Technical Report Archive & Image Library (TRAIL) - 32,509 Matching Results

Search Results

open access

An investigation at high subsonic speeds of the effects of horizontal-tail height on the aerodynamic and loading characteristics in sideslip on a 45 degree sweptback, untapered tail assembly as determined from force tests and integrated vertical-tail span loadings

Description: Report presenting an investigation in the high-speed tunnel of the effects at high subsonic speeds of horizontal-tail height on the aerodynamic and loading characteristics in sideslip of a 45 degree sweptback, untapered tail assembly. Configurations investigated include the fuselage alone, the fuselage plus vertical tail, and with a horizontal tail mounted at 0, 50, and 100 percent vertical-tail span. Results regarding the lateral force coefficient, rolling-moment coefficient, and a comparison … more
Date: June 28, 1955
Creator: Wiley, Harleth G. & Moseley, William C., Jr.
Partner: UNT Libraries Government Documents Department
open access

Investigation at High Subsonic Speeds of the Effects of Various Horizontal Fuselage Forebody Fins on the Directional and Longitudinal Stability of a Complete Model Having a 45 Degree Sweptback Wing

Description: Memorandum presenting an investigation conducted in the high-speed 7- by 10-foot tunnel of the effects of various horizontal fuselage forebody fins on the directional and longitudinal stability characteristics at high subsonic speeds of a complete model with a 45 degree sweptback wing mounted in a high position on the fuselage. The model wing had an aspect ratio of 4, a taper ratio of 0.30, and NACA 65A006 airfoil sections parallel to the free stream.
Date: January 16, 1957
Creator: Sleeman, William C., Jr.
Partner: UNT Libraries Government Documents Department
open access

Investigation at high subsonic speeds of the effects of various underwing external-store arrangements on the aerodynamic characteristics of a 1/16-scale model of the Douglas D-558-II Research Airplane

Description: Report presenting an investigation at high subsonic speeds of various arrangements of underwing external stores on a model of the Douglas D-558-II research airplane. Three sizes of a short-cylinder shape and two sizes of a long-cylinder shape were investigated with three thicknesses of pylon support on one store configuration. Results regarding drag characteristics and lift and pitch characteristics are provided.
Date: July 18, 1955
Creator: Silvers, H. Norman & King, Thomas J., Jr.
Partner: UNT Libraries Government Documents Department
open access

Investigation at high subsonic speeds of the pressure distributions on a 45 degree sweptback horizontal tail mounted at 50-percent and 100-percent vertical-tail span

Description: Report presenting an investigation in the high-speed tunnel at high subsonic speeds and several angles of attack of the chordwise pressure distributions in sideslip at six span stations on a 45 degree sweptback, untapered, vertical tail with a 45 degree sweptback horizontal tail mounted at 50-percent and 100-percent vertical-tail span.
Date: November 24, 1954
Creator: Wiley, Harleth G. & Moseley, William C., Jr.
Partner: UNT Libraries Government Documents Department
open access

An investigation at high subsonic speeds of the pressure distributions on a 45 degree sweptback vertical tail in sideslip with and without a 45 degree sweptback horizontal tail located on the fuselage center line

Description: Report presenting an investigation in the high-speed tunnel at high subsonic speeds and several angles of attack of the chordwise pressure distribution at six spanwise stations on a 45 degree sweptback, untapered vertical tail in sideslip. The presence of the horizontal tail slightly increased the value of section normal-force coefficients on the vertical tail but did not materially alter the nature of the load distribution.
Date: November 2, 1954
Creator: Wiley, Harleth G. & Moseley, William C., Jr.
Partner: UNT Libraries Government Documents Department
open access

Investigation at high subsonic speeds of the static lateral and directional stability and tail-loads characteristics of a model having a highly tapered swept wing of aspect ratio 3 and two horizontal-tail positions

