Technical Report Archive & Image Library (TRAIL) - 5,157 Matching Results

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Longitudinal and Lateral Stability and Control Characteristics and Vertical-Tail-Load Measurements for a 0.03-Scale Model of the Avro CF-105 Airplane at Mach Numbers of 1.60, 1.80, and 2.00

Description: "An investigation has been made in the Langley Unitary Plan wind tunnel at Mach numbers of 1.60, 1.80, and 2.00 to determine the aerodynamic characteristics of a 0.03-scale model of the Avro CF-105 airplane. The investigation included the determination of the static longitudinal and lateral stability, the control and the hinge-moment characteristics of the elevator, rudder, and aileron, as well as the vertical-tail-load characteristics. Although the data are presented without analysis, a limite… more
Date: July 15, 1958
Creator: Silvers, H. Norman; Fournier, Roger H. & Wills, Jane S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effects of Boattail Area Contouring and Simulated Turbojet Exhaust on the Loading and Fuselage-Tail Component Drag of a Twin-Engine Fighter-Type Airplane Model

Description: Effects of boattail area contouring and simulated turbojet exhaust on loading and fuselage-tail component drag of twin-engine fighter-type airplane model.
Date: July 14, 1958
Creator: Foss, Willard E., Jr.; Runckel, Jack F. & Lee, Edwin E., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effects of Boattail Area Contouring and Simulated Turbojet Exhaust on the Loading and Fuselage-Tail Component Drag of a Twin-Engine Fighter-Type Airplane Model

Description: "An investigation of a twin-engine fighter-type airplane model has been conducted in the Langley 16-foot transonic tunnel to determine the effect on drag of a fuselage volume addition incorporating streamline contouring and more extensive boattailing of the engine shrouds. The effect of hot exhausts from the turbojet engines was simulated with hydrogen peroxide gas generators using scaled nonafterburning engine nozzles. Afterbody pressure distributions, base drag coefficients, and forces on the… more
Date: July 14, 1958
Creator: Foss, Willard E., Jr.; Runckel, Jack F. & Lee, Edwin E., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Hydrodynamic Characteristics of a Model of a Proposed Six-Engine Hull-Type Seaplane Designed for Supersonic Flight

Description: Memorandum presenting an investigation of the hydrodynamic characteristics of a six-engine hull-type seaplane designed for supersonic flight. The configuration had four engines mounted on top of the wing in individual nacelles and two engines mounted on top of the aft section of the hull with their inlets located on top of the wing.
Date: July 14, 1958
Creator: Coffee, Claude W., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Hydrodynamic Characteristics of a Model of a Proposed Six-Engine Hull-Type Seaplane Designed for Supersonic Flight

Description: Report presenting an investigation of the hydrodynamic characteristics of a six-engine hull-type seaplane designed for supersonic flight. Four engines were mounted on top of the wing in individual nacelles and two engines were mounted on the top of the aft section of the hull. Results regarding the acceleration, gross-load-total-resistance ratio, stabilizer deflections, and reaction of the inlets to water are presented.
Date: July 14, 1958
Creator: Coffee, Claude W., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Investigation of Control Effectiveness and Stability Characteristics of a Model of a Low-Wing Missile With Interdigitated Tail Surfaces at Mach Numbers of 2.29, 2.97, and 3.51

Description: "A brief investigation of the longitudinal stability and control effectiveness at supersonic speeds of a model of a low-wing missile with interdigitated tail surfaces was made in the Langley Unitary Plan wind tunnel. The data were obtained at Mach numbers M of 2.29, 2.97, and 3.51 for Reynolds number (based on the mean geometric chord of the wing) of 1.15 x 10(exp 6), 1.14 x 10(exp 6), and 1.11 x 10(exp 6), respectively. Data were obtained for three settings of the longitudinal control surface… more
Date: July 14, 1958
Creator: Presnell, John G., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effects of vertical location of the wing and horizontal tail on the static lateral and directional stability of a trapezoidal-wing airplane model at Mach numbers of 1.41 and 2.01

