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Performance of an Inlet Having a Variable-angle Two-dimensional Compression Surface and a Fixed-geometry Subsonic Diffuser for Application to Reduced Engine Rotative Speeds- Mach Numbers 0.66, 1.5, 1.7, and 2.0

Description: Report presenting the performance of a two-dimensional side inlet with a technique of varying compression-surface angle while retaining a fixed-geometry diffuser at several Mach numbers and zero angle of attack. A 12 degree compression ramp was faired into the diffuser contour in this conventional manner. Results regarding the inlet flow field, application to reduced engine speeds, and a inlet performance with a sudden expansion in the diffuser are provided.
Date: January 30, 1958
Creator: Allen, John L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Investigation of Inlet Control Parameters for an External-Internal-Compression Inlet From Mach 2.1 to 3.0

Description: "Investigation of the control parameters of an external-internal compression inlet indicates that the cowl-lip shock provides a signal to position the spike and to start the inlet over a Mach number range from 2.1 to 3.0. Use of a single fixed probe position to control the spike over the range of conditions resulted in a 3.7-count loss in total-pressure recovery at Mach 3.0 and 0 deg angle of attack. Three separate shock-sensing-probe positions were required to set the spike for peak recovery f… more
Date: September 23, 1958
Creator: Anderson, Bernhard H. & Bowditch, David N.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Ground Simulator Studies of a Small Side-Located Controller in a Power Control System

Description: Memorandum presenting an investigation to determine the operating characteristics of a small side-located control stick with the use of a ground simulator incorporating a power control system. The simulator or pitch chair was designed to produce the pitching motion associated with the short-period mode of an airplane. The general opinion of all of the pilots operating the pitch chair was that they were favorably impressed with their ability to precisely track with the small side-located control… more
Date: April 23, 1958
Creator: Assadourian, Arthur
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Transonic Lateral and Longitudinal Aerodynamic Characteristics of a Lateral-Control System Employing Rotatable Airfoils Mounted Vertically at the Wing Tips of an Unswept Wing-Fuselage-Tail Combination

Description: Report presenting the aerodynamic characteristics of a new type of lateral control through a range of Mach numbers. The control consisted of airfoils mounted vertically at the tips of the wing and could be rotated to induce rolling moments or lift on the wing surface. Results regarding lateral-control characteristics and lift-control characteristics are provided.
Date: January 7, 1958
Creator: Axelson, John A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Transonic Investigation of an Axial-Flow Compressor Rotor With a Contracted Exit Annulus

Description: Report presenting an investigation of an axial-flow compressor rotor with a 13-percent reduction in exit annulus in Freon-12 gas at a range of tip speeds. In order to analyze the results caused by the reduction, the performance of the rotor was compared to that of the same rotor with a constant annular area. Results regarding the overall performance, radial variation of performance, and blade-element performance are also provided.
Date: February 17, 1958
Creator: Babington, Robert S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Chemical and physical factors affecting combustion in fuel-nitric acid systems

Description: Report presenting characteristic exhaust-velocity measurements made of the JP-4 fuel-red fuming nitric acid propellant combination in 40-pound-thrust rocket engines with various combustion-chamber lengths and diameters. The results are compared to those from previous studies and discussed in terms of a vaporization model of combustion. Results regarding the effect of UDMH, effect of water on performance of hydrocarbon fuels, effect of water on performance of hydrazine fuel, and some of the chem… more
Date: July 28, 1958
Creator: Baker, Louis, Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Screaming tendency of the gaseous-hydrogen - liquid-oxygen propellant combination

Description: Report presenting an exploratory study of the screaming tendency of the gaseous-hydrogen-liquid-oxygen propellant combination in 200-pound-thrust rocket engines. Four injector classes in a total of 12 different configurations were tested in a variety of chamber lengths over the usable mixture-ratio range. Results regarding acoustic oscillations, unclassified oscillations, driving and damping mechanisms, and effects of screaming on heat transfer are provided.
Date: September 30, 1958
Creator: Baker, Louis, Jr. & Steffen, Fred W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Boundary-Layer-Transition Measurements in Full-Scale Flight

