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open access

Aerodynamic characteristics of a slender cone-cylinder body of revolution at a Mach number of 3.85

Description: "An experimental investigation of the aerodynamics of a slender cone-cylinder body of revolution was conducted at a Mach number of 3.85 for angles of attack of 0 degree to 10 degrees and a Reynolds number of 3.85x10(exp 6). Boundary-layer measurements at zero angle of attack are compared with the compressible-flow formulations for predicting laminar boundary-layer characteristics. Comparison of experimental pressure and force values with theoretical values showed relatively good agreement for s… more
Date: November 5, 1951
Creator: Jack, John R.
open access

Analytical study of static and low-speed performance of thin propellers using two-speed gear ratios to obtain optimum rotational speeds

Description: From Introduction: "The purpose of the present paper is to investigate the effect of two-speed gearing on the take-off efficiency under certain conditions. The present paper gives charts from which the efficiencies can be readily computed for optimum rotational speeds. Also included is a brief discussion of the static thrust of thin propellers, including the effect of camber on the static thrust."
Date: November 5, 1952
Creator: Gilman, Jean, Jr.
open access

Comparison of Transonic Characteristics of Lifting Wings From Experiments in a Small Slotted Tunnel and the Langley High-Speed 7- by 10-Foot Tunnel

Description: Report presenting a comparison of the transonic aerodynamic characteristics of unswept and 45 degree sweptback wings in the high-speed tunnel and slotted tunnel. The purpose of the investigation was to explore the possibilities and limitations associated with transonic testing of relatively large wings in a rectangular slotted tunnel. Results regarding lift, pitching moments, drag, bending moments, and Schileren photographs are provided.
Date: November 5, 1951
Creator: Sleeman, William C., Jr.; Klevatt, Paul L. & Linsley, Edward L.
open access

An Investigation of a 0.16-Scale Model of the Douglas X-3 Airplane to Determine Means of Improving the Low-Speed Longitudinal Stability and Control Characteristics

Description: Report presenting an investigation of a model of the Douglas X-3 to determine some methods to improve the low-speed longitudinal stability and control characteristics. Some of the components tested included plain and slotted leading-edge flaps and plain, split, and slotted trailing-edge flaps. Results regarding the effect of various factors on longitudinal stability and flap characteristics are presented.
Date: November 5, 1952
Creator: McKee, John W. & Riebe, John M.
open access

A Multiple-Range Self-Balancing Thermocouple Potentiometer

Description: "A multiple-range potentiometer circuit is described that provides automatic measurement of temperatures or temperature differences with any one of several thermocouple-material pairs. Techniques of automatic reference junction compensation, span adjustment, and zero suppression are described that permit rapid selection of range and wire material, without the necessity for restandardization, by setting of two external tap switches" (p. 1).
Date: November 5, 1951
Creator: Warshawsky, I. & Estrin, M.
open access

Preliminary results of turbojet-engine altitude-starting investigation

Description: A spark energy of 2.13 joules per spark at 1 spark per second produced ignition to an altitude of 50,000 feet at a flight Mach number of 0.6. The minimum power requirements for ignition were obtained from a combination of low spark repetition rates and high spark energy. The altitude-ignition limit was also increased by increasing spark-gap immersion, fuel temperature, inlet-air temperature, and fuel volatility, and by decreasing flight Mach number. The maximum altitude at which flame propagati… more
Date: November 5, 1951
Creator: Wilsted, H. D. & Armstrong, J. C.
open access

Some Low-Speed Studies of the Effects of Wing Location on Wing-Deformation-Body-Freedom Flutter

Description: Report presenting an investigation of flutter of wings mounted on the after portion of a body free to pitch was made in the flutter research tunnel. Uniform wings of 0 and 45 degrees sweep were tested at various positions rearward of the pitch axis. A low-frequency flutter was observed on the unswept wing, but no flutter was obtained for the swept wings.
Date: November 5, 1952
Creator: Widmayer, E., Jr.
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