Hypersonic Waverider Configurations for Trans-Atmospheric Vehicles

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Abstract:

This thesis describes the development of a catalogue of waverider shapes generated from axisymmetric conical flow. A simple but reliable method of calculating the viscous drag is presented and over one-hundred configurations are shown with various aerodynamic and pertinent geometric design factors. All of the configurations presented are based on Mach number of 10 and Reynolds number based on the length of the waverider of 10 to the 6th power. However, the analysis presented here adapts itself to any Mach or Reynolds number. The lift-to-drag ratios presented range from 4.32 to 5.06 while the average skin friction coefficient ranged from 0.00176 to 0.00205. The volume to area ratio V23Sp ranged from 0.224 to 0.153. Keywords Hypersonic waverider configurations, Hypersonic missiles, Aircraft characteristics.

Author(s):
Martin, William P.
Author Organization(s):
AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH
Descriptive Note:
Master's thesis
Pagination:
0198

Security Markings

DOCUMENT & CONTEXTUAL SUMMARY

Distribution:
Approved For Public Release

RECORD

Collection: TR
Identifying Numbers
Report Number(s):
AFIT/CI/CIA-89-105
Monitor Series:
AFIT
 Subject Terms
Joint Capability Areas:
JCA_1_Force Support; JCA_1.1_Force Management; JCA_5_Command and Control; JCA_5.3_Planning; JCA_3.2_Engagement; JCA_3_Force Application; JCA_3.2.1_Kinetic Means; JCA_1.2_Force Preparation; JCA_1.2.3_Educating; JCA_1.3_Human Capital Management; JCA_1.3.2_Personnel Management
Communities of Interest:
Air Platforms
Descriptor(s):
*CONICAL BODIES, *HYPERSONIC VEHICLES, *AXISYMMETRIC FLOW, GUIDED MISSILES, RATIOS, COMPUTATIONS, AIRCRAFT, RELIABILITY, COEFFICIENTS, LIFT TO DRAG RATIO, SKIN FRICTION, REYNOLDS NUMBER, LENGTH, GEOMETRY, MACH NUMBER, DRAG, VISCOSITY
Field(s)/Group(s):
Aerodynamics, Research and Experimental Aircraft
Report Date:
1988 Jan 01
Creation Date:
1990 Mar 29