UNT Libraries Government Documents Department - 151 Matching Results

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Experimental Flutter Results for Cantilever-Wing Models at Mach Numbers Up to 3.0

Description: Report presenting experimental flutter testing at Mach numbers up to 3.0 using cantilever-wing models with 0 to 60 degree sweepback and 60 degree delta-wing models. The main variables explored were the high Mach number and center-of-gravity location on flutter trends. The theoretical results for flutter analyses were noted to be lower than the experimental results.
Date: June 14, 1955
Creator: Tuovila, W. J. & McCarty, John Locke
Item Type: Refine your search to only Report
open access

A preliminary investigation of the use of circulation control to increase the lift of a 45 degree sweptback wing by suction through trailing-edge slots

Description: Report presenting an investigation to determine the effectiveness of circulation control by applying suction through trailing-edge slots on a 45 degree sweptback wing. Various chordwise extents and depths of slot were investigated with and without deflection of a trailing-edge split flap. Results regarding the correlation of two-dimensional-section results with Ehlers' theory, effectiveness of circulation control on a sweptback wing, effect of slot configuration on circulation control, effect o… more
Date: December 14, 1954
Creator: Cook, Woodrow L.; Griffin, Roy N., Jr. & Hickey, David H.
Item Type: Refine your search to only Report
open access

Some effects of aileron span, aileron chord, and wing twist on rolling effectiveness as determined by rocket-powered model tests and theoretical estimates

Description: A determination of the variation of rolling effectiveness with spanwise aileron extent for full-chord ailerons on a sweptback wing over a range of Mach numbers. The test wings had NACA 65A006 airfoil sections, an aspect ratio of 4.0, 45 degrees sweepback at the quarter-chord line, and a taper ratio of 0.6. Results regarding ailerons and twisted wings are provided.
Date: September 14, 1954
Creator: Strass, H. Kurt & Tucker, Warren A.
Item Type: Refine your search to only Report
open access

Aspects of internal-flow-system design for helicopter propulsive units

Description: A discussion of pertinent items related to the design of internal-flow systems for reciprocating engine, turbine engine, and pressure-jet installations in helicopters. The following items are emphasized: controllable exit and ram recovery for reciprocating-engine cooling, performance penalties possible in turbine-engine installations, the effects of high subsonic flow velocities on the performance of duct elements, and the effects of centrifugal forces on the flow in a ducted helicopter rotor.
Date: September 14, 1954
Creator: Henry, John R.
Item Type: Refine your search to only Report
open access

Effect of boundary-layer control and inlet lip shape on the performance of a twin-scoop air-induction system at Mach numbers from 0 to 1.9

Description: Report presenting an experimental investigation to determine the effect of boundary-layer control and inlet lip shape on the performance of a side-inlet air-induction system for a fighter-type airplane. Two methods of boundary layer control and three inlet lip shapes were investigated at a range of Mach numbers and mass-flow ratios. Results regarding net propulsive thrust are also provided.
Date: February 14, 1956
Creator: Lazzeroni, Frank A. & Pfyl, Frank A.
Item Type: Refine your search to only Report
open access

A fuel-distribution control for gas-turbine engines

Description: "The principle of operation of a device to control the distribution of fuel to any number of discharge nozzles of a gas-turbine engine is presented. A description of an experimental model of the device and the results of a bench investigation are presented. This device controlled the flow to four discharge nozzles within 2 percent of perfect distribution over a wide range of fuel flow and was unaffected by uneven discharge-nozzle pressures" (p. 1).
Date: June 14, 1948
Creator: Gold, Harold & Straight, David M.
Item Type: Refine your search to only Report
open access

High-Speed Wind-Tunnel Investigation of a Sweptback Wing With an Added Triangular Area at the Center

Description: Report discussing an investigation of two sweptback wings of different plan form in order to determine the effects of adding a triangular area to the inboard section of a conventional sweptback wing as a way to create a wing with two stages of sweepback. Lift, drag, and pitching-moment characteristics are provided for a range of Mach numbers.
Date: January 14, 1949
Creator: Henry, Beverly Z., Jr.
Item Type: Refine your search to only Report
open access

The Effectiveness at High Speeds of a 10-Percent-Chord Plain Trailing-Edge Flap on the NACA 65-210 Airfoil Section

Description: This report contains the results of a high-speed wind-tunnel investigation of the effectiveness of a 10-percent-chord plain flap on the NACA 65-210 airfoil section. The results include an indication of the lift-producing characteristics and the effectiveness of the 10-percent-chord flap. From a comparison of the characteristics of the 10-percent-chord flap with those of a 20-percent-chord flap it was concluded that, although a reduction in flap-chord ratio from 0.20 to 0.10 lessens the severity… more
Date: June 14, 1948
Creator: Ilk, Richard J.
Item Type: Refine your search to only Report
open access

