Airfoil: E387 (E)
Builder: Y. Tinel
Comment: clean

Number of Reynolds #'s:
6

Average Reynolds #:
100029
Number of angles of attack:
17
 alpha  /   Cl   /  Cd   /  Spanwise Cd's >>>
 -5.25   -0.292   0.0472  0.0473   0.0450   0.0419   0.0435   0.0447   0.0489   0.0498   0.0568
 -4.24   -0.156   0.0293  0.0270   0.0302   0.0268   0.0279   0.0289   0.0288   0.0304   0.0343
 -3.12   -0.001   0.0220  0.0228   0.0226   0.0211   0.0192   0.0190   0.0211   0.0242   0.0258
 -2.13    0.139   0.0187  0.0201   0.0188   0.0187   0.0187   0.0173   0.0165   0.0187   0.0207
 -1.11    0.238   0.0174  0.0197   0.0173   0.0168   0.0163   0.0158   0.0163   0.0172   0.0196
 -0.08    0.339   0.0202  0.0216   0.0201   0.0196   0.0194   0.0199   0.0203   0.0198   0.0208
  0.95    0.435   0.0229  0.0226   0.0226   0.0218   0.0222   0.0234   0.0231   0.0235   0.0237
  1.96    0.530   0.0266  0.0273   0.0265   0.0263   0.0269   0.0268   0.0267   0.0262   0.0261
  3.00    0.623   0.0290  0.0296   0.0287   0.0287   0.0281   0.0297   0.0289   0.0288   0.0299
  4.00    0.715   0.0317  0.0318   0.0319   0.0311   0.0324   0.0323   0.0318   0.0311   0.0316
  5.04    0.825   0.0278  0.0279   0.0277   0.0278   0.0278   0.0286   0.0282   0.0269   0.0277
  6.04    0.928   0.0239  0.0242   0.0239   0.0240   0.0242   0.0241   0.0237   0.0239   0.0235
  7.07    1.032   0.0218  0.0207   0.0217   0.0211   0.0221   0.0224   0.0215   0.0223   0.0228
  8.11    1.130   0.0215  0.0216   0.0210   0.0225   0.0209   0.0200   0.0192   0.0226   0.0239
  9.17    1.176   0.0269  0.0263   0.0276   0.0269   0.0268   0.0265   0.0271   0.0263   0.0274
 10.11    1.185   0.0363  0.0387   0.0389   0.0377   0.0357   0.0351   0.0342   0.0336   0.0367
 11.14    1.188   0.0526  0.0493   0.0507   0.0513   0.0539   0.0558   0.0567   0.0522   0.0506
Tabulated from data in file bm05141.dat & reduced using program C10.20

Average Reynolds #:
199879
Number of angles of attack:
19
 alpha  /   Cl   /  Cd   /  Spanwise Cd's >>>
 -6.24   -0.332   0.0705  0.0738   0.0708   0.0709   0.0695   0.0668   0.0685   0.0697   0.0736
 -5.20   -0.138   0.0352  0.0359   0.0365   0.0350   0.0364   0.0326   0.0332   0.0354   0.0368
 -4.17   -0.015   0.0192  0.0203   0.0198   0.0185   0.0192   0.0181   0.0184   0.0194   0.0196
 -3.14    0.081   0.0150  0.0156   0.0152   0.0144   0.0157   0.0141   0.0145   0.0152   0.0156
 -2.14    0.178   0.0125  0.0130   0.0125   0.0119   0.0126   0.0124   0.0119   0.0124   0.0134
 -1.09    0.271   0.0102  0.0105   0.0106   0.0102   0.0096   0.0106   0.0096   0.0097   0.0109
 -0.05    0.381   0.0104  0.0104   0.0103   0.0103   0.0103   0.0111   0.0101   0.0102   0.0105
  0.97    0.483   0.0110  0.0108   0.0109   0.0108   0.0110   0.0118   0.0109   0.0107   0.0109
  2.01    0.593   0.0118  0.0116   0.0118   0.0114   0.0120   0.0126   0.0116   0.0114   0.0117
  3.00    0.698   0.0126  0.0122   0.0125   0.0124   0.0131   0.0134   0.0125   0.0124   0.0127
  4.09    0.806   0.0134  0.0127   0.0133   0.0132   0.0141   0.0139   0.0136   0.0132   0.0135
  5.02    0.902   0.0138  0.0133   0.0135   0.0138   0.0144   0.0138   0.0138   0.0136   0.0139
  6.09    1.017   0.0140  0.0136   0.0135   0.0138   0.0143   0.0140   0.0144   0.0141   0.0145
  7.14    1.119   0.0149  0.0148   0.0138   0.0139   0.0145   0.0151   0.0150   0.0157   0.0163
  8.15    1.191   0.0181  0.0179   0.0176   0.0171   0.0185   0.0184   0.0186   0.0177   0.0187
  9.18    1.226   0.0265  0.0275   0.0289   0.0253   0.0253   0.0265   0.0266   0.0256   0.0266
 10.12    1.234   0.0358  0.0356   0.0366   0.0352   0.0361   0.0394   0.0362   0.0334   0.0338
 11.18    1.227   0.0550  0.0416   0.0428   0.0452   0.0572   0.0731   0.0754   0.0600   0.0447
 12.20    1.218   0.0774  0.0546   0.0575   0.0642   0.0778   0.0931   0.1007   0.0932   0.0779
Tabulated from data in file bm04979.dat & reduced using program C10.20

