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AG47ct -02f rot. (ag47ct02r-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: AG47ct -02f rot. (ag47ct02r-il)
Reynolds number: 200,000
Max Cl/Cd: 49.56 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-ag47ct02r-il-200000-n5.txt
Download as CSV file: xf-ag47ct02r-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: AG47ct  -02f rot.                               
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.6379   0.12170   0.11818   0.0327   1.0000   0.0175
  -9.250  -0.6335   0.11781   0.11431   0.0305   1.0000   0.0176
  -9.000  -0.6357   0.11195   0.10849   0.0308   1.0000   0.0184
  -8.750  -0.6285   0.10883   0.10538   0.0315   1.0000   0.0194
  -8.500  -0.6241   0.10522   0.10176   0.0301   1.0000   0.0199
  -8.250  -0.6201   0.10147   0.09803   0.0283   1.0000   0.0203
  -8.000  -0.6162   0.09767   0.09426   0.0263   1.0000   0.0206
  -7.750  -0.6123   0.09381   0.09044   0.0239   1.0000   0.0209
  -7.500  -0.6082   0.08984   0.08649   0.0210   1.0000   0.0213
  -7.250  -0.6008   0.08544   0.08211   0.0167   1.0000   0.0216
  -7.000  -0.5903   0.08062   0.07730   0.0114   1.0000   0.0219
  -6.750  -0.5771   0.07550   0.07216   0.0056   1.0000   0.0221
  -6.500  -0.5615   0.07008   0.06671  -0.0003   1.0000   0.0221
  -6.250  -0.5358   0.06113   0.05757  -0.0098   1.0000   0.0168
  -6.000  -0.5210   0.05622   0.05257  -0.0128   1.0000   0.0153
  -5.750  -0.4996   0.05005   0.04620  -0.0170   1.0000   0.0139
  -5.250  -0.4467   0.03476   0.03000  -0.0228   1.0000   0.0111
  -5.000  -0.4228   0.02993   0.02470  -0.0239   1.0000   0.0109
  -4.750  -0.3973   0.02573   0.01996  -0.0243   1.0000   0.0109
  -4.500  -0.3708   0.02238   0.01603  -0.0243   1.0000   0.0110
  -4.250  -0.3438   0.01993   0.01307  -0.0241   1.0000   0.0112
  -4.000  -0.3175   0.01736   0.01012  -0.0238   1.0000   0.0119
  -3.750  -0.2911   0.01658   0.00923  -0.0237   1.0000   0.0139
  -3.500  -0.2641   0.01559   0.00805  -0.0234   1.0000   0.0159
  -3.250  -0.2371   0.01430   0.00658  -0.0229   1.0000   0.0168
  -3.000  -0.2103   0.01320   0.00537  -0.0224   1.0000   0.0179
  -2.750  -0.1837   0.01217   0.00430  -0.0221   1.0000   0.0207
  -2.500  -0.1567   0.01172   0.00377  -0.0218   1.0000   0.0265
  -2.250  -0.1297   0.01103   0.00307  -0.0216   1.0000   0.0360
  -2.000  -0.1027   0.01050   0.00263  -0.0213   1.0000   0.0583
  -1.750  -0.0759   0.00997   0.00233  -0.0212   1.0000   0.1113
  -1.500  -0.0495   0.00936   0.00212  -0.0212   1.0000   0.2140
  -1.250  -0.0239   0.00852   0.00197  -0.0212   1.0000   0.4015
  -1.000  -0.0029   0.00740   0.00193  -0.0198   1.0000   0.6882
  -0.750   0.0283   0.00672   0.00184  -0.0193   1.0000   1.0000
  -0.500   0.0554   0.00673   0.00176  -0.0191   0.9986   1.0000
  -0.250   0.0972   0.00677   0.00167  -0.0220   0.9544   1.0000
