UNT Libraries Government Documents Department - 215 Matching Results

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Investigations toward simplification of missile control systems

Description: Paper presenting three ideas regarding potential simplifications of missile-control systems in order to make them more reliable without sacrificing system performance. The three methods presented include an autorotating-vane spoiler, a bellows flap, and free controls. All are based on modified airplane control systems.
Date: November 12, 1953
Creator: Curfman, Howard J., Jr.; Strass, H. Kurt & Crane, Harold L.
Item Type: Refine your search to only Report
open access

The Effects of a Small Jet of Air Exhausting From the Nose of a Body of Revolution in Supersonic Flow

Description: Report presenting the results of an investigation to determine the effects of a small jet of air exhausting from the nose of an elliptical body of revolution upon boundary-layer transition and the viscous, pressure, and total drag of the forebody at three body stations at Mach number 1.62. The jet effects on body pressure, pressure variations, boundary-layer transition, and total drag are provided.
Date: November 12, 1952
Creator: Love, Eugene S.
Item Type: Refine your search to only Report
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Ice Prevention on Aircraft by Means of Engine Exhaust Heat and a Technical Study of Heat Transmission From a Clark Y Airfoil

Description: "This investigation was conducted to study the practicability of employing heat as a means of preventing the formation of ice on airplane wings. The report relates essentially to technical problems regarding the extraction of heat from the exhaust gases and its proper distribution over the exposed surfaces. In this connection a separate study has been made to determine the variation of the coefficient of heat transmission along the chord of a Clark Y airfoil. Experiments on ice prevention both … more
Date: June 12, 1931
Creator: Theodorsen, Theodore & Clay, William C.
Item Type: Refine your search to only Report
open access

Lateral Stability and Control Measurements of a Fighter-Type Airplane With a Low-Aspect-Ratio Unswept Wing and a Tee-Tail

Description: Report presenting an investigation of the lateral stability and control effectiveness of a model of a fighter-type airplane model with a low-aspect-ratio and 3.4-percent-thick wing with negative dihedral at a range of Mach numbers, sideslip angles, and angles of attack. Results regarding the lateral characteristics at zero angle of attack, lifting conditions, and lateral and directional controls are provided.
Date: June 12, 1956
Creator: Arabian, Donald D. & Schmeer, James W.
Item Type: Refine your search to only Report
open access

Aerodynamic loadings associated with swept and unswept spoilers on a flat-plate at Mach numbers of 1.61 and 2.01

Description: Report presenting an investigation at two Mach numbers to examine the flow, force, and moment characteristics associated with spoilers mounted on a flat plate at a range of sweep angles. Pressure measurements were obtained over the plate and spoiler faces. The pressures were integrated to determine the spoiler lift, pitching-moment, drag, and hinge-moment characteristics.
Date: March 12, 1956
Creator: Lord, Douglas R. & Czarnecki, K. R.
Item Type: Refine your search to only Report
open access

Aerodynamic characteristics at subsonic and transonic speeds of a 42.7 degree sweptback wing model having an aileron with finite trailing-edge thickness

Description: Report presenting an investigation at subsonic and transonic speeds in the high-speed 7- by 10-foot tunnel to determine the aerodynamic characteristics of a 42.7 degree sweptback wing with a 20-percent-chord and 50-percent-span outboard aileron. The investigation was performed in transonic flow over a bump on the tunnel floor and in subsonic flow on one of the tunnel side walls.
Date: January 12, 1949
Creator: Turner, Thomas R.; Lockwood, Vernard E. & Vogler, Raymond D.
Item Type: Refine your search to only Report
open access

Wind-tunnel investigation of transonic aileron flutter of a semispan wing model with an NACA 23013 section

Description: Report presenting the results of a wind-tunnel investigation of aileron flutter up to 0.822 Mach number. The testing indicated the absence of flutter of significant amplitude when a considerable amount of wing-tip relief existed and the presence of flutter when the relief was minimized. Results regarding the testing without the end plate, with end plate, and comparison with theory are provided.
Date: July 12, 1948
Creator: Perone, Angelo & Erickson, Albert L.
Item Type: Refine your search to only Report
open access

Design and Performance of Experimental Axial-Discharge Mixed-Flow Compressor 1: Impeller Design Theory

Description: Memorandum presenting a description of an axial-discharge mixed-flow compressor, which is especially adapted for jet engines because of the large mass flow per unit frontal area. The best impeller was selected on the basis of the maximum air-flow capacity, which was 19.6 pounds per second for a 14-inch-diameter impeller with a tip speed of 1480 feet per second and a pressure ratio of 3.5.
Date: August 12, 1948
Creator: Goldstein, Arthur W.
Item Type: Refine your search to only Report
open access

Design and performance of experimental axial-discharge mixed-flow compressor 2: performance of impeller

