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in subjects: "aircraft design"  
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Drag of a Wing-Body Configuration Consisting of a Swept-Forward Tapered Wing Mounted on a Body of Fineness Ratio 12 Measured During Free Fall at Transonic Speeds

Description: Report discussing an investigation to determine the drag of a configuration with a body of fitness ratio 12 with stabilizing tail surfaces and a 12-percent-thick 30-degree swept-forward wing using the free-fall method. The drag oft he wing and the total drag were measured separately and compared. The swept-forward wing was found to greatly increase the effect of drag on the body-tail combination.
Date: March 13, 1947
Creator: Thompson, Jim Rogers & Mathews, Charles W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Flight Tests to Determine the Effect of Taper on the Zero-Lift Drag of Wings at Low Supersonic Speeds

Description: Report presenting the results of tests to determine the effect of taper on the zero-lift drag of wings of constant exposed aspect ratio at low supersonic speeds. Findings indicated that maximum thickness, leading-edge, and trailing-edge sweep are all important in determining the drag coefficient of a tapered wing.
Date: July 13, 1947
Creator: Alexander, Sidney R. & Nelson, Robert L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Investigation of Interference, Lift, Drag, and Pitching Moment of a Series of Rectangular Wing and Body Combinations at Mach Numbers of 1.62, 1.93,and 2.41

Description: Report presenting an investigation of a series of rectangular wing and body combinations at Mach numbers 1.62, 1.93, and 2.41 to determine the effects of aspect ratio, incidence angle, and forebody length on the interference lift, drag, and pitching moment. A limited investigation to determine the effect of Reynolds number on the wings in the presence of the body was also carried out. Information regarding wing lift, basic quantities for interference evaluation, interference qualities, contribu… more
Date: August 13, 1952
Creator: Coletti, Donald E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effect of design changes and operating conditions on combustion and operational performance of a 28-inch diameter ram-jet engine

Description: The results of an altitude test-chamber investigation of the effects of a number of design changes and operating conditions on altitude peformance of a 28-inch diameter ram jet engine are presented. Most of the investigation was for a simulated flight Mach number of 2.0 above the tropopause. Fuel-air distribution, gutter width, the presence of a pilot flame, cimbustion-chamber-inlet temperature, and exhaust-nozzle throat area were found to have significant effects on limits of combustion. Combu… more
Date: February 13, 1952
Creator: Shillito, T. B. & Nakanishi, Shigeo
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Transonic Investigation of the Effectiveness and Loading Characteristics of a Flap-Type Aileron With and Without Paddle Balances of an Unswept-Wing-Fuselage Model

Description: Report presenting an investigation of the effectiveness and loading characteristics of an aileron mounted on an unswept-wing-body configuration. A flap-type outboard aileron was tested with and without paddle balances at a range of Mach numbers and angles of attack. The aileron effectiveness, hinge-moment parameter, and effect of the paddle balances are presented.
Date: April 13, 1956
Creator: Hieser, Gerald
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Force and Pressure-Distribution Measurements at a Mach Number of 3.12 of Slender Bodies Having Circular, Elliptical, and Triangular Cross Sections and the Same Longitudinal Distribution of Cross-Sectional Area

Description: Report presenting an investigation to determine the aerodynamic characteristics of bodies with elliptical and triangular cross sections and to compare the data with a body with circular cross sections. Force tests to determine lift, drag, and pitching-moment characteristics as well as pressure-distribution measurements were made for an angle of attack range.
Date: July 13, 1956
Creator: Lange, Roy H. & Wittliff, Charles E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Wind-Tunnel Investigation at Mach Numbers From 0.8 to 1.4 of Static Longitudinal and Lateral-Directional Characteristics of an Unswept-Wing Airplane Model

Description: "Results are presented for a wind-tunnel investigation of an airplane model with a 3.4-percent-thick unswept wing of aspect ratio 2.45 at Mach numbers from 0.8 to 1.4 at a Reynolds number of 1.5 million. Longitudinal characteristics are presented for the basic model and for configuration variations involving two types of wing camber, an area-rule fuselage modification, various external-store arrangements, several conventional missile installations and one designed according to the moment-of-are… more
Date: December 13, 1956
Creator: Summers, James L.; Treon, Stuart L. & Graham, Lawrence A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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