UNT Libraries Government Documents Department - 17 Matching Results

Search Results

Results: 1 - 17
open access

The Aerodynamic Characteristics in Pitch of a 1/15-Scale Model of the Grumman F11F-1 Airplane at Mach Numbers of 1.41, 1.61, and 2.01, TED No. NACA DE 390

Description: "Tests have been made in the Langley 4- by 4-foot supersonic pressure tunnel at Mach numbers of 1.41, 1.61, and 2.01 to determine the static longitudinal stability and control characteristics of various arrangements of the Grumman F11F-1 airplane. Tests were made of the complete model and various combinations of its component parts and, in addition, the effects of various body modifications, a revised vertical tail, and wing fences on the longitudinal characteristics were determined" (p. 1).
Date: May 23, 1956
Creator: Driver, Cornelius
open access

Axial-Flow Compressor Rotating-Stall and Rotor-Blade Vibration Survey

Description: Report presenting a compressor-rotor-blade vibration survey on a production turbojet engine incorporating a 13-stage axial-flow compressor with a pressure ratio of approximately 7 and an air flow of 120 pounds per second. The investigation was conducted due to the major problem that fatigue failures of compressor rotor blades have caused in the development of the axial-flow compressor. Results regarding rotating stall characteristics, rotor-blade vibration, and fourth-stage rotor-blade failure … more
Date: May 23, 1955
Creator: Calvert, Howard F.; Medeiros, Arthur A. & Garrett, Floyd B.
open access

Comparison of Zero-Lift Drags Determined by Flight Tests at Transonic Speeds of Symmetrically Mounted Nacelles in Various Spanwise Positions on a 45 Degrees Sweptback Wing and Body Combination

Description: Report presenting testing of rocket-powered models flown at transonic speeds to determine the effect of nacelle location on zero-lift drag. Low drag was obtained between M = 0.80 and M = 0.91 for all the nacelle positions investigated. Nacelles located at the wing tips gave the lowest drag, which was less than the drag of the combination without the nacelles over most of the speed range.
Date: May 23, 1951
Creator: Pepper, William B., Jr. & Hoffman, Sherwood
open access

Correlation of creep-buckling tests with theory

Description: Report presenting the results of short-time creep-buckling and creep-bending tests of 2024-T4 aluminum-alloy columns of slenderness ratio 111 are presented. Tests were performed at 600 degrees Fahrenheit and strain measurements were taken with high-temperature electric-resistance strain gages.
Date: May 23, 1956
Creator: Patel, Sharad A.; Kempner, Joseph; Erickson, Burton & Mobassery, Abol H.
open access

Drag interference between a pointed cylindrical body and triangular wings of various aspect ratios at Mach numbers of 1.50 and 2.02

Description: The drag of a body alone, six triangular wings of various aspect ratios, and the combinations were measured at Mach numbers of 1.50 and 2.02 at a Reynolds number of 5.5 million (based on the body length). The experimental drag-interference results were in accordance with calculations based on NACA RM A9E19, 1949, with skin-friction effects taken into account, the interference effect being principally the result of fixing transition on the body by adding a wing.
Date: May 23, 1951
Creator: Katzen, Elliott D. & Kaattari, George E.
open access

Effect of leading-edge droop on the aerodynamic and loading characteristics of a 4-percent-thick unswept-wing-fuselage combination at transonic speeds

Description: Report presenting an investigation in the 16-foot transonic tunnel to determine the effects of leading-edge droop on the aerodynamic and loading characteristics of an unswept wing with a taper ratio of 0.5, an aspect ratio of 4, and NACA 65A004 airfoil sections parallel to the plane of symmetry. The results indicate that, below a Mach number of 0.94, leading-edge droop delayed the onset of leading-edge separation and moved the main wing-compression shock rearward.
Date: May 23, 1956
Creator: Schmeer, James W.
open access

Effects of horizontal-tail position and aspect ratio on low-speed static longitudinal stability and control characteristics of a 60 degree triangular-wing model having twin triangular all-movable tails

Description: Report presenting a low-speed investigation in the stability tunnel to determine the effects of tail height, length, and aspect ratio on the static longitudinal stability and control characteristics of a 60 degree triangular-wing model with twin triangular all-movable tails located near the wing tips.
Date: May 23, 1952
Creator: Jaquet, Byron M.
open access

Investigation of a high-pressure-ratio eight-stage axial-flow research compressor with two transonic inlet stages 5: preliminary analysis of over-all performance of modified compressor

Description: Report presenting an investigation of the overall performance of a modified eight-stage axial-flow compressor as part of the investigation of the problems encountered in a high-pressure-ratio axial-flow compressor with transonic inlet stages. The maximum total pressure ratio obtained at design speed was 11.0 at an equivalent weight flow of 70.9 pounds per second with an adiabatic efficiency of 0.81. Results regarding modified compressor performance and comparison with predicted performance are … more
Date: May 23, 1955
Creator: Standahar, Raymond M. & Geye, Richard P.
open access

An Investigation of a Supersonic Aircraft Configuration Having a Tapered Wing With Circular-Arc Sections and 40 Degree Sweepback: A Pressure-Distribution Study of the Aerodynamic Characteristics of the Wing at Mach Number 1.59

