CALCULATIONS OF THE FLOW CONDITIONS IN A CONSTANT BASE PRESSURE LAUNCHER WITH A REAL HYDROGEN GAS PROPELLANT,
Abstract
The constant base pressure process in a hypervelocity launcher is the subject of investigation. The barrel entrance and reservoir pressures required to achieve a constant pressure at the projectile base are calculated. These pressures are calculated for both an ideal-gas propellant and a real hydrogen propellant. Comparison is made between the chambered case when sonic flow speed is required at the barrel entrance to the unchambered case when supersonic flow occurs. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Nov 14, 1966
- Accession Number
- AD0660662
Entities
People
- A. E. Siegel
- D. N. Bixler
Organizations
- Naval Ordnance Laboratory