Preliminary Design and Experimental Investigation of the FDL-5A Unmanned High L/D Spacecraft: Part I - Summary

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Report Number: AFFDL TR 68-24 Part 1
Author(s): Lloyd, J. T.
Corporate Author(s): Lockheed-California Company
Laboratory: Air Force Flight Dynamics Laboratory
Date of Publication: 1968-03
Pages: 89
Contract: AF 33(615)-5241
DoD Project: 1366
DoD Task: 136616
Identifier: AD0390193

Conceptual design and experimental wind tunnel testing of unmanned entry research vehicles having high hypersonic lift/drag ration and high volume are desribed. Analytic parametic data are presented for two lifting body classes designated HLD-35 and FDL-5. The FDL-5 is a unique configuration which is aerodynamically stabilized without outboard fins. Experimental aerodynamic and heat transfer data from the Arnold Engineering Development Center Wind Tunnels A, B, C and F are compared with analytic data for the FDL-5. Candidate structure and subsystems are selected for performing unmanned hypersonic research with the vehicle.

Provenance: AFRL/VACA

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