Description: Report presenting tests of the extent of laminar flow that can be obtained with practical wing-surface conditions. Chemical sublimation was used for boundary-layer-flow visualization on the wings of a supersonic fighter airplane in level flight. A method of continuous monitoring using heat temperature resistance gauges was also used on one wing.
Date: July 28, 1958
Creator: Banner, Richard D.; McTigue, John G. & Petty, Gilbert, Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Boundary-Layer-Transition Measurements in Full-Scale Flight

Description: Chemical sublimation has been employed for boundary-layer-flow visualization on the wings of a supersonic fighter airplane in level flight at speeds near a Mach number of 2.0. The tests have shown that laminar flow can be obtained over extensive areas of the wing with practical wing-surface conditions. In addition to the flow visualization tests, a method of continuously monitoring the conditions of the boundary layer has been applied to flight testing, using heated temperature resistance gages… more
Date: July 28, 1958
Creator: Banner, Richard D.; McTigue, John G. & Petty, Gilbert, Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Wind-Tunnel Data on the Longitudinal and Lateral-Directional Rotary Derivatives of a Straight-Wing, Research Airplane Configuration at Mach Numbers From 2.5 to 3.5

Description: Memorandum presenting the results of wind-tunnel oscillation tests to measure the rotary derivatives of a research airplane configuration at supersonic speeds. Measurements were made of the damping in yaw, pitch, and roll, the static longitudinal and directional stability derivatives, the effective-dihedral derivative, the rolling moment due to yawing, and the yawing moment due to rolling. The configuration was found to be statistically stable throughout the Mach number range, although its stab… more
Date: March 25, 1958
Creator: Beam, Benjamin H. & Endicott, Kenneth C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Off-Design Performance of Divergent Ejectors

Description: Report presenting an investigation of the off-design performance of fixed- and variable-geometry divergent ejectors. Results regarding fixed geometry and low secondary flow, fixed geometry and high secondary flow, variable geometry and low secondary flow, variable geometry and high secondary flow, and ejectors with full afterburning are provided.
Date: September 30, 1958
Creator: Beheim, Milton A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Off-Design Performance of Divergent Ejectors

Description: "The off-design performance of fixed- and of variable-geometry divergent ejectors was investigated. The ejectors, which were designed for turbojet operation at Mach 3, were investigated in the Mach number range of 0.8 to 2. The performance of a fixed-geometry ejector with high secondary-flow rates was competitive with that of more complex variable-geometry ejectors. Variable-geometry ejectors with compromises to reduce mechanical complexity produced performance reasonably close to that of an id… more
Date: September 30, 1958
Creator: Beheim, Milton A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Investigation of Control Signals for Variable Ramps of Twin-Duct Side Inlets

Description: Report presenting an investigation to determine the effectiveness of experimental control signals applied to a theoretical inlet throat Mach number control system and normal-shock-position control system for varying the inlet geometry of a twin-duct prototype aircraft. Results regarding inlet instability, control requirements, individual throat Mach number control signals, average throat Mach number control signals, theoretical thraot Mach number control analysis, effect of angle of attack, and… more
Date: January 16, 1958
Creator: Beheim, Milton A. & Yeager, Richard A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Investigation of Control Signals for Variable Ramps of Twin-Duct Side Inlets

Description: Report presenting an investigation in the supersonic wind tunnel to determine the effectiveness of experimental control signals applied to a theoretical inlet throat Mach number control system and normal-shock-position control system for varying the inlet geometry of a twin-duct, side-inlet, fuselage forebody model of a prototype aircraft. These types of control systems have been found to be particularly helpful in supersonic flight. Results regarding inlet stability, control requirements, indi… more
Date: January 16, 1958
Creator: Beheim, Milton A. & Yeager, Richard A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Stability of Ballistic Reentry Bodies

Description: Report discussing various features of the stability of ballistic reentry shapes, including considerations for ballistic-missile and manned-satellite reentry capsules. Attainment of satisfactory stability of reentry bodies with subsonic terminal velocities was not found to be too difficult, but undesirable features that may cause marginal stability characteristics may be introduced in an effort to minimize weight. Reentry bodies with supersonic terminal velocities have fewer stability issues.
Date: August 11, 1958
Creator: Bird, John D. & Reese, David E., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effectiveness of various protective coverings on magnesium fins at Mach number 2.0 and stagnation temperatures up to 3,600 degrees R

