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GOE 328 AIRFOIL (goe328-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 328 AIRFOIL (goe328-il)
Reynolds number: 1,000,000
Max Cl/Cd: 120.66 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe328-il-1000000.txt
Download as CSV file: xf-goe328-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 328 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
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.4134   0.11040   0.10877  -0.0097   1.0000   0.0167
  -9.250  -0.4098   0.10664   0.10501  -0.0123   1.0000   0.0168
  -9.000  -0.4068   0.10203   0.10042  -0.0137   1.0000   0.0169
  -8.750  -0.3979   0.09906   0.09746  -0.0138   1.0000   0.0170
  -8.500  -0.3898   0.09632   0.09472  -0.0147   1.0000   0.0172
  -8.250  -0.3820   0.09359   0.09200  -0.0160   1.0000   0.0174
  -8.000  -0.3746   0.09083   0.08926  -0.0174   1.0000   0.0176
  -7.750  -0.3678   0.08803   0.08648  -0.0191   1.0000   0.0179
  -7.500  -0.3620   0.08519   0.08366  -0.0209   1.0000   0.0182
  -7.250  -0.3464   0.08143   0.07990  -0.0260   0.9854   0.0190
  -7.000  -0.3185   0.07479   0.07318  -0.0405   0.9536   0.0205
  -6.750  -0.3025   0.07047   0.06876  -0.0454   0.9285   0.0205
  -6.500  -0.2851   0.06629   0.06447  -0.0496   0.9088   0.0205
  -6.250  -0.2652   0.06192   0.05997  -0.0539   0.8922   0.0206
  -5.500  -0.2139   0.05211   0.04990  -0.0597   0.8495   0.0215
  -5.250  -0.1907   0.04945   0.04714  -0.0621   0.8362   0.0220
  -5.000  -0.1656   0.04649   0.04406  -0.0647   0.8234   0.0227
  -4.750  -0.1288   0.04231   0.03964  -0.0690   0.8118   0.0249
  -4.500  -0.0998   0.03895   0.03607  -0.0711   0.8003   0.0250
  -4.250  -0.0719   0.03555   0.03247  -0.0728   0.7893   0.0251
  -4.000  -0.0474   0.02948   0.02610  -0.0753   0.7796   0.0257
  -3.750  -0.0221   0.02794   0.02444  -0.0759   0.7692   0.0260
  -3.500   0.0041   0.02655   0.02294  -0.0765   0.7589   0.0264
  -3.250   0.0312   0.02511   0.02137  -0.0771   0.7489   0.0270
  -3.000   0.0591   0.02353   0.01961  -0.0776   0.7389   0.0278
  -2.750   0.0902   0.02203   0.01787  -0.0776   0.7286   0.0303
  -2.500   0.1199   0.02097   0.01657  -0.0777   0.7180   0.0307
  -2.250   0.1486   0.01950   0.01483  -0.0779   0.7067   0.0308
  -1.750  -0.0263   0.01326   0.01048  -0.1032   0.7207   0.0272
  -0.500   0.3503   0.01061   0.00456  -0.0796   0.6327   0.0313
  -0.250   0.3790   0.01013   0.00401  -0.0797   0.6226   0.0313
   0.000   0.4077   0.00970   0.00352  -0.0798   0.6123   0.0312
   0.250   0.4362   0.00929   0.00306  -0.0799   0.6011   0.0312
   0.500   0.4648   0.00875   0.00246  -0.0800   0.5886   0.0318
   0.750   0.4934   0.00851   0.00219  -0.0802   0.5744   0.0327
   1.000   0.5219   0.00841   0.00204  -0.0803   0.5580   0.0335
   1.250   0.5504   0.00834   0.00192  -0.0804   0.5384   0.0343
   1.500   0.5787   0.00834   0.00182  -0.0806   0.5141   0.0350
   1.750   0.6069   0.00838   0.00176  -0.0807   0.4882   0.0359
   2.000   0.6349   0.00847   0.00176  -0.0807   0.4661   0.0374
   2.250   0.6631   0.00852   0.00173  -0.0808   0.4488   0.0389
   2.500   0.6914   0.00855   0.00170  -0.0810   0.4351   0.0428
   2.750   0.7197   0.00861   0.00174  -0.0811   0.4238   0.0471
   3.000   0.7414   0.00670   0.00195  -0.0803   0.4153   1.0000
   3.250   0.7696   0.00686   0.00203  -0.0804   0.4059   1.0000
   3.500   0.7979   0.00698   0.00211  -0.0805   0.3973   1.0000
   3.750   0.8259   0.00713   0.00221  -0.0806   0.3880   1.0000
   4.000   0.8540   0.00728   0.00231  -0.0807   0.3781   1.0000
   4.250   0.8820   0.00741   0.00241  -0.0808   0.3678   1.0000
   4.500   0.9098   0.00759   0.00253  -0.0808   0.3536   1.0000
   4.750   0.9375   0.00777   0.00265  -0.0809   0.3400   1.0000