Description: Report presenting an investigation to determine the effects of vertical location of the wing and horizontal tail on the static lateral and directional stability at various combined angles of attack and sideslip for a supersonic airplane configuration at Mach numbers of 1.41 and 2.01. The configurations investigated included a high-wing, midwing, and low-wing arrangement in combination with horizontal-tail positions varying from a location of 0.208 wing semispan below to 0.556 semispan above the… more
Date: July 9, 1958
Creator: Robinson, Ross B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Transonic Characteristics of Outboard Ailerons on a 4-Percent-Thick 30 Degree Sweptback Wing, Including Some Effects of Aileron Trailing-Edge Thickness and Aerodynamic Balance

Description: Report presenting an investigation to determine the roll effectiveness, hinge-moment characteristics, and aileron center-of-load locations on an outboard 40-percent-semispan flap-type aileron on a 30 degree sweptback wing with an aspect ratio of 3.0, a taper ratio of 0.2, and NACA 65A004 airfoil sections. Results regarding general aileron characteristics and other aerodynamic characteristics are also presented.
Date: July 9, 1958
Creator: Whitcomb, Charles F. & Critzos, Chris C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effects of canards on airplane performance and stability

Description: Report presenting an investigation on canard airplane configurations in preference to a trailing-edge flap or tail control. Wide ranges in control plan form, size, and position and in wing plan form were found. Interference effects between the canard and other configuration components were not serious, and those that might be can be reduced by rearrangement of the vertical tail.
Date: July 7, 1958
Creator: Hall, Charles F. & Boyd, John W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Longitudinal stability and control characteristics at Mach numbers of 1.41 and 2.01 of a 67 degree swept-wing airplane configuration with canard control surfaces

Description: Report presenting an investigation in the 4- by 4-foot supersonic pressure tunnel at Mach numbers of 1.41 and 2.01 to determine the stability and control characteristics of a canard-controlled airplane configuration with potentially high values of lift-drag ratio. The configurations investigated included a plane and a twisted wing with approximately 67 degrees of sweep and an aspect ratio of 2.91 and three trapezoidal canard surfaces with ratios of exposed area to wing area of 0.032, 0.076, and… more
Date: July 7, 1958
Creator: Spearman, M. Leroy & Robinson, Ross B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Performance of Multiple Jet-Exit Installations

Description: Memorandum presenting the results of recent exploratory investigations of the performance of clustered jet-exit installations at Mach numbers from 0.60 to 3.05. Data presented in this report were obtained with tunnel-wall-mounted models with cold-air-jet exhaust. Results regarding base pressures, effect of boattailing, effect of afterbody-nozzle geometry, and terminal fairings are provided.
Date: July 7, 1958
Creator: Swihart, John M. & Nelson, William J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Performance of multiple jet-exit installations

Description: Report presenting an investigation of the performance of clustered jet-exit installations at Mach numbers from 0.60 to 3.05. The data were obtained with tunnel-wall-mounted models with cold-air-jet exhaust. Results indicated that large base-pressure drag coefficients may be encountered in the transonic and low supersonic speed range and that the best configuration in the test was boattailed between the nacelles, had a cylindrical nacelle afterbody, and a divergent nozzle with a design pressure … more
Date: July 7, 1958
Creator: Swihart, John M. & Nelson, William J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Qualitative Measurements of the Effective Heats of Ablation of Several Materials in Supersonic Air Jets at Stagnation Temperatures Up to 11,000 Degrees F

Description: Report presenting testing on the effective heats of ablation of a number of materials using supersonic arc jets at stagnation temperatures ranging from 2000 degrees F to 11,000 degrees F. Materials examined included Teflon, nylon, Lucite, polystyrene, ammonium chloride, sodium carbonate, several phenolic resins, and melamine-fiber glass laminate.
Date: July 7, 1958
Creator: Rashis, Bernard; Witte, William G. & Hopko, Russell N.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Static Stability and Control of Hypersonic Gliders

Description: Memorandum presenting a study of the static stability and control problems associated with several hypersonic boost gliders. Generally, it is possible to obtain the desired trim features. Results regarding the high-lift-drag-ratio type of gliders and low-lift-drag-ratio type of gliders are provided.
Date: July 7, 1958
Creator: Rainey, Robert W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

