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GOE 596 AIRFOIL (goe596-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GOE 596 AIRFOIL (goe596-il)
Reynolds number: 1,000,000
Max Cl/Cd: 112.48 at α=4.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe596-il-1000000-n5.txt
Download as CSV file: xf-goe596-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 596 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.4143   0.09391   0.09217  -0.0345   1.0000   0.0132
 -10.250  -0.4089   0.09153   0.08979  -0.0353   1.0000   0.0134
 -10.000  -0.4048   0.08897   0.08726  -0.0361   1.0000   0.0135
  -9.750  -0.4009   0.08656   0.08485  -0.0367   1.0000   0.0137
  -9.500  -0.3971   0.08356   0.08188  -0.0382   0.9997   0.0139
  -9.250  -0.3898   0.07980   0.07813  -0.0414   0.9889   0.0142
  -8.750  -0.4816   0.02082   0.01723  -0.0926   0.9059   0.0198
  -8.500  -0.4644   0.01891   0.01501  -0.0918   0.8926   0.0201
  -8.250  -0.4417   0.01819   0.01415  -0.0912   0.8815   0.0204
  -8.000  -0.4181   0.01765   0.01349  -0.0906   0.8704   0.0205
  -7.750  -0.3944   0.01707   0.01278  -0.0900   0.8597   0.0207
  -7.500  -0.3701   0.01661   0.01221  -0.0895   0.8496   0.0209
  -7.250  -0.3460   0.01608   0.01155  -0.0889   0.8390   0.0211
  -7.000  -0.3211   0.01562   0.01098  -0.0885   0.8299   0.0214
  -6.750  -0.2966   0.01509   0.01031  -0.0879   0.8207   0.0216
  -6.500  -0.2718   0.01450   0.00959  -0.0874   0.8112   0.0220
  -6.250  -0.2474   0.01378   0.00872  -0.0869   0.8016   0.0222
  -6.000  -0.2227   0.01319   0.00797  -0.0863   0.7903   0.0225
  -5.750  -0.1975   0.01262   0.00727  -0.0858   0.7780   0.0228
  -5.500  -0.1723   0.01210   0.00661  -0.0852   0.7645   0.0231
  -5.250  -0.1469   0.01168   0.00607  -0.0847   0.7495   0.0233
  -5.000  -0.1215   0.01133   0.00558  -0.0842   0.7311   0.0236
  -4.750  -0.0961   0.01110   0.00523  -0.0836   0.7078   0.0239
  -4.500  -0.0710   0.01094   0.00491  -0.0830   0.6803   0.0241
  -4.250  -0.0456   0.01077   0.00460  -0.0824   0.6567   0.0242
  -4.000  -0.0206   0.01034   0.00405  -0.0818   0.6388   0.0245
  -3.750   0.0046   0.00998   0.00358  -0.0812   0.6229   0.0249
  -3.500   0.0303   0.00975   0.00326  -0.0808   0.6080   0.0252
  -3.250   0.0564   0.00959   0.00303  -0.0803   0.5938   0.0255
  -3.000   0.0827   0.00944   0.00282  -0.0799   0.5812   0.0258
  -2.750   0.1090   0.00932   0.00263  -0.0796   0.5697   0.0261
  -2.500   0.1359   0.00917   0.00245  -0.0793   0.5613   0.0265
  -2.000   0.1897   0.00891   0.00213  -0.0787   0.5481   0.0272
  -1.750   0.2167   0.00880   0.00198  -0.0784   0.5414   0.0277
  -1.500   0.2437   0.00871   0.00186  -0.0782   0.5362   0.0282
  -1.250   0.2710   0.00863   0.00177  -0.0779   0.5310   0.0288
  -1.000   0.2981   0.00856   0.00167  -0.0777   0.5251   0.0293
  -0.750   0.3253   0.00850   0.00159  -0.0775   0.5198   0.0296
  -0.500   0.3525   0.00841   0.00148  -0.0772   0.5142   0.0302
  -0.250   0.3795   0.00834   0.00139  -0.0770   0.5090   0.0311
   0.000   0.4067   0.00829   0.00134  -0.0767   0.5044   0.0322
   0.250   0.4341   0.00825   0.00130  -0.0766   0.4995   0.0334
   0.500   0.4613   0.00823   0.00128  -0.0763   0.4937   0.0347
   0.750   0.4885   0.00823   0.00126  -0.0761   0.4878   0.0361
   1.000   0.5156   0.00821   0.00125  -0.0759   0.4801   0.0403
   1.250   0.5425   0.00821   0.00126  -0.0756   0.4727   0.0504
   1.500   0.5690   0.00807   0.00128  -0.0754   0.4657   0.1134
   1.750   0.5944   0.00786   0.00133  -0.0750   0.4576   0.2362
   2.000   0.6183   0.00746   0.00141  -0.0744   0.4479   0.4396
   2.500   0.7132   0.00645   0.00168  -0.0833   0.4198   1.0000
   2.750   0.7367   0.00663   0.00175  -0.0824   0.3994   1.0000
   3.000   0.7604   0.00681   0.00184  -0.0816   0.3807   1.0000
   3.250   0.7836   0.00705   0.00195  -0.0806   0.3576   1.0000
   3.500   0.8071   0.00726   0.00208  -0.0797   0.3402   1.0000
   3.750   0.8313   0.00744   0.00220  -0.0790   0.3274   1.0000
   4.000   0.8551   0.00765   0.00233  -0.0781   0.3124   1.0000
