Inviscid supersonic flow past cones at zero incidence: (i) shock angle.
Abstract:ESDU 70008, which is one of a series of four, presents data for the shock angle of a sharp-nosed right-circular cone at zero incidence in a uniform, inviscid, supersonic airflow. The data, given in carpet form, are for upstream Mach numbers increasing from the shock detachment value to a value of 4 for cones with semi-vertex angles from zero to 50 degrees and were obtained from an exact solution of the conical flow equations.
|Data Item ESDU 70008|
- 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