-internal drag of nacelle Cd +- 0.00005

-corrections for alpha,Machnumber,static and dynamic pressure,
 Reynoldsnumber, aerodynamic coefficients (CAC,CYAC,CNC,CLAC,CMAC,
 CNAC,CXC,CYC,CZC,CLAAC,CMAAC,CNAAC)

-accuracy: Ma 0.75 +- 0.015, Re 3e6 +- 0.015, T 305K +- 1K
           at the above conditions
           CA,CX  +-0.0001
           CZ(alpha) +-0.01 deg

-transitionstrips (depth: 2mm) on wing, fuselage nose and nacelle front

  lower wing root, kink and tip: x/c =  25%, height 50 mue m, grain no 240
  upper wing root: x/c = 5%, kink x/c = 15%, eta = 0.844 x/c = 15%, 
                  tip x/c 5%, height 63 mue m, grain no 220

  fuse nose at x = 15 mm, height 76 mue m, grain no 180

  nacelle (from inlet plane) inside at 15 mm, height 102 mue m, grain no 120
                             outside at 12 mm, height 220 mue m, grain no 63

-pressure taps wing at etas: 0.15, 0.238, 0.331, 0.377, 0.409, 0.512, 0.636, 0.844

-pressure taps on nacelle cfm 56 at 60, 180 and 300 deg (0 deg at wing attachment point)

-mutual Machnumbers for clean geometry and geometry with long naclles position 1:
 0.72 / 0.74 / 0.75 / 0.76 / 0.77

-Z-sting mount in wind tunnel