Average Reynolds #:
300289
Number of angles of attack:
19
 alpha  /   Cl   /  Cd   /  Spanwise Cd's >>>
 -6.25   -0.304   0.0669  0.0688   0.0678   0.0671   0.0652   0.0658   0.0665   0.0648   0.0691
 -5.21   -0.139   0.0341  0.0357   0.0351   0.0346   0.0335   0.0321   0.0325   0.0336   0.0359
 -4.18   -0.028   0.0169  0.0178   0.0174   0.0165   0.0168   0.0159   0.0161   0.0173   0.0172
 -3.20    0.064   0.0131  0.0136   0.0134   0.0125   0.0139   0.0124   0.0130   0.0133   0.0129
 -2.07    0.184   0.0110  0.0111   0.0111   0.0104   0.0114   0.0107   0.0108   0.0111   0.0115
 -1.11    0.288   0.0092  0.0091   0.0091   0.0089   0.0088   0.0091   0.0090   0.0091   0.0101
 -0.04    0.393   0.0083  0.0081   0.0081   0.0083   0.0082   0.0086   0.0082   0.0083   0.0086
  1.02    0.502   0.0088  0.0084   0.0086   0.0088   0.0087   0.0092   0.0088   0.0089   0.0088
  1.96    0.610   0.0092  0.0090   0.0092   0.0089   0.0093   0.0098   0.0091   0.0089   0.0093
  3.02    0.714   0.0098  0.0096   0.0098   0.0099   0.0102   0.0104   0.0096   0.0094   0.0099
  4.00    0.817   0.0105  0.0101   0.0102   0.0107   0.0109   0.0111   0.0106   0.0100   0.0103
  5.06    0.935   0.0112  0.0110   0.0107   0.0114   0.0117   0.0113   0.0117   0.0107   0.0110
  6.11    1.041   0.0115  0.0112   0.0107   0.0113   0.0117   0.0115   0.0126   0.0116   0.0118
  7.15    1.135   0.0131  0.0128   0.0122   0.0128   0.0132   0.0125   0.0140   0.0129   0.0140
  8.14    1.201   0.0176  0.0175   0.0175   0.0169   0.0178   0.0177   0.0179   0.0174   0.0184
  9.15    1.241   0.0246  0.0262   0.0267   0.0234   0.0239   0.0245   0.0244   0.0232   0.0241
 10.12    1.250   0.0343  0.0327   0.0344   0.0323   0.0366   0.0412   0.0362   0.0301   0.0310
 11.16    1.245   0.0537  0.0410   0.0401   0.0405   0.0516   0.0692   0.0756   0.0652   0.0466
 12.17    1.236   0.0774  0.0586   0.0581   0.0633   0.0763   0.0890   0.0978   0.0964   0.0797
Tabulated from data in file bm04981.dat & reduced using program C10.20