Description: Memorandum presenting a pressure-distribution investigation of a wing of a complete supersonic aircraft configuration as conducted in the 4- by 4-foot supersonic tunnel at Mach number 1.59 based on the mean aerodynamic chord. The experimental life and drag coefficients were less than those predicted by linear theory. Results regarding section pressure characteristics, section characteristics, spanwise characteristics, and overall wing characteristics are provided.
Date: May 23, 1950
Creator: Cooper, Morton & Spearman, M. Leroy
open access

Jet effects on base and afterbody pressures of a cylindrical afterbody at transonic speeds

Description: An investigation of the effects of jet nozzle geometry, size of base annulus, and base bleed upon the base and afterbody pressures of a cylindrical afterbody at transonic speeds has been conducted. Sonic and supersonic conical nozzles with jet-to-base diameter ratios from 0.25 to 0.85 were investigated with a cold jet at jet total-pressure ratios up to approximately 8.0 through a Mach number range from 0.6 to 1.25. Base pressure coefficients of about -0.55 were measured for the sonic nozzles at… more
Date: May 23, 1956
Creator: Cubbage, James M., Jr.
open access

Preliminary Results of the Determination of Inlet-Pressure Distortion Effects on Compressor Stall and Altitude Operating Limits of the J57-P-1 Turbojet Engine

Description: "During an investigation of the J57-P-1 turbojet engine in the Lewis altitude wind tunnel, effects of inlet-flow distortion on engine stall characteristics and operating limits were determined. In addition to a uniform inlet-flow profile, the inlet-pressure distortions imposed included two radial, two circumferential, and one combined radial-circumferential profile. Data were obtained over a range of compressor speeds at an altitude of 50,000 and a flight Mach number of 0.8; in addition, the hi… more
Date: May 23, 1955
Creator: Wallner, L. E.; Lubick, R. J. & Chelko, L. J.
open access

Review of some recent data on buffet boundaries

Description: Report presenting a study of a large amount of data pertaining to high-speed buffet boundaries of various airplane configurations. The data indicate a strong influence of wing configuration on buffet boundaries. Results regarding low-lift buffeting, high-lift buffeting, buffet boundaries, and buffet intensity are provided.
Date: May 23, 1951
Creator: Purser, Paul E. & Wyss, John A.
open access

Rolling Effectiveness of a Thin Tapered Wing Having Partial-Span Ailerons as Determined by Rocket-Powered Test Vehicles

Description: "The rolling effectiveness of a thin, tapered, and essentially unswept wing having outboard partial-span plain ailerons has been determined by means of rocket-powered test vehicles. The rolling power decreased abruptly in the Mach number range from 0.85 to 0.95 and more gradually at higher speeds. At the maximum Mach number of the tests (1.95), the rolling effectiveness was only 20 percent of that at a Mach number of 0.85" (p. 1).
Date: May 23, 1950
Creator: Sandahl, Carl A. & Strass, H. Kurt
open access

A Study by Means of a Dynamic-Model Investigation of the Use of Canard Surfaces as an Aid in Recovering From Spins and as a Means for Preventing Directional Divergence Near the Stall

Description: Memorandum presenting an aircraft modification involving the incorporation of small canard surfaces into the design, which is meant to compensate for eliminating ailerons. Results of testing in the 20-foot free-spinning tunnel of dynamic models of two sweptback-wing fighter airplanes showed that canard surfaces were very effective in aiding termination of spins of these models. A discussion of the spin tests, catapult and force tests, and effect of jet-engine angular momentum is provided.
Date: May 23, 1956
Creator: Klinar, Walter J.
open access

Time-History Data of Maneuvers Performed by an F-86A Airplane During Squadron Operational Training

Description: "Preliminary results of one phase of a control-motion study program are presented in the form of plots of load factor.and angular acceleration against indicated airspeed and of time histories of several measured quantities. The results were obtained from 197 maneuvers performed by an F-86A jet-fighter airplane during normal squadron operational training. Most of the tactical maneuvers of which the F-86A is capable were performed at pressure altitudes ranging from 0 to 32,000 feet and at indicat… more
Date: May 23, 1952
Creator: Henderson, Campbell; Thornton, James & Mayo, Alton
open access

Turboprop-engine design considerations 1: effect of mode of engine operation on performance of turboprop engine with current compressor pressure ratio

Description: Report presenting a cycle analysis of a turboprop engine for various modes of operation over a range of flight conditions in order to determine whether one mode of operation has any marked advantages. The methods of operation explored included constant compressor equivalent design speed, constant design engine rotative speed, adjustable turbine stators, and variable exhaust-nozzle area.
Date: May 23, 1955
Creator: Davison, Elmer H.
open access

Turboprop-engine design considerations 2: design requirements and performance of turboprop engines with a single-spool high-pressure-ratio compressor

Description: Report of an investigation of the effect of mode of engine operation, engine configuration, and airplane flight condition on the performance and design requirements of a turboprop engine with a high-pressure-ratio single-spool compressor. Both single-spool engines and gas-generating engines are considered. The free-turbine engine was found to be less versatile than the single-spool engine because the range of turbine-inlet temperature over which it can operate is restricted.
Date: May 23, 1955
Creator: Davison, Elmer H. & Stalla, Margaret C.
Back to Top of Screen