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A Transonic Wind-Tunnel Investigation of the Performance and of the Static Stability and Control Characteristics of a 1/15-Scale Model of the Grumman F9F-9 Airplane, Ted No. NACA DE 390

Description: Report presenting an investigation of the aerodynamic characteristics of a model of the Grumman F9F-9 airplane in the transonic tunnel. Results regarding the transonic drag-rise increment, drag analysis, and effective downwash angle are provided.
Date: October 1, 1954
Creator: Bielat, Ralph P.
Item Type: Refine your search to only Report
open access

Investigation at high subsonic speeds of finned and unfinned bodies mounted at various locations from the wings of unswept- and swept-wing--fuselage models, including measurements of body loads

Description: Report presenting an investigation to determine the effects of location of bodies (finned and unfinned) on the aerodynamic characteristics of unswept- and swept-wing--fuselage models and to determine the aerodynamic loads on the bodies in the presence of the wings. Results for the complete model characteristics and for the body are provided.
Date: April 1, 1954
Creator: Alford, William J., Jr. & Silvers, H. Norman
Item Type: Refine your search to only Report
open access

Starting and performance characteristics of a large asymmetric supersonic free-jet facility

Description: Report presenting the characteristics of an asymmetric free-jet facility constructed to investigate a 48-inch-diameter ramjet engine and the associated asymmetric supersonic inlet and inlet diffuser. The design flow Mach number of 2.755 could not be established in the free-jet facility with dry inlet air at a temperature of 528 degrees Fahrenheit and overall pressure ratios up to 11.
Date: April 1, 1954
Creator: Seashore, Ferris L. & Hurrell, Herbert G.
Item Type: Refine your search to only Report
open access

A transonic wind-tunnel investigation of the effects of twist and camber with and without incidence, twist and body indentation on the aerodynamic characteristics of a 45 degree sweptback wing-body configuration

Description: Report presenting a transonic wind-tunnel investigation of several sweptback wing-body configurations to determine the effects of twist and camber with incidence, the separate effects of twist without camber, and the influence of body indentation on the effects of twist and camber, and twist alone.
Date: April 1, 1954
Creator: Cooper, J. Lawrence
Item Type: Refine your search to only Report
open access

Experimental data for four full-scale conical cooling-air ejectors

Description: Report presenting an experimental investigation to determine the pumping and thrust characteristics of four full-scale conical air ejectors over a range of primary gas temperature. The spacing ratio was found to influence both ejector pumping and thrust performance. Results regarding the ejector performance and ejector-shroud wall pressure distribution are also provided.
Date: November 1, 1954
Creator: Ciepluch, C. C. & Fenn, D. B.
Item Type: Refine your search to only Report
open access

The Use of Area Suction to Increase the Effectiveness of a Trailing-Edge Flap on a Triangular Wing of Aspect Ratio 2

Description: "A wind-tunnel investigation was conducted to determine the effect of applying area-suction boundary-layer control to a constant-chord plain flap on a triangular wing of aspect ratio 2. The results showed that with small amounts of suction applied near the leading edge of the flap, high lift at relatively low attitudes can be obtained" (p. 1). The typical lift, drag, pitching-moment data, effects of the porous area, effects of suction, and comparison of theoretical and experimental flap lift ar… more
Date: April 1, 1954
Creator: Kelly, Mark W. & Tolhurst, William H., Jr.
Item Type: Refine your search to only Report
open access

Performance of Five Low-Temperature-Ratio Ram-Jet Combustors Over Range of Simulated Altitudes

Description: Memorandum presenting the analysis of direct-connect performance data obtained with five flame holders of various gutter and can types operated in a 20-inch-diameter ramjet engine at Mach number 3, which revealed that the specific impulse of each of the flame holders was about the same. The combustion-chamber length had a marked effect on specific impulse. Results regarding flame-holder performance and effect of combustion-chamber length on flame-holder performance are provided.
Date: November 1, 1954
Creator: Wentworth, Carl B.
Item Type: Refine your search to only Report
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