Average Reynolds #:
349865
Number of angles of attack:
19
 alpha  /   Cl   /  Cd   /  Spanwise Cd's >>>
 -6.25   -0.288   0.0647  0.0674   0.0654   0.0632   0.0624   0.0621   0.0637   0.0643   0.0688
 -5.18   -0.144   0.0337  0.0347   0.0341   0.0337   0.0330   0.0317   0.0324   0.0343   0.0358
 -4.19   -0.038   0.0164  0.0173   0.0169   0.0161   0.0164   0.0154   0.0155   0.0171   0.0169
 -3.15    0.071   0.0123  0.0124   0.0124   0.0116   0.0130   0.0116   0.0123   0.0126   0.0122
 -2.11    0.180   0.0106  0.0107   0.0106   0.0100   0.0111   0.0103   0.0105   0.0109   0.0110
 -1.16    0.277   0.0090  0.0088   0.0088   0.0089   0.0087   0.0089   0.0089   0.0090   0.0097
 -0.05    0.389   0.0078  0.0074   0.0076   0.0079   0.0075   0.0080   0.0079   0.0079   0.0082
  0.94    0.493   0.0081  0.0078   0.0080   0.0082   0.0079   0.0085   0.0081   0.0083   0.0082
  1.97    0.605   0.0085  0.0082   0.0086   0.0084   0.0086   0.0089   0.0084   0.0085   0.0086
  3.00    0.714   0.0091  0.0090   0.0091   0.0091   0.0094   0.0096   0.0090   0.0086   0.0092
  4.03    0.833   0.0098  0.0096   0.0096   0.0101   0.0101   0.0103   0.0100   0.0095   0.0095
  5.08    0.942   0.0104  0.0103   0.0099   0.0104   0.0109   0.0103   0.0111   0.0101   0.0101
  6.08    1.045   0.0111  0.0112   0.0101   0.0111   0.0113   0.0108   0.0121   0.0107   0.0114
  7.08    1.134   0.0128  0.0127   0.0123   0.0127   0.0131   0.0124   0.0137   0.0124   0.0135
  8.11    1.200   0.0177  0.0182   0.0181   0.0168   0.0176   0.0175   0.0179   0.0172   0.0183
  9.11    1.240   0.0238  0.0255   0.0258   0.0230   0.0231   0.0238   0.0235   0.0225   0.0235
 10.14    1.249   0.0347  0.0336   0.0344   0.0336   0.0373   0.0424   0.0361   0.0297   0.0303
 11.15    1.245   0.0564  0.0411   0.0414   0.0419   0.0558   0.0745   0.0801   0.0685   0.0478
 12.14    1.238   0.0781  0.0554   0.0569   0.0638   0.0811   0.0977   0.1003   0.0934   0.0761
Tabulated from data in file bm04983.dat & reduced using program C10.20

Average Reynolds #:
459961
Number of angles of attack:
19
 alpha  /   Cl   /  Cd   /  Spanwise Cd's >>>
 -6.23   -0.292   0.0651  0.0677   0.0665   0.0645   0.0622   0.0618   0.0640   0.0659   0.0683
 -5.20   -0.150   0.0341  0.0349   0.0346   0.0347   0.0334   0.0322   0.0324   0.0343   0.0361
 -4.16   -0.040   0.0145  0.0148   0.0147   0.0144   0.0147   0.0134   0.0139   0.0152   0.0146
 -3.13    0.064   0.0114  0.0113   0.0115   0.0110   0.0121   0.0109   0.0114   0.0115   0.0112
 -2.13    0.172   0.0099  0.0097   0.0099   0.0097   0.0104   0.0095   0.0098   0.0102   0.0101
 -1.08    0.280   0.0085  0.0085   0.0084   0.0084   0.0083   0.0086   0.0085   0.0087   0.0090
 -0.09    0.382   0.0069  0.0066   0.0068   0.0070   0.0065   0.0068   0.0068   0.0069   0.0074
  0.96    0.500   0.0072  0.0067   0.0072   0.0073   0.0071   0.0074   0.0071   0.0074   0.0073
  1.98    0.611   0.0075  0.0073   0.0077   0.0074   0.0076   0.0078   0.0074   0.0075   0.0076
  3.00    0.721   0.0079  0.0077   0.0080   0.0079   0.0082   0.0083   0.0078   0.0075   0.0080
  4.03    0.835   0.0087  0.0084   0.0085   0.0089   0.0089   0.0092   0.0088   0.0082   0.0084
  5.12    0.948   0.0094  0.0093   0.0091   0.0093   0.0096   0.0096   0.0101   0.0089   0.0093
  6.09    1.045   0.0101  0.0101   0.0095   0.0103   0.0102   0.0097   0.0108   0.0095   0.0104
  7.15    1.132   0.0128  0.0127   0.0123   0.0125   0.0132   0.0127   0.0135   0.0126   0.0131
  8.18    1.195   0.0172  0.0176   0.0173   0.0164   0.0173   0.0170   0.0173   0.0168   0.0177
  9.12    1.236   0.0224  0.0228   0.0236   0.0212   0.0221   0.0229   0.0222   0.0214   0.0227
 10.14    1.255   0.0318  0.0296   0.0319   0.0309   0.0338   0.0391   0.0345   0.0272   0.0278
 11.12    1.252   0.0543  0.0341   0.0345   0.0383   0.0589   0.0800   0.0811   0.0655   0.0419
 12.16    1.242   0.0790  0.0439   0.0508   0.0672   0.0883   0.1035   0.1058   0.0946   0.0783
Tabulated from data in file bm04985.dat & reduced using program C10.20