Description: Report presenting an investigation made in the 7- by 10-foot tunnel of the static lateral and directional stability and some tail-load characteristics of a model with a highly tapered swept wing and two horizontal-tail positions. Testing were made with the horizontal tail located at the tip of the swept vertical tail and with the horizontal tail located in the wing-chord plane extended. Results regarding static lateral and directional stability and vertical-tail loads are provided.
Date: September 11, 1956
Creator: Few, Albert G., Jr.
Partner: UNT Libraries Government Documents Department
open access

Investigation at High Subsonic Speeds of the Static Longitudinal and Lateral Stability Characteristics of Two Canard Airplane Configurations

Description: "The present investigation was conducted in the Langley high-speed 7-by 10-foot tunnel to determine the static longitudinal and lateral stability characteristics at high subsonic speeds of two canard airplane configurations previously tested at supersonic speeds. The Mach number range of this investigation extended from 0.60 to 0.94 and a maximum angle-of-attack range of -2deg to 24deg was obtained at the lowest test Mach number. Two wing plan forms of equal area were studied in the present tes… more
Date: December 3, 1957
Creator: Sleeman, William C., Jr.
Partner: UNT Libraries Government Documents Department
open access

Investigation at High Subsonic Speeds of the Use of Low Auxiliary Tail Surfaces Having Dihedral to Improve the Longitudinal and Directional Stability of a T-Tail Model at High Lift

Description: Memorandum presenting an investigation of the use of low auxiliary horizontal-tail surfaces to alleviate the pitch-up tendency at high lift of an airplane configuration with a T-tail. The basic model had a wing with an aspect ratio of 3, a taper ratio of 0.143, and an unswept 80-percent chord line.
Date: December 5, 1957
Creator: Sleeman, William C., Jr.
Partner: UNT Libraries Government Documents Department
open access

Investigation at large scale of the pressure distribution and flow phenomena over a wing with the leading edge swept back 47.5 degrees having circular-arc airfoil sections and equipped with drooped-nose and plain flaps

Description: Report presenting an investigation of the pressure distribution over a wing with the leading-edge swept back 47.5 degrees and with symmetrical circular-arc airfoil sections in the full-scale tunnel at a designated Mach and Reynolds number. The investigation included measurements of the surface static pressures along the chord for six spanwise stations, for a large angle-of-attack range, and for several angles of yaw.
Date: September 8, 1949
Creator: Lange, Roy H.; Whittle, Edward F., Jr. & Fink, Marvin P.
Partner: UNT Libraries Government Documents Department
open access

Investigation at Low Speed of 45 Degrees and 60 Degrees Sweptback, Tapered, Low-Drag Wings Equipped With Various Types of Full-Span, Trailing-Edge Flaps

Description: Note presenting an investigation to determine the low-speed aerodynamic characteristics of two sweptback, low-drag, tapered wings equipped with full-span split and slotted flaps and three special types of trailing-edge flaps. Two sweep angles of 45 and 60 degrees, measured at the quarter chord, were used. The effect of the flaps on drag and pitching moment is the same as that indicated by other test data available.
Date: October 1951
Creator: Harper, John J.
Partner: UNT Libraries Government Documents Department
open access

An investigation at low speed of a 51.3 degree sweptback semispan wing equipped with 16.7-percent-chord plain flaps and ailerons having various spans and three trailing-edge angles

Description: Report presenting a wind-tunnel investigation performed at low speed to determine the aerodynamic characteristics of a 51.3 degree sweptback semispan wing equipped with 16.7-percent-chord plain flaps and ailerons with various spans and spanwise locations and one with span of aileron with trailing-edge angles of 6, 14, and 25 degrees. Results regarding the wing aerodynamic characteristics, aileron-control characteristics, spoiler control characteristics, and effect of wing-tip shape are provided. more
Date: November 12, 1948
Creator: Fischel, Jack & Schneiter, Leslie E.
Partner: UNT Libraries Government Documents Department
open access

An investigation at low speed of a 51.3 degrees sweptback semispan wing with a raked tip and with 16.7-percent-chord ailerons having three spans and three trailing-edge angles

