Altitude Simulation by Test Cell 1-42B During Rocket Motor Firings of Short Duration
Abstract
Twelve rocket motor firings were performed to determine propulsion efficiencies of two propellant formulations at high expansion ratios because the rocket exhaust gases produced by different propellant formulations will behave uniquely when expanded to the low pressure of high altitudes and may, therefore, provide varying propulsion efficiencies. These efficiencies may differ from the efficiencies of sea level firings at lower expansion ratios. It is obviously important that the delivered performance of a propellant at high altitude be known for system design calculations. The altitude simulation facility provided pressure altitudes above 100,000 feet, and all motor firings were successful.
Document Details
- Document Type
- Technical Report
- Publication Date
- Mar 01, 1969
- Accession Number
- AD0862744
Entities
People
- John Denker
Organizations
- Air Force Research Laboratory