Airfoil: M6 (85%)
Builder: L. Spychalla
Comment: clean

Number of Reynolds #'s:
 4 

Average Reynolds #:
 60000 
Number of angles of attack:
 11 
 alpha /   Cl   /  Cd   /  Spanwise Cd's >>>
 -5.48  -0.419   0.0424   0.0422   0.0434   0.0430   0.0407
 -4.03  -0.324   0.0290   0.0296   0.0292   0.0293   0.0279
 -2.45  -0.230   0.0214   0.0226   0.0215   0.0202   0.0213
 -0.91  -0.056   0.0159   0.0163   0.0143   0.0125   0.0207
  0.64   0.116   0.0205   0.0200   0.0242   0.0165   0.0215
  2.20   0.363   0.0226   0.0224   0.0285   0.0191   0.0205
  3.74   0.509   0.0295   0.0288   0.0352   0.0293   0.0247
  5.26   0.630   0.0308   0.0281   0.0345   0.0333   0.0274
  6.79   0.748   0.0272   0.0264   0.0315   0.0253   0.0257
  8.32   0.872   0.0252   0.0233   0.0291   0.0231   0.0254
  9.84   0.921   0.0358   0.0340   0.0356   0.0356   0.0379
Tabulated from data in file CL00666.DAT & reduced using program Q02.00D

Average Reynolds #:
 100400 
Number of angles of attack:
 11 
 alpha /   Cl   /  Cd   /  Spanwise Cd's >>>
 -4.31  -0.353   0.0264   0.0273   0.0261   0.0271   0.0254
 -2.96  -0.279   0.0203   0.0205   0.0207   0.0211   0.0191
 -1.43  -0.096   0.0135   0.0151   0.0096   0.0214   0.0079
  0.15   0.193   0.0131   0.0144   0.0127   0.0127   0.0125
  1.68   0.361   0.0146   0.0146   0.0187   0.0130   0.0120
  3.23   0.482   0.0169   0.0170   0.0191   0.0163   0.0152
  4.75   0.606   0.0176   0.0171   0.0194   0.0164   0.0175
  6.29   0.738   0.0176   0.0170   0.0180   0.0170   0.0184
  7.82   0.861   0.0203   0.0208   0.0207   0.0189   0.0209
  9.33   0.929   0.0297   0.0281   0.0289   0.0306   0.0310
 10.85   1.006   0.0416   0.0407   0.0397   0.0418   0.0440
Tabulated from data in file CL00715.DAT & reduced using program Q02.00D

Average Reynolds #:
 200400 
Number of angles of attack:
 11 
 alpha /   Cl   /  Cd   /  Spanwise Cd's >>>
 -4.79  -0.416   0.0287   0.0289   0.0293   0.0286   0.0280
 -2.32  -0.152   0.0123   0.0138   0.0096   0.0162   0.0094
 -1.40  -0.055   0.0093   0.0111   0.0081   0.0104   0.0078
  0.73   0.229   0.0099   0.0095   0.0099   0.0101   0.0101
  1.69   0.316   0.0104   0.0101   0.0105   0.0107   0.0101
  3.85   0.518   0.0112   0.0111   0.0112   0.0108   0.0116
  4.75   0.600   0.0116   0.0112   0.0117   0.0112   0.0122
  7.01   0.810   0.0134   0.0132   0.0136   0.0132   0.0135
  7.37   0.825   0.0155   0.0155   0.0146   0.0149   0.0168
  9.34   0.928   0.0249   0.0243   0.0244   0.0248   0.0260
 10.86   0.999   0.0350   0.0337   0.0339   0.0353   0.0371
Tabulated from data in file CL00723.DAT & reduced using program Q02.00D

Average Reynolds #:
 300300 
Number of angles of attack:
 11 
 alpha /   Cl   /  Cd   /  Spanwise Cd's >>>
 -4.47  -0.400   0.0234   0.0222   0.0237   0.0251   0.0228
 -2.90  -0.207   0.0122   0.0133   0.0142   0.0108   0.0104
 -2.17  -0.127   0.0116   0.0105   0.0123   0.0124   0.0111
  0.14   0.090   0.0095   0.0082   0.0089   0.0121   0.0087
  1.68   0.326   0.0086   0.0081   0.0084   0.0092   0.0089
  4.08   0.563   0.0095   0.0088   0.0100   0.0093   0.0101
  5.60   0.702   0.0108   0.0103   0.0110   0.0107   0.0112
  7.12   0.813   0.0139   0.0134   0.0128   0.0140   0.0152
  7.81   0.846   0.0170   0.0168   0.0161   0.0169   0.0181
  9.34   0.938   0.0223   0.0218   0.0219   0.0224   0.0231
 11.52   1.028   0.0378   0.0359   0.0356   0.0401   0.0396
Tabulated from data in file CL00725.DAT & reduced using program Q02.00D

File m685.drg created on 09-12-1997 at 13:46:24 using program FORMAT