Description: Report presenting a wind-tunnel investigation at low speed to determine the aerodynamic characteristics of a 51.3 degree sweptback semispan wing with a raked tip and with 16.7-percent-chord sealed plain ailerons. Lift, drag, pitching-moment, and hinge-moment data were obtained for the wing with transition free and fixed with various spans of aileron deflected as lift flaps. The rolling moment, yawing moment, hinge moment, and aileron seal pressure characteristics were determined for each of the… more
Date: July 21, 1948
Creator: Fischel, Jack & Schneiter, Leslie E.
Partner: UNT Libraries Government Documents Department
open access

An Investigation at Low Speed of a Large-Scale Triangular Wing of Aspect Ratio Two 1: Characteristics of a Wing Having a Double-Wedge Airfoil Section With Maximum Thickness at 20-Percent Chord

Description: Report presenting an investigation of the low-speed characteristics of a 25-foot span triangular wing with an aspect ratio of 2. the airfoil section of the wing was a symmetrical double wedge with 5-percent maximum thickness at 20-percent chord. Results regarding the longitudinal characteristics, lateral characteristics, and directional characteristics are provided.
Date: November 13, 1947
Creator: Anderson, Adrien E.
Partner: UNT Libraries Government Documents Department
open access

An Investigation at Low Speed of a Large-Scale Triangular Wing of Aspect Ratio Two 2: The Effect of Airfoil Section Modifications and the Determination of the Wake Downwash

Description: Report presenting a study of the characteristics of a large-scale triangular wing to include the effects of section modifications. The wing in this report is the same as the one in the previous report but features various degrees of rounding of the wing leading edge and wing maximum thickness rather than having sharp edges. Results regarding the effects of airfoil section modifications, visible trailing vortices, and surveys in the extended chord plane are provided.
Date: December 10, 1947
Creator: Anderson, Adrien E.
Partner: UNT Libraries Government Documents Department
open access

An Investigation at Low Speed of a Large-Scale Triangular Wing of Aspect Ratio Two 3: Characteristics of Wing With Body and Vertical Tail

Description: Report presenting an investigation to determine the aerodynamic characteristics in sideslip of a triangular wing of aspect ratio 2.04 in combination with a body of fineness ratio 12.5 and a vertical tail surface. The body combined with the triangular plan-form wing caused no significant changes in the lift characteristics of the wing and only a 1-percent decrease in the static margin. Results regarding the longitudinal characteristics, lateral and directional characteristics, and estimation of … more
Date: October 14, 1949
Creator: Anderson, Adrien E.
Partner: UNT Libraries Government Documents Department
open access

Investigation at low speed of the downwash, sidewash, and wake characteristics behind a large-scale triangular wing, including the effects of yaw, full-span trailing-edge flaps, and two leading-edge modifications

Description: Report presenting an investigation at low speed in the Langley full-scale tunnel of the downwash, sidewash, and wake behind a large-scale 60 degree triangular wing with 10-percent-thick biconvex airfoil sections. Results regarding the air-stream surveys for three different configurations and stability and trim are provided.
Date: October 27, 1952
Creator: Whittle, Edward F., Jr. & Hawes, John G.
Partner: UNT Libraries Government Documents Department
open access

Investigation at low speed of the effectiveness and hinge moments of a constant-chord elevator on a large-scale triangular wing with section modification

Description: Report presenting an investigation in the full-scale tunnel to determine the low-speed longitudinal, lateral, and hinge-moment control characteristics of a basic 60 degree delta wing of aspect ratio 2.31 with 10-percent-thick biconvex symmetrical airfoil sections. The wing was tested with a nose glove using NACA 65-010 section ordinates and a constant-chord plain semispan ailavator with two segments.
Date: April 24, 1951
Creator: Hawes, John G. & May, Ralph W., Jr.
Partner: UNT Libraries Government Documents Department
open access

Investigation at Low Speed of the Flow Field Behind the Lifting Surfaces of a Model Equipped With a 60 Degree Triangular Wing and a 60 Degree Triangular Canard Tail

