Axial pressure coefficient distributions for forebodies of fineness ratio 1.0, 1.5 and 2.0 at zero incidence in transonic flow.
Abstract:ESDU 80008 presents charts of the distribution of forebody pressure coefficient for spherically blunted tangent ogive, spherically blunted paraboloid and modified ellipsoid forebodies of fineness ratio 1.0, 1.5 and 2.0 at zero incidence over a Mach number range from 0.4 to 1.05. It complements ESDU 79004 which presents wave drag data for the same families of forebody shapes. The charts were derived by use of a computer program developed at the Aircraft Research Association and based on a modified version of the South-Jameson finite difference method which calculates the inviscid transonic potential flow around axisymmetric forebodies. Although the calculations are for inviscid flow they are applicable to real flows at moderate to high Reynolds number where the boundary layers are thin and flow separations are absent.
|Data Item ESDU 80008|
- 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