THE FEASIBILITY OF A MACH 7 TRANSPORT EMPLOYING AIRBREATHING PROPULSION SYSTEMS.

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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

Author(s):
Pietrangeli, G. J. ; Nice, E. V.
Author Organization(s):
JOHNS HOPKINS UNIV SILVER SPRING MD APPLIED PHYSICS LAB
Descriptive Note:
Revised ed.,
Supplementary Note:
Revision of manuscript received 15 Nov 60.
Pagination:
0173

Security Markings

DOCUMENT & CONTEXTUAL SUMMARY

Distribution:
Approved For Public Release

RECORD

Collection: TR
Identifying Numbers
Report Number(s):
CF-2900
Contract/Grant Number(s):
Nord-7386
 Subject Terms
Joint Capability Areas:
JCA_4.1_Deployment and Distribution
Modernization Areas:
Hypersonics
Communities of Interest:
No COI(s) Identified
Descriptor(s):
(*TRANSPORT AIRCRAFT, *RAMJET ENGINES), HYPERSONIC FLIGHT, PERFORMANCE(ENGINEERING), FEASIBILITY STUDIES, TURBOJET ENGINES, LIFT, PROPULSION SYSTEMS, AERODYNAMIC CHARACTERISTICS
Field(s)/Group(s):
Transport Aircraft, Jet and Gas Turbine Engines
Report Date:
1961 Jul 01