Description: Report presenting an investigation of the flow behind the lifting surfaces of a model equipped with a 60 degree triangular wing and a 60 degree triangular canard tail. Results regarding the force and moment data, air-stream surveys behind the wing, effective values of downwash and dynamic-pressure ratio, effect of tail height and length, a comparison with previous data, the effects of component area and ratio, and the effect of a canard tail are provided.
Date: June 29, 1953
Creator: Newman, Ernest E. & Cahill, Jones F.
Partner: UNT Libraries Government Documents Department
open access

An investigation at low speed of the flow over a simulated flat plate at small angles of attack using pitot-static and hot-wire probes

Description: Report presenting results from pitot-static and hot-wire anemometer surveys at low speed of the flow over a thin, sharp-edge airfoil which simulated a flat plate. The primary purpose was to obtain detailed measurements of the flow associated with the so-called thin-airfoil type of stall. Results regarding the preliminary tests, pressure distributions, mean flow measurements, velocity fluctuation measurements, and observations and measurements of the flow in the immediate vicinity of the leading… more
Date: March 1957
Creator: Gault, Donald E.
Partner: UNT Libraries Government Documents Department
open access

Investigation at low speed of the longitudinal stability characteristics of a 60 degree swept-back tapered low-drag wing

Description: Report presenting an investigation made in the 300 mph 7- by 10-foot tunnel to determine at low speed in the longitudinal stability characteristics of a 60 degree sweptback, tapered, low-drag wing of aspect ratio 2.55. The results show undesirably large changes in the longitudinal stability characteristics of the 60 degree sweptback wings.
Date: May 1947
Creator: Lowry, John G. & Schneiter, Leslie E.
Partner: UNT Libraries Government Documents Department
open access

An Investigation at Low Speed of the Spin Instability of Mortar-Shell Tails

Description: An investigation was made in the Langley stability tunnel to study the influence of number of fins, fin shrouding, and fin aspect ratio on the spin instability of mortar-shell tail surfaces. It was found that the 12-fin tails tested spun less rapidly throughout the angle-of-yaw range than did the 6-fin tails and that fin shrouding reduced the spin encountered by a large amount.
Date: June 19, 1957
Creator: Bird, John D. & Lichtenstein, Jacob H.
Partner: UNT Libraries Government Documents Department
open access

Investigation at low speeds of deflectors and spoilers as gust alleviators on a model of the Bell X-5 airplane with 35 degree swept wings and on a high-aspect-ratio 35 degree swept-wing-fuselage model

Description: Results of an investigation at low speeds to determine the gust-alleviation capabilities (reduction in lift-curve slope) of spoilers and deflectors on a 35 degree swept-wing model of high aspect ratio and on a 1/4-scale model of the X-5 airplane with 35 degree swept wings indicate that deflector and spoiler-deflector types of controls can be designed to provide considerable gust alleviation for a swept-wing airplane while still maintaining stability and control.
Date: June 1957
Creator: Croom, Delwin R. & Huffman, Jarrett K.
Partner: UNT Libraries Government Documents Department
open access

Investigation at low speeds of the effect of aspect ratio and sweep on rolling stability derivatives of untapered wings

Description: Report presenting a wind-tunnel investigation conducted in rolling flow to determine the effects of aspect ratio and sweep on the rolling stability derivatives for a series of untapered wings. The results indicated that when the aspect ratio is held constant, an increase in sweepback angle causes a significant reduction in the damping in roll at low lift coefficients for only the higher aspect ratios tested.
Date: March 1949
Creator: Goodman, Alex & Fisher, Lewis R.
Partner: UNT Libraries Government Documents Department
open access

Investigation at low speeds of the effect of aspect ratio and sweep on rolling stability derivatives of untapered wings

Description: A low-scale wind-tunnel investigation was conducted in rolling flow to determine the effects of aspect ratio and sweep (when varied independently) on the rolling stability derivatives for a series of untapered wings. The rolling-flow equipment of the Langley stability tunnel was used for the tests. The data of the investigation have been used to develop a method of accounting for the effects of the drag on the yawing moment due to rolling throughout the lift range.
Date: January 19, 1949
Creator: Goodman, Alex & Fisher, Lewis R.
Partner: UNT Libraries Government Documents Department
Back to Top of Screen