Average Reynolds #:
500094
Number of angles of attack:
19
 alpha  /   Cl   /  Cd   /  Spanwise Cd's >>>
 -6.20   -0.289   0.0643  0.0664   0.0651   0.0652   0.0649   0.0626   0.0611   0.0619   0.0675
 -5.18   -0.155   0.0352  0.0359   0.0353   0.0353   0.0346   0.0334   0.0336   0.0354   0.0378
 -4.15   -0.040   0.0139  0.0141   0.0141   0.0139   0.0142   0.0131   0.0132   0.0147   0.0140
 -3.20    0.056   0.0114  0.0115   0.0114   0.0111   0.0122   0.0109   0.0112   0.0115   0.0111
 -2.16    0.171   0.0097  0.0095   0.0097   0.0092   0.0101   0.0093   0.0096   0.0099   0.0100
 -1.09    0.276   0.0085  0.0084   0.0083   0.0083   0.0083   0.0085   0.0084   0.0086   0.0088
 -0.04    0.388   0.0067  0.0064   0.0066   0.0068   0.0063   0.0067   0.0066   0.0068   0.0072
  0.88    0.497   0.0068  0.0063   0.0069   0.0070   0.0066   0.0070   0.0068   0.0071   0.0070
  1.97    0.613   0.0072  0.0069   0.0073   0.0070   0.0072   0.0075   0.0071   0.0072   0.0073
  2.98    0.720   0.0077  0.0077   0.0078   0.0077   0.0080   0.0081   0.0076   0.0071   0.0079
  4.02    0.833   0.0084  0.0082   0.0084   0.0087   0.0088   0.0088   0.0084   0.0078   0.0082
  5.08    0.941   0.0091  0.0089   0.0089   0.0091   0.0094   0.0093   0.0096   0.0086   0.0089
  6.11    1.047   0.0099  0.0098   0.0095   0.0101   0.0100   0.0097   0.0105   0.0094   0.0100
  7.15    1.129   0.0128  0.0126   0.0121   0.0127   0.0131   0.0127   0.0135   0.0126   0.0131
  8.14    1.195   0.0169  0.0173   0.0170   0.0162   0.0170   0.0167   0.0172   0.0167   0.0174
  9.14    1.244   0.0226  0.0231   0.0236   0.0213   0.0223   0.0231   0.0223   0.0218   0.0230
 10.09    1.259   0.0300  0.0295   0.0325   0.0293   0.0309   0.0347   0.0300   0.0260   0.0267
 11.17    1.257   0.0548  0.0344   0.0343   0.0383   0.0569   0.0780   0.0820   0.0696   0.0449
 12.13    1.248   0.0804  0.0457   0.0533   0.0718   0.0897   0.1028   0.1062   0.0955   0.0782
Tabulated from data in file bm04987.dat & reduced using program C10.20

File e387_c.drg created using program C10.20 on Thu May 22 17:01:34 2003
