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Results of initial wind-tunnel flutter experiments at low speed with a towed airplane model having a 40 degree sweptback wing of aspect ratio 3.62 equipped with pylon-mounted stores

Description: Report presenting wind-tunnel flutter testing at a range of Mach numbers conducted on a swept-wing towed airplane model equipped with an autopilot system. Results regarding the towed model tests, fixed-root tests, and a comparison between the calculated and experimental flutter characteristics are provided.
Date: March 24, 1955
Creator: Martina, Albert P. & Young, George E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Investigation of a Cermet Gas-Turbine-Blade Material of Titanium Carbide Infiltrated With Hastalloy C

Description: A cermet composition was investigated as a potential material for gas-turbine blades. Blades of HS-21 alloy were also operated in the engine simultaneously to provide a basis of comparison. The cermet blades survived as long as approximately 312-1/2 hours at about 1500 degrees F with an average midspan centrifugal stress of approximately 11,500 psi.
Date: January 24, 1955
Creator: Hoffman, Charles A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Investigation of a High-Performance Axial-Flow Compressor Transonic Inlet Rotor Designed for 37.5 Pounds Per Second Per Square Foot of Frontal Area: Aerodynamic Design and Overall Performance

Description: Report presenting an investigation of the design and tests of a transonic inlet rotor with emphasis placed on increasing the design specific weight flow while maintaining reasonably high pressure ratio and efficiency. Information regarding peak efficiency and how to best achieve it through design is provided.
Date: March 24, 1955
Creator: Savage, Melvyn & Felix, A. Richard
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

The Wave Drag of Arbitrary Configurations in Linearized Flow as Determined by Areas and Forces in Oblique Planes

Description: "The wave drag, based on linearized theory, of any lifting or non-lifting planar or nonplanar object in a steady supersonic flow is shown to be identical at a fixed Mach number to the average wave drag of a series of equivalent bodies of revolution. The streamwise gradient of area, measured normal to the free stream, at a section of each of these equivalent bodies of revolution is given by the sum of two quantities: 1. the streamwise gradient of area, measured in parallel oblique planes tangent… more
Date: March 24, 1955
Creator: Lomax, Harvard
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

A flight investigation at transonic speeds of a model having a triangular wing of aspect ratio 3

Description: Report presenting free-falling recoverable-model tests at transonic speeds on a model with a triangular wing of aspect ratio 3 and a 45 degree swept tail located in the chord plane of the wing. Static and dynamic longitudinal-stability data for the complete model, force and moment data for the major components of the model, and load distributions over the fuselage of the model were evaluated at a range of angles of attack. results regarding lift, drag, static longitudinal stability, dynamic lon… more
Date: June 24, 1955
Creator: White, Maurice D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

The longitudinal characteristics at Mach numbers up to 0.92 of several wing-fuselage-tail combinations having sweptback wings with NACA four-digit thickness distributions

Description: Report presenting a wind-tunnel investigation to determine the effects of various wing-fence arrangements on the longitudinal characteristics of several wing-fuselage and wing-fuselage-tail combinations with sweptback wings with NACA four-digit thickness distributions. Testing occurred with wings of several degrees of sweepback and a horizontal tail at several tail heights. Results regarding fence development, wing-fuselage combinations, and wing-fuselage-tail combinations are provided.
Date: March 24, 1955
Creator: Sutton, Fred B. & Dickson, Jerald K.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Description and bibliography of NACA research on wing controls: January 1946 - February 1955

Description: Report presenting some accompanying tables and bibliography for experimental aerodynamic studies in the field of wing controls during the period between January 1946 and February 1955. The tables are grouped according to the following major classifications: trailing-edge flap controls, leading-edge flap controls, and spoiler controls.
Date: March 24, 1955
Creator: Brewer, Jack D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

A Flight Investigation at Transonic Speeds of a Model Having a Triangular Wing of Aspect Ratio 4

Description: Report presenting testing of free-falling recoverable-model tests at transonic speeds on a model with an aspect-ratio-4 triangular wing and a 45 degree sweptback tail in the extended wing-chord plane. Results regarding the lift, drag, stability, tail effectiveness, and buffet boundary are provided.
Date: March 24, 1955
Creator: Bright, Loren G.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

A study of the application of airfoil section data to the estimation of the high-subsonic-speed characteristics of swept wings

Description: Report presenting estimates of the variation with Mach number of the aerodynamic characteristics of swept wings on the basis of airfoil section data combined with span-loading theory. Results regarding adjusted wing theory procedure and adjusted wing data procedure are provided.
Date: June 24, 1955
Creator: Hunton, Lynn W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

A comparative analysis of the performance of long-range hypervelocity vehicles

Description: From Summary: "Long-range hypervelocity vehicles are studied in terms of their motion in powered flight, and their motion and aerodynamic heating in unpowered flight. Powered flight is analyzed for an idealized propulsion system which rather closely approaches present-day rocket motors. Unpowered flight is characterized by a return to earth along a ballistic, skip, or glide trajectory. Only those trajectories are treated which yield the maximum range for a given velocity at the end of powered f… more
Date: March 24, 1955
Creator: Eggers, Alfred J., Jr.; Allen, H. Julian & Neice, Stanford E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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