A Thrust Computer for Turbo-Jet Engines
Abstract
The Thrust of a turbo-jet engine is the primary parameter indicating engine performance, but this parameter is not directly measurable during flight. Gross thrust can be expressed as a thermodynamic function of exhaust and ambient pressures and engine constants. Thus, gross thrust must be determined during flight by automatic computing techniques. An airborne analog computer has been designed, constructed, and evaluated at the Naval Research Laboratory for continuous solution of gross thrust.
Document Details
- Document Type
- Technical Report
- Publication Date
- Mar 16, 1950
- Accession Number
- AD1214353
Entities
People
- E. S. Van Valkenburg
Organizations
- United States Naval Research Laboratory