Description: Report presenting eight thin magnesium fins, seven with the leading edges swept back 17 degrees and one with the leading edge swept back 45 degrees, in the preflight high-temperature jet. The investigation was made to determine the effectiveness of various protective coverings designed to alleviate aerodynamic-heating effects and intended for application on the first stage of rocket-propelled multistage hypersonic models.
Date: January 9, 1958
Creator: Bland, William M., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Some Effects of Fin Leading-Edge Shape on Aerodynamic Heating at Mach Number 2.0 at a Stagnation Temperature of About 2,600 Degrees R

Description: Report presenting testing of three uninstrumented tapered magnesium fins with the leading edges swept back 17 degrees in an ethylene-heated high-temperature jet. The testing was carried out to investigate some effects of leading-edge diameter and leading-edge shape on the aerodynamic heating by noting the time for melting to begin on the fins. Results indicated that increasing the diameter of cylindrical leading edge increased the time required for melting to start.
Date: January 9, 1958
Creator: Bland, William M., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Free-flight pressure measurements over a flare-stabilized rocket model with a modified Von Karman nose for Mach numbers up to 4.3

Description: Report presenting pressures measured during a free-flight test at zero angle of attack over a rocket model with a modified Von Karman nose in combination with a cylindrical center section and a 10 degree half-angle flare.
Date: January 13, 1958
Creator: Bland, William M., Jr. & Kolenkiewicz, Ronald
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Free-Flight Aerodynamic-Heating Data at Mach Numbers Up to 10.9 on a Flat-Faced Cylinder

Description: Memorandum presenting a five-stage rocket-propelled model flown up to a Mach number of 10.9 and a corresponding free-stream Reynolds number of 6.57 x 10(exp 6) based on nose diameter. Temperatures were measured at 16 stations on the inside of a flat-faced cylinder made of copper. Results regarding the flight test, wall temperatures, heat-transfer data, measurement repeatibility and effects of angle of attack, comparison of measured and theoretical stagnation-point heating rates, and measured an… more
Date: January 13, 1958
Creator: Bland, William M., Jr.; Swanson, Andrew G. & Kolenkiewicz, Ronald
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Experimental results of an investigation of two methods of inflight thrust measurement applicable to afterburning turbojet engines with ejectors

Description: Report presenting an investigation in an altitude test chamber using a turbojet engine equipped with an afterburner and ejector to compare directly two techniques of determining thrust that are both applicable to flight installations. One method uses a swinging uncooled rake at the ejector outlet while the other requires extensive instrumentation to measure the momentum forces of systems and the force on the internal surface of the ejector nozzle. Results regarding the swinging-rake technique a… more
Date: May 2, 1958
Creator: Bloomer, Harry E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Experimental ablation cooling

Description: Report presenting the results of an experimental investigation on the ablation of a number of promising materials for heating conditions comparable to those which maybe encountered by unmanned reentry satellite vehicles or heating conditions associated with reentry ballistic missiles. Results regarding exploratory tests, further Teflon tests, and graphite testing are provided.
Date: July 15, 1958
Creator: Bond, Aleck C.; Rashis, Bernard & Levin, L. Ross
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Performance of an Isentropic, All-Internal-Contraction, Axisymmetric Inlet Designed for Mach 2.50

Description: Memorandum presenting an experimental investigation of an internal-contraction, axially symmetric inlet with isentropic compression surfaces on both the cowl and centerbody conducted over a range of Mach numbers from 2.0 to 2.7 at angles of attack from 0 to 6 degrees. The study was made to determine the optimum bleed system, together with a method of controlling the inlet.
Date: September 15, 1958
Creator: Bowditch, David N. & Anderson, Bernhard H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

An Investigation of the Free-Spinning and Recovery Characteristics of a 1/24-Scale Model of the Grumman F11F-1 Airplane With Alternate Nose Configurations With and Without Wing Fuel Tanks, TED No. NACA AD 395

Description: "A supplementary investigation has been conducted in the Langley 20-foot free-spinning tunnel on a l/24-scale model of the Grumman F11F-1 airplane to determine the spin and recovery characteristics with alternate nose configurations, the production version and the elongated APS-67 version, with and without empty and full wing tanks. When spins were obtained with either alternate nose configuration, they were oscillatory and recovery characteristics were considered unsatisfactory on the basis of… more
Date: March 5, 1958
Creator: Bowman, James S., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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