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GOE 403 AIRFOIL (goe403-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 403 AIRFOIL (goe403-il)
Reynolds number: 200,000
Max Cl/Cd: 75.81 at α=4°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe403-il-200000.txt
Download as CSV file: xf-goe403-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 403 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.3332   0.08938   0.08607  -0.0259   1.0000   0.0352
  -7.250  -0.3357   0.08716   0.08393  -0.0257   1.0000   0.0361
  -7.000  -0.3394   0.08506   0.08190  -0.0259   1.0000   0.0372
  -6.750  -0.3392   0.08292   0.07983  -0.0286   1.0000   0.0381
  -6.500  -0.3371   0.08074   0.07771  -0.0320   1.0000   0.0386
  -6.250  -0.3362   0.07855   0.07555  -0.0336   1.0000   0.0389
  -6.000  -0.3380   0.07647   0.07351  -0.0337   1.0000   0.0390
  -5.750  -0.3331   0.07372   0.07074  -0.0350   0.9996   0.0391
  -5.500  -0.3099   0.06569   0.06269  -0.0415   0.9951   0.0402
  -5.250  -0.2880   0.06212   0.05911  -0.0428   0.9905   0.0420
  -5.000  -0.2525   0.05819   0.05507  -0.0490   0.9854   0.0478
  -4.750  -0.1955   0.05015   0.04670  -0.0643   0.9793   0.0531
  -4.500  -0.1697   0.04721   0.04377  -0.0660   0.9737   0.0558
  -4.250  -0.1104   0.04096   0.03690  -0.0773   0.9696   0.0656
  -4.000  -0.0877   0.03791   0.03398  -0.0782   0.9627   0.0684
  -3.750  -0.0460   0.03421   0.02997  -0.0832   0.9581   0.0808
  -3.500   0.0036   0.02310   0.01740  -0.0882   0.9551   0.0527
  -3.250   0.0350   0.02088   0.01501  -0.0896   0.9476   0.0565
  -3.000   0.0761   0.01889   0.01250  -0.0921   0.9439   0.0623
  -2.750   0.1123   0.01749   0.01060  -0.0933   0.9374   0.0649
  -2.500   0.1478   0.01566   0.00861  -0.0949   0.9314   0.0694
  -2.250   0.1824   0.01462   0.00738  -0.0959   0.9240   0.0727
  -2.000   0.2174   0.01377   0.00635  -0.0969   0.9164   0.0766
  -1.750   0.2480   0.01297   0.00549  -0.0971   0.9064   0.0815
  -1.500   0.2794   0.01252   0.00500  -0.0975   0.8964   0.0901
  -1.250   0.3097   0.01187   0.00438  -0.0976   0.8860   0.1021
  -1.000   0.3380   0.01131   0.00387  -0.0973   0.8739   0.1337
  -0.750   0.3648   0.01092   0.00357  -0.0968   0.8606   0.1709
  -0.500   0.3912   0.01064   0.00339  -0.0962   0.8467   0.2100
  -0.250   0.4161   0.01016   0.00330  -0.0956   0.8324   0.3224
   0.000   0.4562   0.00854   0.00312  -0.0977   0.8184   1.0000
   0.250   0.4812   0.00864   0.00304  -0.0967   0.8012   1.0000
   0.500   0.5063   0.00873   0.00298  -0.0958   0.7834   1.0000
   0.750   0.5316   0.00882   0.00292  -0.0950   0.7653   1.0000
   1.000   0.5566   0.00891   0.00288  -0.0941   0.7456   1.0000
   1.250   0.5817   0.00901   0.00285  -0.0933   0.7251   1.0000
   1.500   0.6069   0.00911   0.00285  -0.0925   0.7044   1.0000
   1.750   0.6321   0.00924   0.00286  -0.0917   0.6838   1.0000
   2.000   0.6575   0.00941   0.00290  -0.0910   0.6644   1.0000
   2.250   0.6828   0.00959   0.00298  -0.0904   0.6456   1.0000
   2.500   0.7083   0.00980   0.00312  -0.0898   0.6288   1.0000
   2.750   0.7338   0.01004   0.00327  -0.0892   0.6135   1.0000
   3.000   0.7587   0.01026   0.00341  -0.0885   0.5946   1.0000
   3.250   0.7820   0.01049   0.00350  -0.0874   0.5668   1.0000
   3.500   0.8065   0.01073   0.00369  -0.0867   0.5476   1.0000
   3.750   0.8293   0.01098   0.00385  -0.0856   0.5182   1.0000
   4.000   0.8514   0.01123   0.00397  -0.0843   0.4806   1.0000
   4.500   0.8956   0.01190   0.00438  -0.0819   0.3916   1.0000
   4.750   0.9119   0.01290   0.00476  -0.0800   0.2695   1.0000
   5.000   0.9159   0.01579   0.00628  -0.0769   0.0368   1.0000
   5.250   0.9387   0.01641   0.00705  -0.0758   0.0314   1.0000
   5.500   0.9605   0.01714   0.00793  -0.0746   0.0288   1.0000
   5.750   0.9807   0.01804   0.00902  -0.0732   0.0275   1.0000
   6.000   0.9984   0.01916   0.01031  -0.0714   0.0270   1.0000
   6.250   1.0143   0.02042   0.01166  -0.0694   0.0269   1.0000
   6.500   1.0256   0.02233   0.01362  -0.0668   0.0260   1.0000
   6.750   1.0444   0.02349   0.01488  -0.0652   0.0249   1.0000
   7.000   1.0633   0.02540   0.01679  -0.0636   0.0252   1.0000
   7.250   1.0895   0.02819   0.01955  -0.0630   0.0261   1.0000
   7.500   1.1140   0.02861   0.02013  -0.0617   0.0278   1.0000
   7.750   1.1506   0.03252   0.02428  -0.0616   0.0349   1.0000
  14.500   0.8208   0.16851   0.16563  -0.0791   0.0575   1.0000
  14.750   0.8164   0.17321   0.17032  -0.0823   0.0543   1.0000
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