Axial pressure coefficient distributions for spherically blunted secant ogive forebodies of fineness ratio 1.0, 1.5 and 2.0 at zero incidence in transonic flow.
Abstract:ESDU 83018 gives graphs showing the axial variation of the pressure coefficient along the length of the forebodies for which wave drag data are given in ESDU 83017. The Mach number range is from 0.40 to 1.05. The data were calculated using a program based on a modified version of the South-Jameson finite difference method for inviscid transonic flow around unducted axisymmetric bodies. However, the results apply to real flow at moderate to high Reynolds number when the boundary layers are thin and no flow separations occur. Data for spherically blunted tangent ogive forebodies are in ESDU 80008.
|Data Item ESDU 83018|
- 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