   0.000   0.1384   0.00684   0.00158  -0.0245   0.8794   1.0000
   0.250   0.1671   0.00703   0.00148  -0.0239   0.8032   1.0000
   0.500   0.1919   0.00727   0.00144  -0.0228   0.7545   1.0000
   0.750   0.2174   0.00751   0.00145  -0.0220   0.7216   1.0000
   1.000   0.2435   0.00773   0.00150  -0.0214   0.6949   1.0000
   1.250   0.2702   0.00788   0.00155  -0.0209   0.6643   1.0000
   1.500   0.2966   0.00805   0.00160  -0.0204   0.6283   1.0000
   1.750   0.3228   0.00825   0.00164  -0.0199   0.5861   1.0000
   2.000   0.3489   0.00849   0.00168  -0.0194   0.5376   1.0000
   2.250   0.3750   0.00879   0.00175  -0.0189   0.4845   1.0000
   2.500   0.4011   0.00913   0.00186  -0.0186   0.4282   1.0000
   2.750   0.4273   0.00951   0.00204  -0.0183   0.3705   1.0000
   3.000   0.4535   0.00992   0.00222  -0.0180   0.3145   1.0000
   3.250   0.4797   0.01036   0.00245  -0.0178   0.2638   1.0000
   3.500   0.5061   0.01079   0.00270  -0.0177   0.2199   1.0000
   3.750   0.5325   0.01122   0.00299  -0.0175   0.1833   1.0000
   4.000   0.5590   0.01165   0.00335  -0.0174   0.1548   1.0000
   4.250   0.5855   0.01209   0.00371  -0.0172   0.1291   1.0000
   4.500   0.6120   0.01251   0.00410  -0.0170   0.1102   1.0000
   4.750   0.6384   0.01296   0.00453  -0.0168   0.0947   1.0000
   5.000   0.6646   0.01343   0.00503  -0.0166   0.0806   1.0000
   5.250   0.6908   0.01394   0.00556  -0.0164   0.0703   1.0000
   5.500   0.7168   0.01451   0.00614  -0.0162   0.0608   1.0000
   5.750   0.7427   0.01505   0.00672  -0.0159   0.0519   1.0000
   6.000   0.7684   0.01570   0.00748  -0.0156   0.0458   1.0000
   6.250   0.7937   0.01642   0.00826  -0.0153   0.0392   1.0000
   6.500   0.8191   0.01713   0.00911  -0.0150   0.0344   1.0000
   6.750   0.8441   0.01794   0.01003  -0.0146   0.0305   1.0000
   7.000   0.8677   0.01920   0.01138  -0.0142   0.0272   1.0000
   7.250   0.8926   0.02003   0.01241  -0.0138   0.0242   1.0000
   7.500   0.9167   0.02107   0.01365  -0.0134   0.0219   1.0000
   7.750   0.9398   0.02235   0.01508  -0.0129   0.0201   1.0000
   8.000   0.9601   0.02469   0.01765  -0.0123   0.0187   1.0000
   8.250   0.9823   0.02639   0.01969  -0.0117   0.0177   1.0000
   8.500   1.0038   0.02806   0.02171  -0.0112   0.0160   1.0000
   8.750   1.0238   0.03003   0.02401  -0.0107   0.0148   1.0000
   9.000   1.0418   0.03232   0.02664  -0.0103   0.0140   1.0000
   9.250   1.0579   0.03479   0.02941  -0.0099   0.0133   1.0000
   9.500   1.0695   0.03805   0.03304  -0.0096   0.0127   1.0000
   9.750   1.0703   0.04328   0.03879  -0.0097   0.0123   1.0000
  10.000   1.0663   0.04867   0.04470  -0.0104   0.0120   1.0000
  10.250   1.0561   0.05435   0.05079  -0.0125   0.0119   1.0000
  10.500   1.0366   0.06108   0.05772  -0.0178   0.0120   1.0000
  10.750   0.9384   0.09789   0.09479  -0.0463   0.0143   1.0000
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