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Investigation of the Static Stability Characteristics of Five Hypersonic Missile Configurations at Mach Numbers From 2.29 to 4.65
Report presenting an investigation to determine the static stability characteristics of five hypersonic missile configurations. Testing was performed at a range of Mach and Reynolds numbers. Results regarding the effect of base block, longitudinal stability, directional stability, and Reynolds number effect are provided.
Date:
June 30, 1958
Creator:
Turner, Kenneth L. & Appich, W. H., Jr.
System:
The UNT Digital Library
A Flight-Test Study of Total-Pressure Distortion in a Thick-Lipped Nose Inlet
Memorandum presenting flight tests conducted on a thick-lipped nose inlet of a transonic swept-wing aircraft. The total-pressure recovery and distortion at the compressor face were measured over the maneuvering range of the airplane for Mach numbers up to 1.03. Results regarding the radial total-pressure profile, average total-pressure recovery, and total-pressure distortion are provided.
Date:
June 30, 1958
Creator:
Wingrove, Rodney C.
System:
The UNT Digital Library
Investigation of the Static Stability Characteristics of Five Hypersonic Missile Configurations at Mach Numbers From 2.29 to 4.65
Report presenting an investigation in the Unitary Plan wind tunnel to determine the static stability characteristics of five hypersonic missile configurations. Tests were performed at a range of Mach and Reynolds numbers based on body length. Results regarding the effect of a base block, longitudinal and directional stability, and Reynolds number effect are provided.
Date:
June 30, 1958
Creator:
Turner, Kenneth L. & Appich, W. H., Jr.
System:
The UNT Digital Library
Transonic investigation of yawed wings of aspect ratios 3 and 6 with a Sears-Haack body and with symmetrical and asymmetrical bodies indented for a Mach number of 1.20
Report presenting an investigation to determine the experimental and predicted wave-drag characteristics of wing-body combinations. Two yawed wings, each with an average sweep of about 40 degrees, were tested with various bodies, and the results were compared with existing data for similar models with sweptback wings. Results regarding the aerodynamic characteristics and pressure results are provided.
Date:
June 30, 1958
Creator:
Holdaway, George H. & Hatfield, Elaine W.
System:
The UNT Digital Library
Viscous Flows in Inlets
Report discusses ways to reduce "viscous effects", which increase total pressure losses due to friction at increasing free-stream Mach numbers. Some of the effects are related to the inlet of an aircraft and potential issues in design. From Introduction: "Care must be exercised in inlet design to maintain uniform steady boundary-layer and core flows in the throat."
Date:
June 30, 1958
Creator:
Scherrer, Richard; Lundell, John H. & Anderson, Lewis A.
System:
The UNT Digital Library