Preliminary Investigation to Determine Propeller Section Characteristics by Measuring the Pressure Distribution on an NACA 10-(3)(08)-03 Propeller Under Operating Conditions

Description: "An investigation has been made in the Langley 16-foot high-speed tunnel to determine the propeller-section characteristics by measuring the pressure distribution on the airfoil sections of a rotating propeller. The pressures were measured at nine radial stations on an NACA 10-(3)(08)-03 design two-blade propeller. This paper presents the results of the pressure measurements in the form of normal-force and moment coefficients and covers a range of nominal angle of attack (simple blade element t… more
Date: July 14, 1948
Creator: Evans, Albert J. & Liner, George
Item Type: Refine your search to only Report
open access

Experimental Investigation of the Effect of Forebody Bluntness on the Pressure Recovery and Drag of a Twin-Scoop Inlet-Body Combination at Mach Numbers of 1.4 and 1.7

Description: Memorandum presenting the pressure recovery, mass flow, and drag of a twin-scoop inlet-body combination measured at Mach numbers 1.4 and 1.7 at zero angle of attack. Tests were made of the inlet-body combination with an ogival forebody, an ogival forebody with a small amount of bluntness near the tip, and two forebodies of elliptical longitudinal section. Results regarding the effect of forebody bluntness on pressure recovery, effect of forebody bluntness on mass-flow ratio, and the effects of … more
Date: February 14, 1952
Creator: Stroud, John F.
Item Type: Refine your search to only Report
open access

The Use of Area Suction for the Purpose of Delaying Separation of Air Flow at the Leading Edge of a 63 Degree Swept-Back Wing: Effects of Controlling the Chordwise Distribution of Suction Air Velocities

Description: Report discusses the results of an updated investigation into the effectiveness of area suction when used to prevent air-flow separation at the leading edge of a 63 degree swept-back wing. This new report investigates the results of tests with chordwise distribution of the suction-air velocities controlled to give lower total-flow quantity requirements. The primary focus is the delay effected in air-flow separation and improvements made on aerodynamic characteristics of a wing with area suction… more
Date: January 14, 1952
Creator: Cook, Woodrow L. & Kelly, Mark W.
Item Type: Refine your search to only Report
open access

Spreading of Exhaust Jet From 16 Inch Ream Jet at Mach Number 2.0

Description: "An investigation of the jet-spreading characteristics of a 16 inch ram-jet engine was conducted in the 8 by 6 foot supersonic tunnel at a Mach number of 2.0; both a converging nozzle having a contraction ratio of 0.71 and a cylindrical extension to the combustion chamber were used. The jet boundaries determined by means of pitot pressure surveys were compared with boundaries calculated from one-dimensional continuity and momentum relations. For the cylindrical nozzle, the jet reaches its maxim… more
Date: August 14, 1952
Creator: Wilcox, Fred & Pennington, Donald
Item Type: Refine your search to only Report
open access

Some fundamental aspects of nitric acid oxidants for rocket applications

Description: From Summary: "The literature pertaining to the preparation, physical properties, corrosiveness, thermal stability, constitution, and analysis of various nitric acids is reviewed primarily with respect to their use as rocket oxidants. Conflicting data are evaluated and recommendations for additional experimental work are indicated. Reactions of nitric acid which could occur during the starting and steady-stage phases of rocket operation are discussed and probable mechanisms are selected on the … more
Date: January 14, 1953
Creator: Ladanyi, Dezso J.; Miller, Riley O.; Karo, Wolf & Feiler, Charles E.
Item Type: Refine your search to only Report
open access

Spark ignition of flowing gases III : effect of turbulence promoter on energy required to ignite a propane-air mixture

Description: Report presenting an investigation to determine the effect of turbulence generated by different sizes of wire grid on the minimum spark-ignition energy of a flowing propane-air mixture. Gas-stream velocity, size of turbulence promoter, and distance from the promoter plate to the electrodes on minimum ignition energy were evaluated and the effects are shown in figures.
Date: January 14, 1953
Creator: Swett, Clyde C., Jr. & Donlon, Richard H.
Item Type: Refine your search to only Report
open access

The effects of sweepback on longitudinal characteristics of a 1/30-scale semispan model of the Bell X-5 airplane as determined from NACA wing-flow tests at transonic speeds

Description: Report presenting tests using the NACA wing-flow method to determine the effect of sweepback angle on the longitudinal characteristics of a scale semispan model of the Bell X-5 variable-sweep airplane at a range of Mach numbers. Lift, drag, and pitching moments were obtained for a range of angles of attack.
Date: November 14, 1952
Creator: Kolnick, Joseph J. & Kennedy, Robert M.
Item Type: Refine your search to only Report
open access

Low-Speed Wind-Tunnel Investigation of the Effects of Propeller Operation at High Thrust on the Longitudinal Stability and Trim of a Twin-Engine Airplane Configuration

