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in creator/contributor: "Henderson, James H"  
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Effect at Transonic Speeds of Inboard Spoilers on the Static Longitudinal Stability Characteristics of a 45 Degree Sweptback Wing-Body Combination Having a Leading-Edge Chord-Extension

Description: Memorandum presenting an exploratory investigation in the 9- by 12-inch blowdown tunnel to determine the effect of inboard spoilers located along the 20- and 30-percent-chord lines on the static longitudinal stability characteristics of a semispan 45 degree sweptback wing-body combination with a leading-edge chord-extension. The model pitching-moment characteristics were improved by spoilers extending from 15 percent semispan to 45 percent semispan. Results regarding pitching moment, lift, drag… more
Date: June 14, 1954
Creator: Henderson, James H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

A correlation with flight tests of results obtained from the measurement of wing pressure distributions on a 1/4-scale model of the X-1 airplane (10-percent-thick wing)

Description: Report presenting an investigation in the transonic tunnel of the aerodynamic characteristics of a scale model of an X-1 airplane in order to correlate wing pressure-distribution results obtained in a slotted wind tunnel with flight test data on the full-scale airplane. Results regarding basic pressure measurements, and correlation of pressure measurements are provided.
Date: September 3, 1952
Creator: Runckel, Jack F. & Henderson, James H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

An Investigation of the Effects of a Vortex-Generator Configuration on the Aerodynamic Characteristics of a 1/4-Scale Model of the X-1 Airplane (10-Percent-Thick Wing)

Description: From Summary: "An investigation of a vortex-generator configuration on the wings of a l/4-scale model of the X-1 airplane having a 10-percent-thick wing was conducted in the Langley 16-foot transonic tunnel. The effect of the vortex generators was determined by comparing the model aerodynamic characteristics, wing-pressure distributions, and wing-wake patterns for model configurations with and without vortex generators on the wings. Results are presented from tests at 0.1 increments in Mach num… more
Date: December 23, 1952
Creator: Runckel, Jack F. & Henderson, James H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Transonic Aerodynamic and Loads Characteristics of a 4-Percent-Thick Unswept-Wing--Fuselage Combination

Description: Report presenting an investigation in the transonic tunnel to determine the basic aerodynamic and loading characteristics of an unswept-wing-fuselage combination with a wing of aspect ratio 4, taper ratio 0.5, and NACA 65A004 airfoil sections. Force, moment, and pressure measurements were obtained for a range of Mach numbers and angles of attack.
Date: May 24, 1954
Creator: Hieser, Gerald; Henderson, James H. & Swihart, John M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

The Langley annular transonic tunnel

Description: Report describes the development of the Langley annular transonic tunnel, a facility in which test Mach numbers from 0.6 to slightly over 1.0 are achieved by rotating the test model in an annular passage between two concentric cylinders. Data obtained for two-dimensional airfoil models in the Langley annular transonic tunnel at subsonic and sonic speeds are shown to be in reasonable agreement with experimental data from other sources and with theory when comparisons are made for nonlifting cond… more
Date: January 19, 1953
Creator: Habel, Louis W.; Henderson, James H. & Miller, Mason F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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