REALLY HIGH SPEED PROPULSION BY SCRAMJETS

reportActive / Technical Report | Accession Number: AD0638520 | Open PDF

Abstract:

The high overall efficiency of the scramjet engine is potentially maintained over the speed range from Mach 5 to 20. At higher speeds, hydrogen fuel is essential and a fixed geometry appears feasible. Optimization of the intake diffusion can be carried out most easily in terms of the intake process efficiency and velocity ratio. The optimum amount of diffusion is reduced when realistic nozzle losses are included. The development of a hypersonic flight test vehicle is recommended.

Author(s):
Curran, E. T. ; Swithenbank, J.
Author Organization(s):
SHEFFIELD UNIV (UNITED KINGDOM) DEPT OF CHEMICAL ENGINEERING AND FUEL TECHNOLOGY
Descriptive Note:
Scientific rept.
Supplementary Note:
Pub. in Aircraft Engineering.
Annotation:
High speed propulsion by scramjets.
Pagination:
0035

Security Markings

DOCUMENT & CONTEXTUAL SUMMARY

Distribution:
Approved For Public Release

RECORD

Collection: TR
Identifying Numbers
Report Number(s):
HIC-67, AFOSR-66-1861
Contract/Grant Number(s):
AF-EOAR-23-65
Task Number(s):
971101
Project Number(s):
AF-9711
Monitor Series:
66-1861, AFOSR
 Subject Terms
Joint Capability Areas:
JCA_3.2_Engagement; JCA_3_Force Application; JCA_3.2.1_Kinetic Means; JCA_8.2.4_Leverage Capacities and Capabilities of Security Establishments; JCA_8.2_Shape; JCA_8_Building Partnerships; JCA_5_Command and Control; JCA_5.3_Planning; JCA_1.2_Force Preparation; JCA_1_Force Support; JCA_6.4.1_Secure Information Exchange; JCA_6_Net Centric; JCA_1.4.2_Health Service Delivery; JCA_1.4_Force Support
Communities of Interest:
Weapons Technologies
Descriptor(s):
*RAMJET ENGINES, OPTIMIZATION, PERFORMANCE(ENGINEERING), HYDROGEN, FUELS, PROPULSION SYSTEMS, NOZZLES, DIFFUSION, SUPERSONIC FLOW, HYPERSONIC FLIGHT, UNITED KINGDOM
Field(s)/Group(s):
Jet and Gas Turbine Engines
Keyword(s):
SCRAM, FOREIGN REPORT
Report Date:
1965 Oct 01