   0.0402
  -1.250   0.3573   0.01291   0.00480  -0.1008   0.7943   0.0416
  -1.000   0.3836   0.01250   0.00434  -0.1003   0.7856   0.0416
  -0.750   0.4102   0.01216   0.00394  -0.0999   0.7774   0.0419
  -0.500   0.4366   0.01187   0.00361  -0.0994   0.7681   0.0423
  -0.250   0.4629   0.01165   0.00335  -0.0989   0.7587   0.0430
   0.000   0.4895   0.01149   0.00312  -0.0985   0.7495   0.0440
   0.250   0.5159   0.01137   0.00296  -0.0980   0.7394   0.0453
   0.500   0.5423   0.01128   0.00282  -0.0976   0.7292   0.0474
   0.750   0.5687   0.01123   0.00271  -0.0971   0.7183   0.0501
   1.000   0.5950   0.01118   0.00264  -0.0966   0.7062   0.0564
   1.250   0.6179   0.01036   0.00278  -0.0960   0.6926   0.3968
   1.750   0.6839   0.00931   0.00273  -0.0979   0.6506   1.0000
   2.000   0.7083   0.00945   0.00270  -0.0969   0.6197   1.0000
   2.250   0.7323   0.00965   0.00270  -0.0960   0.5864   1.0000
   2.500   0.7558   0.00990   0.00274  -0.0950   0.5573   1.0000
   2.750   0.7794   0.01019   0.00284  -0.0940   0.5332   1.0000
   3.000   0.8033   0.01049   0.00300  -0.0932   0.5130   1.0000
   3.250   0.8278   0.01076   0.00318  -0.0925   0.4970   1.0000
   3.500   0.8525   0.01102   0.00337  -0.0919   0.4843   1.0000
   3.750   0.8774   0.01128   0.00358  -0.0913   0.4733   1.0000
   4.000   0.9026   0.01151   0.00382  -0.0908   0.4625   1.0000
   4.250   0.9275   0.01176   0.00405  -0.0902   0.4514   1.0000
   4.500   0.9521   0.01202   0.00430  -0.0896   0.4395   1.0000
   4.750   0.9766   0.01229   0.00458  -0.0890   0.4276   1.0000
   5.000   1.0010   0.01255   0.00486  -0.0883   0.4143   1.0000
   5.250   1.0249   0.01283   0.00514  -0.0876   0.3978   1.0000
   5.500   1.0484   0.01311   0.00544  -0.0868   0.3761   1.0000
   5.750   1.0710   0.01345   0.00576  -0.0859   0.3486   1.0000
   6.000   1.0925   0.01387   0.00609  -0.0849   0.3135   1.0000
   6.250   1.1122   0.01445   0.00651  -0.0836   0.2721   1.0000
   6.500   1.1311   0.01515   0.00703  -0.0823   0.2378   1.0000
   6.750   1.1497   0.01589   0.00765  -0.0809   0.2089   1.0000
   7.000   1.1682   0.01664   0.00827  -0.0796   0.1821   1.0000
   7.250   1.1878   0.01729   0.00885  -0.0785   0.1580   1.0000
   7.500   1.2075   0.01791   0.00944  -0.0773   0.1378   1.0000
   7.750   1.2257   0.01867   0.01007  -0.0760   0.1054   1.0000
   8.000   1.2408   0.01970   0.01092  -0.0743   0.0722   1.0000
   8.250   1.2535   0.02096   0.01199  -0.0722   0.0410   1.0000
   8.500   1.2647   0.02233   0.01319  -0.0699   0.0209   1.0000
   8.750   1.2788   0.02336   0.01430  -0.0679   0.0177   1.0000
   9.000   1.2911   0.02451   0.01560  -0.0656   0.0155   1.0000
   9.250   1.3014   0.02562   0.01688  -0.0631   0.0142   1.0000
   9.500   1.3115   0.02664   0.01806  -0.0606   0.0132   1.0000
   9.750   1.3194   0.02781   0.01938  -0.0579   0.0124   1.0000
  10.000   1.3249   0.02916   0.02092  -0.0552   0.0117   1.0000
  10.250   1.3292   0.03064   0.02255  -0.0525   0.0113   1.0000
  10.500   1.3316   0.03235   0.02439  -0.0499   0.0108   1.0000
  10.750   1.3327   0.03424   0.02643  -0.0474   0.0105   1.0000
  11.000   1.3323   0.03639   0.02871  -0.0452   0.0102   1.0000
  11.250   1.3293   0.03894   0.03139  -0.0431   0.0099   1.0000
  11.500   1.3246   0.04193   0.03450  -0.0412   0.0095   1.0000
  11.750   1.3300   0.04384   0.03659  -0.0401   0.0090   1.0000
  12.000   1.3316   0.04632   0.03923  -0.0389   0.0088   1.0000
  12.250   1.3332   0.04884   0.04192  -0.0381   0.0085   1.0000
  12.500   1.3332   0.05169   0.04494  -0.0373   0.0083   1.0000
  12.750   1.3320   0.05478   0.04820  -0.0367   0.0080   1.0000
  13.000   1.3302   0.05804   0.05167  -0.0364   0.0079   1.0000
  13.250   1.3270   0.06157   0.05538  -0.0363   0.0077   1.0000
  13.500   1.3229   0.06535   0.05934  -0.0365   0.0076   1.0000
  13.750   1.3173   0.06945   0.06363  -0.0370   0.0075   1.0000
  14.000   1.3107   0.07388   0.06826  -0.0380   0.0075   1.0000
  14.250   1.3027   0.07871   0.07328  -0.0394   0.0074   1.0000
  14.500   1.2936   0.08391   0.07868  -0.0412   0.0073   1.0000
  14.750   1.2836   0.08953   0.08448  -0.0434   0.0073   1.0000
  15.000   1.2724   0.09559   0.09074  -0.0462   0.0072   1.0000
  15.250   1.2604   0.10205   0.09739  -0.0493   0.0072   1.0000
  15.500   1.2475   0.10895   0.10448  -0.0529   0.0072   1.0000
  15.750   1.2339   0.11629   0.11201  -0.0570   0.0072   1.0000
  16.000   1.2196   0.12413   0.12003  -0.0615   0.0072   1.0000
  16.250   1.2042   0.13264   0.12873  -0.0666   0.0073   1.0000
  16.500   1.1881   0.14189   0.13815  -0.0724   0.0074   1.0000
  16.750   1.1711   0.15207   0.14850  -0.0788   0.0075   1.0000
  17.000   1.1520   0.16359   0.16018  -0.0860   0.0077   1.0000
  17.250   1.1305   0.17674   0.17342  -0.0940   0.0079   1.0000
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