   4.250   0.8792   0.00783   0.00247  -0.0774   0.3013   1.0000
   4.500   0.9032   0.00803   0.00261  -0.0766   0.2887   1.0000
   4.750   0.9267   0.00828   0.00277  -0.0758   0.2712   1.0000
   5.000   0.9498   0.00855   0.00296  -0.0749   0.2511   1.0000
   5.250   0.9723   0.00888   0.00317  -0.0740   0.2273   1.0000
   5.500   0.9928   0.00937   0.00347  -0.0727   0.1910   1.0000
   5.750   1.0137   0.00982   0.00379  -0.0715   0.1644   1.0000
   6.000   1.0355   0.01022   0.00408  -0.0705   0.1453   1.0000
   6.250   1.0560   0.01071   0.00442  -0.0693   0.1177   1.0000
   6.500   1.0691   0.01177   0.00513  -0.0669   0.0531   1.0000
   6.750   1.0909   0.01214   0.00546  -0.0659   0.0446   1.0000
   7.000   1.1131   0.01247   0.00577  -0.0649   0.0402   1.0000
   7.250   1.1359   0.01275   0.00606  -0.0641   0.0381   1.0000
   7.500   1.1582   0.01305   0.00636  -0.0632   0.0361   1.0000
   7.750   1.1800   0.01339   0.00670  -0.0622   0.0341   1.0000
   8.000   1.2012   0.01375   0.00706  -0.0611   0.0321   1.0000
   8.250   1.2229   0.01405   0.00739  -0.0602   0.0312   1.0000
   8.500   1.2445   0.01436   0.00772  -0.0592   0.0303   1.0000
   8.750   1.2653   0.01469   0.00807  -0.0581   0.0292   1.0000
   9.000   1.2854   0.01505   0.00845  -0.0569   0.0280   1.0000
   9.250   1.3046   0.01545   0.00886  -0.0556   0.0268   1.0000
   9.500   1.3224   0.01591   0.00933  -0.0540   0.0254   1.0000
   9.750   1.3412   0.01624   0.00971  -0.0526   0.0249   1.0000
  10.000   1.3579   0.01660   0.01010  -0.0508   0.0241   1.0000
  10.250   1.3735   0.01698   0.01051  -0.0489   0.0231   1.0000
  10.500   1.3885   0.01741   0.01096  -0.0469   0.0220   1.0000
  10.750   1.4022   0.01792   0.01148  -0.0448   0.0207   1.0000
  11.000   1.4168   0.01840   0.01200  -0.0429   0.0198   1.0000
  11.250   1.4311   0.01892   0.01255  -0.0411   0.0188   1.0000
  11.500   1.4444   0.01950   0.01316  -0.0392   0.0177   1.0000
  11.750   1.4568   0.02015   0.01383  -0.0373   0.0167   1.0000
  12.000   1.4687   0.02086   0.01458  -0.0355   0.0157   1.0000
  12.250   1.4802   0.02162   0.01538  -0.0337   0.0146   1.0000
  12.500   1.4905   0.02249   0.01629  -0.0319   0.0137   1.0000
  12.750   1.4998   0.02348   0.01731  -0.0301   0.0128   1.0000
  13.000   1.5091   0.02450   0.01839  -0.0285   0.0122   1.0000
  13.250   1.5179   0.02562   0.01957  -0.0270   0.0117   1.0000
  13.500   1.5254   0.02690   0.02090  -0.0256   0.0110   1.0000
  13.750   1.5321   0.02830   0.02236  -0.0242   0.0106   1.0000
  14.000   1.5372   0.02991   0.02403  -0.0230   0.0100   1.0000
  14.250   1.5425   0.03157   0.02576  -0.0219   0.0097   1.0000
  14.500   1.5476   0.03334   0.02760  -0.0210   0.0094   1.0000
  14.750   1.5519   0.03525   0.02959  -0.0202   0.0090   1.0000
  15.000   1.5550   0.03737   0.03179  -0.0196   0.0088   1.0000
  15.250   1.5570   0.03969   0.03418  -0.0192   0.0085   1.0000
  15.500   1.5579   0.04223   0.03681  -0.0190   0.0082   1.0000
  15.750   1.5571   0.04502   0.03968  -0.0189   0.0079   1.0000
  16.000   1.5549   0.04809   0.04283  -0.0189   0.0076   1.0000
  16.250   1.5525   0.05124   0.04607  -0.0192   0.0075   1.0000
  16.500   1.5504   0.05443   0.04935  -0.0195   0.0073   1.0000
  16.750   1.5476   0.05777   0.05278  -0.0199   0.0072   1.0000
  17.000   1.5437   0.06133   0.05644  -0.0205   0.0071   1.0000
  17.250   1.5395   0.06496   0.06016  -0.0212   0.0070   1.0000
  17.500   1.5346   0.06877   0.06407  -0.0220   0.0069   1.0000
  17.750   1.5274   0.07300   0.06840  -0.0230   0.0068   1.0000
  18.000   1.5212   0.07718   0.07268  -0.0241   0.0066   1.0000
  18.250   1.5140   0.08160   0.07719  -0.0255   0.0065   1.0000
  18.500   1.5051   0.08640   0.08209  -0.0270   0.0065   1.0000
  18.750   1.4973   0.09111   0.08690  -0.0287   0.0063   1.0000
  19.000   1.4875   0.09627   0.09217  -0.0306   0.0063   1.0000
  19.250   1.4789   0.10131   0.09730  -0.0326   0.0062   1.0000
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