A Flight-Test Study of Total-Pressure Distortion in a Thick-Lipped Nose Inlet

Description: Memorandum presenting flight tests conducted on a thick-lipped nose inlet of a transonic swept-wing aircraft. The total-pressure recovery and distortion at the compressor face were measured over the maneuvering range of the airplane for Mach numbers up to 1.03. Results regarding the radial total-pressure profile, average total-pressure recovery, and total-pressure distortion are provided.
Date: June 30, 1958
Creator: Wingrove, Rodney C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Investigation of the Static Stability Characteristics of Five Hypersonic Missile Configurations at Mach Numbers From 2.29 to 4.65

Description: Report presenting an investigation to determine the static stability characteristics of five hypersonic missile configurations. Testing was performed at a range of Mach and Reynolds numbers. Results regarding the effect of base block, longitudinal stability, directional stability, and Reynolds number effect are provided.
Date: June 30, 1958
Creator: Turner, Kenneth L. & Appich, W. H., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Investigation of the Static Stability Characteristics of Five Hypersonic Missile Configurations at Mach Numbers From 2.29 to 4.65

Description: Report presenting an investigation in the Unitary Plan wind tunnel to determine the static stability characteristics of five hypersonic missile configurations. Tests were performed at a range of Mach and Reynolds numbers based on body length. Results regarding the effect of a base block, longitudinal and directional stability, and Reynolds number effect are provided.
Date: June 30, 1958
Creator: Turner, Kenneth L. & Appich, W. H., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Transonic investigation of yawed wings of aspect ratios 3 and 6 with a Sears-Haack body and with symmetrical and asymmetrical bodies indented for a Mach number of 1.20

Description: Report presenting an investigation to determine the experimental and predicted wave-drag characteristics of wing-body combinations. Two yawed wings, each with an average sweep of about 40 degrees, were tested with various bodies, and the results were compared with existing data for similar models with sweptback wings. Results regarding the aerodynamic characteristics and pressure results are provided.
Date: June 30, 1958
Creator: Holdaway, George H. & Hatfield, Elaine W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Viscous Flows in Inlets

Description: Report discusses ways to reduce "viscous effects", which increase total pressure losses due to friction at increasing free-stream Mach numbers. Some of the effects are related to the inlet of an aircraft and potential issues in design. From Introduction: "Care must be exercised in inlet design to maintain uniform steady boundary-layer and core flows in the throat."
Date: June 30, 1958
Creator: Scherrer, Richard; Lundell, John H. & Anderson, Lewis A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Hydrodynamic Characteristics of Missiles Launched Under Water

Description: Report presenting some of the hydrodynamic problems associated with launching an air missile from underwater. The results of an experiment with models are also provided, including deviation angle, effect of forward speed of the submarine, curved path of the missile, and potential environmental disruptions.
Date: June 27, 1958
Creator: Dawson, John R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Maneuver Performance of Interceptor Missiles

Description: "From these preliminary wind-tunnel tests of interceptor missile configurations and the analysis of point defense against ballistic missiles, it is concluded that adequate aerodynamic lift is readily available and should be utilized when operating under high-dynamic-pressure conditions and that more work should be done on controls, either aerodynamic or reaction type, so that the configurations may be trimmed to the angles of attack required to develop the necessary turning force" (p. 5).
Date: June 27, 1958
Creator: Stone, David G.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

The Prospects for Laminar Flow on Hypersonic Airplanes

Description: The factors which affect the extent of laminar flow on airplanes for hypersonic flight are discussed on the basis of the available data. Factors considered include flight Reynolds number, surface roughness, angle of attack, angle of leading-edge sweepback, and aerodynamic interference. Test data are presented for one complete configuration.
Date: June 27, 1958
Creator: Seiff, Alvin
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Exploratory Investigation of Performance of Experimental Fuel-Rich Hydrogen Combustion System

Description: Memorandum presenting an exploratory investigation conducted to determine the performance characteristics of a fuel-rich hydrogen combustor; in addition, the performance of an afterburner operating with the fuel-rich exhaust mixture was evaluated. Results regarding performance of the fuel-rich combustor, afterburner performance, and resonating combustion are provided.
Date: June 25, 1958
Creator: Smith, Arthur L. & Grobman, Jack S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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