   5.000   0.9648   0.00800   0.00279  -0.0809   0.3204   1.0000
   5.250   0.9918   0.00827   0.00296  -0.0809   0.3003   1.0000
   5.500   1.0190   0.00851   0.00313  -0.0809   0.2844   1.0000
   5.750   1.0459   0.00876   0.00332  -0.0809   0.2694   1.0000
   6.000   1.0726   0.00905   0.00354  -0.0809   0.2522   1.0000
   6.250   1.0991   0.00934   0.00377  -0.0808   0.2362   1.0000
   6.500   1.1253   0.00968   0.00403  -0.0807   0.2183   1.0000
   6.750   1.1509   0.01008   0.00432  -0.0805   0.1946   1.0000
   7.000   1.1678   0.01173   0.00533  -0.0794   0.0830   1.0000
   7.250   1.1895   0.01265   0.00601  -0.0787   0.0433   1.0000
   7.500   1.2133   0.01323   0.00651  -0.0782   0.0299   1.0000
   7.750   1.2373   0.01376   0.00701  -0.0778   0.0238   1.0000
   8.000   1.2620   0.01416   0.00742  -0.0774   0.0215   1.0000
   8.250   1.2849   0.01478   0.00806  -0.0768   0.0188   1.0000
   8.500   1.3093   0.01516   0.00848  -0.0764   0.0178   1.0000
   8.750   1.3329   0.01562   0.00896  -0.0759   0.0167   1.0000
   9.000   1.3552   0.01620   0.00957  -0.0752   0.0156   1.0000
   9.250   1.3748   0.01707   0.01051  -0.0742   0.0146   1.0000
   9.500   1.3970   0.01757   0.01106  -0.0735   0.0142   1.0000
   9.750   1.4182   0.01815   0.01170  -0.0727   0.0136   1.0000
  10.000   1.4385   0.01877   0.01237  -0.0717   0.0131   1.0000
  10.250   1.4581   0.01941   0.01304  -0.0708   0.0125   1.0000
  10.500   1.4749   0.02024   0.01392  -0.0694   0.0119   1.0000
  10.750   1.4810   0.02184   0.01565  -0.0665   0.0113   1.0000
  11.000   1.4969   0.02253   0.01640  -0.0650   0.0112   1.0000
  11.250   1.5093   0.02331   0.01724  -0.0630   0.0109   1.0000
  11.500   1.5178   0.02424   0.01826  -0.0604   0.0107   1.0000
  11.750   1.5256   0.02532   0.01942  -0.0581   0.0104   1.0000
  12.000   1.5328   0.02656   0.02073  -0.0560   0.0102   1.0000
  12.250   1.5395   0.02794   0.02219  -0.0542   0.0100   1.0000
  12.500   1.5456   0.02949   0.02382  -0.0526   0.0097   1.0000
  12.750   1.5513   0.03118   0.02558  -0.0513   0.0095   1.0000
  13.000   1.5555   0.03310   0.02759  -0.0501   0.0093   1.0000
  13.250   1.5581   0.03531   0.02988  -0.0491   0.0092   1.0000
  13.500   1.5573   0.03797   0.03262  -0.0482   0.0090   1.0000
  13.750   1.5521   0.04121   0.03597  -0.0474   0.0088   1.0000
  14.000   1.5416   0.04511   0.03999  -0.0466   0.0087   1.0000
  14.250   1.5311   0.04911   0.04412  -0.0458   0.0085   1.0000
  14.500   1.5337   0.05179   0.04690  -0.0459   0.0085   1.0000
  14.750   1.5350   0.05469   0.04991  -0.0460   0.0084   1.0000
  15.000   1.5339   0.05791   0.05324  -0.0462   0.0083   1.0000
  15.250   1.5318   0.06133   0.05676  -0.0466   0.0082   1.0000
  15.500   1.5288   0.06497   0.06052  -0.0471   0.0081   1.0000
  15.750   1.5246   0.06887   0.06452  -0.0477   0.0080   1.0000
  16.000   1.5197   0.07296   0.06872  -0.0486   0.0079   1.0000
  16.250   1.5141   0.07723   0.07310  -0.0495   0.0078   1.0000
  16.500   1.5082   0.08165   0.07763  -0.0506   0.0077   1.0000
  16.750   1.5017   0.08624   0.08233  -0.0519   0.0076   1.0000
  17.000   1.4948   0.09097   0.08717  -0.0533   0.0075   1.0000
  17.250   1.4874   0.09585   0.09215  -0.0549   0.0075   1.0000
  17.500   1.4796   0.10088   0.09730  -0.0566   0.0074   1.0000
  17.750   1.4714   0.10605   0.10258  -0.0585   0.0073   1.0000
  18.000   1.4630   0.11129   0.10793  -0.0605   0.0072   1.0000
  18.250   1.4542   0.11666   0.11340  -0.0627   0.0072   1.0000
  18.500   1.4455   0.12215   0.11900  -0.0651   0.0071   1.0000
  18.750   1.4362   0.12784   0.12480  -0.0676   0.0071   1.0000
  19.000   1.4274   0.13352   0.13058  -0.0704   0.0070   1.0000
  19.250   1.4179   0.13943   0.13660  -0.0734   0.0070   1.0000
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