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GOE 79 (PFALZ 11) AIRFOIL (goe79-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 79 (PFALZ 11) AIRFOIL (goe79-il)
Reynolds number: 1,000,000
Max Cl/Cd: 120.11 at α=6.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe79-il-1000000.txt
Download as CSV file: xf-goe79-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 79 (PFALZ 11) 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
  ------ -------- --------- --------- -------- -------- --------
  -7.250  -0.1771   0.07152   0.07001  -0.0284   0.9407   0.0164
  -7.000  -0.1699   0.06850   0.06684  -0.0305   0.8996   0.0167
  -6.750  -0.2444   0.08126   0.07973  -0.0248   0.9856   0.0162
  -6.500  -0.2045   0.07652   0.07493  -0.0353   0.9513   0.0167
  -6.250  -0.1730   0.07269   0.07092  -0.0433   0.9072   0.0168
  -6.000  -0.1468   0.06932   0.06740  -0.0493   0.8819   0.0168
  -5.750  -0.1249   0.06571   0.06370  -0.0529   0.8634   0.0169
  -5.500  -0.1104   0.06274   0.06066  -0.0533   0.8464   0.0170
  -5.250  -0.0900   0.06012   0.05796  -0.0554   0.8291   0.0171
  -5.000  -0.0661   0.05757   0.05532  -0.0583   0.8113   0.0174
  -4.750  -0.0398   0.05494   0.05260  -0.0616   0.7926   0.0177
  -4.500  -0.0117   0.05227   0.04982  -0.0651   0.7721   0.0182
  -4.250   0.0183   0.04954   0.04696  -0.0688   0.7504   0.0189
  -4.000   0.0567   0.04670   0.04394  -0.0737   0.7289   0.0195
  -3.750   0.0957   0.04388   0.04092  -0.0785   0.7071   0.0196
  -3.500   0.1333   0.04097   0.03780  -0.0825   0.6859   0.0196
  -3.250   0.1597   0.03792   0.03463  -0.0845   0.6676   0.0197
  -3.000   0.1842   0.03584   0.03246  -0.0857   0.6513   0.0199
  -2.750   0.2122   0.03398   0.03050  -0.0873   0.6386   0.0201
  -2.500   0.2421   0.03220   0.02861  -0.0890   0.6266   0.0204
  -2.250   0.2734   0.03041   0.02671  -0.0907   0.6157   0.0209
  -2.000   0.3054   0.02866   0.02482  -0.0922   0.6057   0.0215
  -1.750   0.3413   0.02695   0.02295  -0.0936   0.5968   0.0224
  -1.500   0.3783   0.02522   0.02099  -0.0947   0.5881   0.0226
  -1.250   0.4110   0.02349   0.01907  -0.0955   0.5788   0.0226
   0.000   0.5605   0.01723   0.01215  -0.0987   0.5249   0.0257
   0.250   0.5923   0.01644   0.01112  -0.0986   0.5143   0.0259
   0.500   0.6224   0.01489   0.00941  -0.0993   0.5027   0.0262
   0.750   0.6510   0.01418   0.00860  -0.0997   0.4888   0.0265
   1.000   0.6797   0.01361   0.00792  -0.0999   0.4711   0.0269
   1.250   0.7084   0.01314   0.00727  -0.1000   0.4457   0.0276
   1.500   0.7377   0.01318   0.00694  -0.0994   0.4115   0.0297
   1.750   0.7660   0.01226   0.00579  -0.0997   0.3746   0.0304
   2.000   0.7934   0.01208   0.00546  -0.0998   0.3463   0.0313
   2.250   0.8213   0.01236   0.00551  -0.0994   0.3266   0.0340
   2.500   0.8496   0.01169   0.00474  -0.0995   0.3136   0.0350
   2.750   0.8775   0.01147   0.00450  -0.0996   0.3031   0.0364
   4.000   1.0171   0.01080   0.00357  -0.0990   0.2612   0.0368
   4.250   1.0450   0.01076   0.00349  -0.0989   0.2535   0.0348
   4.500   1.0725   0.01079   0.00350  -0.0989   0.2454   0.0356
   4.750   1.1002   0.01083   0.00354  -0.0988   0.2383   0.0362
   5.000   1.1275   0.01093   0.00361  -0.0987   0.2303   0.0365
   5.250   1.1550   0.01101   0.00369  -0.0986   0.2234   0.0377
   5.500   1.1819   0.01117   0.00382  -0.0984   0.2152   0.0393