Description: Report presenting an investigation to determine the effects of dual-rotation propeller operation at high thrust on the static longitudinal stability characteristics of a semispan powered model representing a twin-engine airplane configuration with flaps retracted. Stability and trim changes associated with an extreme constant power conditions were greatly dependent on tail height and vertical location of the center of gravity. Results regarding basic data, effects of power on overall stability … more
Date: July 14, 1952
Creator: Sleeman, William C., Jr. & Linsley, Edward L.
Item Type: Refine your search to only Report
open access

Control Hinge-Moment and Effectiveness Characteristics of a 60 Degree Half-Delta Tip Control on a 60 Degree Delta Wing at Mach Numbers of 1.41 and 1.96

Description: Memorandum presenting an investigation of a half-delta wing-tip control on a semispan 60 degree delta-wing-fuselage combination conducted in the 9- by 12-inch supersonic blowdown tunnel. Control-surface hinge moments and bending moments, as well as the characteristics of the complete wing-fuselage combination, were obtained over a large range of control deflection and angle of attack at specified Mach and Reynolds numbers. Results regarding the control bending-moment and hinge-moment characteri… more
Date: October 14, 1952
Creator: Guy, Lawrence D.
Item Type: Refine your search to only Report
open access

Investigation at high subsonic speeds of bodies mounted from the wing of an unswept-wing-fuselage model, including measurements of body loads

Description: Report presenting an investigation with the dual purpose of determining the effect of two bodies in various positions, symmetrically located from the plane of symmetry, on the aerodynamic characteristics of a wing-fuselage model and determining the aerodynamic loads on one of two bodies. Some of the most significant effects were obtained for the direct-mounted tip bodies which gave a large increase in the lift-curve slope of the basic model.
Date: November 14, 1952
Creator: Silvers, H. Norman & King, Thomas J., Jr.
Item Type: Refine your search to only Report
open access

Oxidation-resistance mechanism and other properties of molybdenum disilicide

Description: The outstanding oxidation resistance of molybdenum disilicide at 2400 F and above was found to depend on the formation of a protective siliceous coating which a-cristobalie has been identified. Molybdenum disilicide is not inherently resistant to oxidation and in powdered form burns at low temperatures.Melting and casting experiments have demonstrated the decomposition of the material at the melting point. The room-temperature modulus of elasticity has been determined and electric-resistivity d… more
Date: March 14, 1952
Creator: Maxwell, W. A.
Item Type: Refine your search to only Report
open access

Relations between fuel properties and combustion carbon deposition

Description: Report discussing some methods for predicting the carbon-forming propensity of turbojet-engine fuels from results of simple laboratory tests of the fuels. The prediction of carbon deposition from fuel characteristics including aromatic content, hydrogen-carbon ratio, distillation temperatures, gravity, and aniline point from several empirical laboratory carbon-deposition tests are provided. Results regarding fuel composition and volatility, related fuel properties, empirical laboratory tests, a… more
Date: April 14, 1952
Creator: Jonash, Edmund R.; Wear, Jerrold D. & Hibbard, Robert R.
Item Type: Refine your search to only Report
open access

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

Description: Report presenting a low-speed investigation in the stability tunnel to determine the static longitudinal stability and control characteristics of a 60 degree triangular-wing model with various triangular-all-movable horizontal tails. An all-movable trail of 10 percent of the wing area and aspect ratio 2.31 was investigated in 17 tail positions, including positions above, below, and to the rear of the assumed center of gravity.
Date: December 14, 1951
Creator: Jaquet, Byron M.
Item Type: Refine your search to only Report
open access

Analysis of coolant-flow requirements for an improved, internal-strut-supported, air-cooled turbine-rotor blade

Description: From Introduction: "The purpose of this report is to present the results of the investigation, to compare the coolant-flow requirements of the two configurations, and to show what advantages an air-cooled internal-strut-supported blade may have over an equivalent shell-supported air-cooled blade."
Date: February 14, 1952
Creator: Schramm, Wilson B. & Nachtigall, Alfred J.
Item Type: Refine your search to only Report
open access

Investigations of air-cooled turbine rotors for turbojet engines 2: mechanical design, stress analysis, and burst test of modified J33 split-disk rotor

Description: A full-scale J33 air-cooled split turbine rotor was designed and spin-pit tested to destruction. Stress analysis and spin-pit results indicated that the rotor in a J33 turbojet engine, however, showed that the rear disk of the rotor operated at temperatures substantially higher than the forward disk. An extension of the stress analysis to include the temperature difference between the two disks indicated that engine modifications are required to permit operation of the two disks at more nearly … more
Date: January 14, 1952
Creator: Kemp, Richard H. & Moseson, Merland L.
Item Type: Refine your search to only Report
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