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The Effect of Moment-of-Area-Rule Modifications on the Zero-Lift Drag of Three Wing-Body Combinations
Memorandum presenting an experimental investigation to determine the effect on drag of applying the moment-of-area-rule modifications to wing-body combinations with various wing plan forms. The effect of mounting air-to-air type missiles on the wing-mounted bodies of revolution which are part of the moment-of-area-rule modification was also investigated.
Date:
May 2, 1958
Creator:
Dickey, Robert R.
System:
The UNT Digital Library
Effects of Modifications to a Control Surface on a 6-Percent-Thick Unswept Wing on the Transonic Control-Surface Flutter Derivatives
Transonic flutter derivatives for unswept wing control surface configurations determined by pressure cell measurements. The control surfaces were mounted on a wing with an aspect ratio of 3, a taper ratio of 0.6, and a wing-thickness ratio of 0.06. Results regarding aerodynamic balance, vortex generators, splitter-plate configurations, and wedges are provided.
Date:
May 2, 1958
Creator:
Wyss, John A.; Sorenson, Robert M. & Gambucci, Bruno J.
System:
The UNT Digital Library
Effects of modifications to a control surface on a 6-percent-thick unswept wing on the transonic control-surface flutter derivatives
Report presenting a determination of transonic flutter characteristics from pressure cell measurements on control surfaces sinusoidally oscillated at an amplitude of plus or minus 1.08 degrees at frequencies from 5 to 30 cycles per second. Various control-surface configurations were investigated, including internal and external aerodynamic balance, vortex generators, a splitter-plate type of control surface, and superposition of triangular shaped wedges or tetrahedra along the rear portion of the control-surface chord.
Date:
May 2, 1958
Creator:
Wyss, John A.; Sorenson, Robert M. & Gambucci, Bruno J.
System:
The UNT Digital Library
Experimental results of an investigation of two methods of inflight thrust measurement applicable to afterburning turbojet engines with ejectors
Report presenting an investigation in an altitude test chamber using a turbojet engine equipped with an afterburner and ejector to compare directly two techniques of determining thrust that are both applicable to flight installations. One method uses a swinging uncooled rake at the ejector outlet while the other requires extensive instrumentation to measure the momentum forces of systems and the force on the internal surface of the ejector nozzle. Results regarding the swinging-rake technique and internal-pressure technique are provided.
Date:
May 2, 1958
Creator:
Bloomer, Harry E.
System:
The UNT Digital Library
Investigation of Flutter Characteristics of Three Low-Aspect-Ratio All-Movable Half-Span Control Surfaces at Mach Numbers From 1.49 to 2.87
Memorandum presenting results of a supersonic flutter investigation of three low-aspect-ratio control surfaces. Two controls were all-movable but the third had a fixed cutout. Results regarding the experiments and calculations are provided.
Date:
May 2, 1958
Creator:
Morgan, Homer G.; Figge, Irving E. & Presnell, John G., Jr.
System:
The UNT Digital Library
Investigation of Flutter Characteristics of Three Low-Aspect-Ratio All-Movable Half-Span Control Surfaces at Mach Numbers From 1.49 to 2.87
Report presenting the results of a supersonic flutter investigation of three low-aspect-ratio control surfaces, two which had all-movable controls and one with a fixed cutout. Experimental results are provided and compared to calculations using the piston theory for plan form 2. Modifications for improving the flutter of the various control surfaces are also described.
Date:
May 2, 1958
Creator:
Morgan, Homer G.; Figge, Irving E. & Presnell, John G., Jr.
System:
The UNT Digital Library