THE FEASIBILITY OF A MACH 7 TRANSPORT EMPLOYING AIRBREATHING PROPULSION SYSTEMS.
Abstract
An extensive study of various propulsion and performance aspects of a single stage long range Mach 7 delta wing transport, 30,000 lb payload (125 passengers and cargo), was completed. The study encompasses consideration of the propulsive performance of a hypersonic ramjet design featuring lift augmentation. Particular attention is given to the influence of geometry, equivalence ratio, diffuser recovery characteristics, and boundary layer bleed on this performance. Considerable attention is given to climb and acceleration which is accomplished in two phases; a Mach 0-3.6 turbojet phase, and a Mach 3.6-7.0 ramjet phase. The significance of the number of turbojet engines, ramjet engine size, called-for tangential acceleration, and gross weight at take-off for trajectory characteristics, climb-time, climb-fuel and climb-range is presented. The results demonstrate that it is technically feasible to construct a hypersonic transport of intercontinental range. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Jul 01, 1961
- Accession Number
- AD0654428
Entities
People
- E. V. Nice
- G. J. Pietrangeli
Organizations
- Johns Hopkins University Applied Physics Laboratory