   5.750   1.2091   0.01128   0.00393  -0.0983   0.2077   0.0428
   6.000   1.2357   0.01149   0.00409  -0.0981   0.1962   0.0490
   6.250   1.2587   0.01048   0.00449  -0.0976   0.1842   1.0000
   6.500   1.2846   0.01081   0.00472  -0.0973   0.1684   1.0000
   6.750   1.3085   0.01142   0.00511  -0.0968   0.1330   1.0000
   7.000   1.3302   0.01235   0.00576  -0.0960   0.0923   1.0000
   7.250   1.3554   0.01273   0.00611  -0.0957   0.0886   1.0000
   7.500   1.3803   0.01313   0.00650  -0.0952   0.0849   1.0000
   7.750   1.4051   0.01353   0.00690  -0.0948   0.0816   1.0000
   8.000   1.4301   0.01386   0.00726  -0.0944   0.0799   1.0000
   8.250   1.4554   0.01414   0.00758  -0.0941   0.0785   1.0000
   8.500   1.4802   0.01447   0.00794  -0.0937   0.0764   1.0000
   8.750   1.5043   0.01486   0.00834  -0.0932   0.0741   1.0000
   9.000   1.5278   0.01532   0.00881  -0.0926   0.0715   1.0000
   9.250   1.5500   0.01592   0.00946  -0.0918   0.0684   1.0000
   9.500   1.5747   0.01617   0.00975  -0.0915   0.0676   1.0000
   9.750   1.5991   0.01644   0.01005  -0.0910   0.0665   1.0000
  10.000   1.6231   0.01674   0.01039  -0.0906   0.0648   1.0000
  10.250   1.6465   0.01708   0.01075  -0.0900   0.0626   1.0000
  10.500   1.6688   0.01753   0.01120  -0.0894   0.0600   1.0000
  10.750   1.6902   0.01805   0.01175  -0.0885   0.0574   1.0000
  11.000   1.7138   0.01830   0.01205  -0.0880   0.0558   1.0000
  11.250   1.7362   0.01866   0.01242  -0.0874   0.0527   1.0000
  11.500   1.7566   0.01919   0.01292  -0.0865   0.0485   1.0000
  11.750   1.7775   0.01963   0.01338  -0.0857   0.0449   1.0000
  12.000   1.7958   0.02027   0.01399  -0.0845   0.0399   1.0000
  12.250   1.8118   0.02107   0.01475  -0.0830   0.0342   1.0000
  12.500   1.8258   0.02196   0.01564  -0.0813   0.0292   1.0000
  12.750   1.8377   0.02290   0.01659  -0.0792   0.0254   1.0000
  13.000   1.8464   0.02390   0.01764  -0.0766   0.0226   1.0000
  13.250   1.8508   0.02497   0.01875  -0.0734   0.0208   1.0000
  13.500   1.8541   0.02624   0.02008  -0.0704   0.0192   1.0000
  13.750   1.8598   0.02748   0.02140  -0.0681   0.0183   1.0000
  14.000   1.8631   0.02904   0.02303  -0.0659   0.0174   1.0000
  14.250   1.8636   0.03101   0.02508  -0.0640   0.0165   1.0000
  14.500   1.8628   0.03331   0.02748  -0.0625   0.0158   1.0000
  14.750   1.8659   0.03538   0.02965  -0.0614   0.0154   1.0000
  15.000   1.8670   0.03778   0.03217  -0.0606   0.0150   1.0000
  15.250   1.8662   0.04055   0.03504  -0.0601   0.0146   1.0000
  15.500   1.8628   0.04375   0.03834  -0.0598   0.0143   1.0000
  15.750   1.8569   0.04743   0.04213  -0.0599   0.0139   1.0000
  16.000   1.8478   0.05167   0.04648  -0.0603   0.0136   1.0000
  16.250   1.8350   0.05652   0.05147  -0.0610   0.0134   1.0000
  16.500   1.8179   0.06210   0.05718  -0.0620   0.0131   1.0000
  16.750   1.7978   0.06819   0.06341  -0.0633   0.0129   1.0000
  17.000   1.7820   0.07390   0.06925  -0.0647   0.0128   1.0000
  17.250   1.7674   0.07956   0.07505  -0.0663   0.0127   1.0000
  17.500   1.7501   0.08578   0.08140  -0.0681   0.0127   1.0000
  17.750   1.7321   0.09230   0.08805  -0.0702   0.0126   1.0000
  18.000   1.7136   0.09901   0.09490  -0.0725   0.0125   1.0000
  18.250   1.6940   0.10604   0.10205  -0.0750   0.0124   1.0000
  18.500   1.6763   0.11283   0.10896  -0.0776   0.0123   1.0000
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