Foredrag of spherically-blunted conical forebodies at zero incidence in supersonic flow for Mach numbers up to 5.
Abstract:ESDU 68021 gives the total forebody drag, including skin friction and boundary layer normal pressure (or wave) drag components, taking account of the effects of viscosity, for spherically blunted cones at zero incidence and supersonic Mach numbers up to 5. The largely empirical data are presented in the form of a foredrag coefficient as a function of freestream Mach number (between 1 and 5) and cone semi-vertex angle (between 5 and 60 degrees) for values of blunting ratio, radius of nose blunting to radius of cone, of 0, 0.2, 0.4, 0.6, 0.8 and 1.0. The geometry and flow characteristics overlap those for normal pressure drag given in ESDU 82028 for Mach numbers of 3 and above.
|Data Item ESDU 68021|
- Aircraft Noise
- Fatigue - Endurance Data
- Fatigue - Fracture Mechanics
- Fluid Mechanics, Internal Flow
- Fluid Mechanics, Internal Flow (Aerospace)
- Heat Transfer
- Physical Data, Chemical Engineering
- Stress and Strength
- Transonic Aerodynamics
- Vibration and Acoustic Fatigue
- Wind Engineering
Aerospace Materials Data
Additional Engineering References