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Use of Shock-Trap Bleed to Improve Pressure Recovery of Fixed-and Variable-Capture-Area Internal-Contraction Inlets; Mach Number 2.0 to 3.0
Report presenting an investigation of two internal-contraction inlets in the block tunnel. The fixed inlet was tested at Mach number 2.94 with a conventional ram-scoop bleed and a shock-trap bleed. Results regarding the fixed-capture-area inlet and variable-capture-area inlet are provided.
Date:
August 14, 1958
Creator:
Luidens, Roger W. & Flaherty, Richard J.
System:
The UNT Digital Library
Wind-Tunnel Investigation of the Effect of Sweep and Taper Ratio on Effectiveness of Spoiler-Slot-Deflector Controls on Aspect-Ratio-4 Wings at Transonic Speeds
Report presenting a wind-tunnel investigation performed in the high-speed tunnel to study the effect of wing sweep and taper ratio on spoiler-slot-deflector control effectiveness. All of the wings tested were aspect-ratio-4 and had NACA 65A004 airfoil sections as well as a variety of sweep angles, taper ratios, and spoiler projections. The results are presented without analysis.
Date:
August 14, 1958
Creator:
Hammond, Alexander D. & McKinney, Linwood W.
System:
The UNT Digital Library
Longitudinal and lateral aerodynamic characteristics at combined angles of attack and sideslip of a generalized missile model having a rectangular wing at a Mach number of 4.08
Report presenting an investigation in the 9- by 9-inch Mach number 4 blowdown jet on a generalized body-wing-tail missilelike configuration to determine the source of the adverse rolling moment due to yaw experienced by this type of configuration with lifting surfaces and ventral and dorsal tail surfaces. Results regarding the longitudinal characteristics and lateral characteristics are provided.
Date:
August 14, 1958
Creator:
Smith, Fred M.; Ulmann, Edward F. & Dunning, Robert W.
System:
The UNT Digital Library
An Experimental Investigation of Two Internal-Compression Air-Inlet Designs Which Use Fluid Boundaries as a Means of Supersonic Compression
Report presenting an investigation of the internal-flow characteristics of two novel designs of internal-compression air inlets in the supersonic blowdown tunnel. A longitudinally slotted contracting channel and effective contracting channel formed by the natural thickening of the boundary layer in a confined channel can be used to obtain pressure recoveries at a satisfactory level.
Date:
August 14, 1958
Creator:
Howell, Robert R. & Trescot, Charles D., Jr.
System:
The UNT Digital Library