The influence of body geometry and flow conditions on axisymmetric velocity distributions at subcritical Mach numbers.
Abstract:ESDU 78037 gives curves for velocity distribution using results from a computation method that allows iteratively for the displacement effect of the boundary layer and wake. Comparison of the results with experiment in one case shows the accuracy of the method to be within 1 per cent right up to the tail. The curves are plotted to show the effect of various geometry and flow changes on the velocity distribution: forebody length, forebody shape, afterbody length and shape, fineness ratio, Reynolds number, Mach number. ESDU 78019 and 79020 respectively give results computed with the same program for the profile drag and the boundary layer development for the same families of bodies made up of a forebody, afterbody and a cylindrical central portion.
|Data Item ESDU 78037|
- 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