Description: Report presenting an analysis of an axial-discharge mixed-flow compressor designed to combine the compactness, reliability, and wide operating range of a mixed-flow compressor with the high flow capacity per unit of frontal area that characterizes the axial-flow compressor. The primary objective of this design was to maximize the flow capacity for a predetermined pressure ratio. Results regarding the flow distribution at the impeller inlet, flow distribution at the impeller outlet, and impeller… more
Date: August 12, 1948
Creator: Wilcox, Ward W.
Item Type: Refine your search to only Report
open access

Experimental determination of the lateral stability of a glider towed by a single towline and correlation with an approximate theory

Description: Report presenting an investigation to determine the effects of various design parameters on the lateral-stability characteristics of a glider towed by a single towline. The investigation showed that it is possible to obtain inherent lateral stability with a single towline system.
Date: November 12, 1948
Creator: Maggin, Bernard & Shanks, Robert E.
Item Type: Refine your search to only Report
open access

Tests of a centering spring used as an artificial feel device on the elevator of a fighter airplane

Description: Report presenting tests to investigate the use of a simple centering spring, which had no variation of force gradient with impact pressure, as an artificial feel device for the elevator control of a fighter airplane. Testing was conducted using a Chance Vought F4U-4B airplane equipped with power controls. Results regarding the force experienced and effects of the feel system are provided.
Date: September 12, 1952
Creator: Adams, James J. & Whitten, James B.
Item Type: Refine your search to only Report
open access

Investigation of a 24-inch shock-in-rotor type supersonic compressor designed for simple radial equilibrium behind normal shock

Description: A 24-inch-diameter shock-in-rotor supersonic compressor rotor designed to obtain simple radial equilibrium behind the normal shock obtained a maximum total-pressure ratio of 2.02 at an adiabatic efficiency of 0.74 and a weight flow of 61.5 pounds per second at design speed. Although this design method considerably reduced the radial forces, there was no apparent reduction in the radial forces, there was no apparent reduction in the radial redistribution of mass flow over the radial redistributi… more
Date: December 12, 1951
Creator: Lown, Harold & Hartmann, Melvin J.
Item Type: Refine your search to only Report
open access

Lateral and directional dynamic-response characteristics of a 35 degree swept-wing airplane as determined from flight measurements

Description: Report presenting lateral and directional dynamic response characteristics of a 35 degree swept-wing fighter-type airplane determined from flight measurements and compared with predictions based on theoretical studies and wind-tunnel testing. Results regarding the frequency responses, theoretical and experimental transfer functions, stability derivatives, aeroelastic effects, response at low frequency, and effects of minor derivatives, product of inertia, and flight-path angle are provided.
Date: December 12, 1952
Creator: Triplett, William C. & Brown, Stuart C.
Item Type: Refine your search to only Report
open access

Longitudinal-control effectiveness and downwash characteristics at transonic speeds of a 1/30-scale semispan model of the Bell X-5 airplane as determined by the NACA wing-flow method

Description: Report presenting an investigation at transonic speeds using the wing-flow method to determine the longitudinal-control effectiveness and downwash characteristics of a 1/30-scale semispan model of the Bell X-5 airplane with three different degrees of sweepback. Lift, drag, and pitching moment are presented for various angles of attack for several horizontal-tail settings and with the tail off for each angle of sweep tested.
Date: January 12, 1953
Creator: Silsby, Norman S. & Morris, Garland J.
Item Type: Refine your search to only Report
open access

The longitudinal characteristics at Mach numbers up to 0.9 of a wing-fuselage-tail combination having a wing with 40 degrees of sweepback and an aspect ratio of 10

Description: Report presenting an investigation to evaluate the effects of an all-movable horizontal tail on the longitudinal characteristics of a sweptback wing and a fuselage of a type suitable for long-range high-speed airplanes. Tests were conducted at low speed and at high Mach numbers over a range of Reynolds numbers. Large reductions in longitudinal stability of the wing-fuselage-tail combination were found at lift coefficients well below the stall.
Date: December 12, 1952
Creator: Tinling, Bruce E.
Item Type: Refine your search to only Report
open access

Longitudinal Stability, Trim, and Drag Characteristics of a Rocket-Propelled Model of an Airplane Configuration Having a 45 Degree Sweptback Wing and an Unswept Horizontal Tail

Description: Report discussing an investigation of the longitudinal stability, trim, and drag of a rocket-propelled model at low lift coefficients at a range of Mach numbers. the configuration included a wing and horizontal tail of aspect ratio 4 and thickness ratio in the streamwise direction of 6 percent.
Date: August 12, 1952
Creator: Parks, James H. & Kehlet, Alan B.
Item Type: Refine your search to only Report
open access

Preliminary investigation of effect of angle of attack on pressure recovery and stability characteristics for a vertical-wedge-nose inlet at Mach number of 1.90

Description: Report presenting a preliminary investigation of a wedge-type compression surface mounted vertically in a circular cowling conducted in the supersonic wind tunnel at a Mach number of 1.90 and range of angles of attack. With symmetrical cowling, the pressure recovery and stability characteristics comparable to a conical inlet were obtained, but twin-duct flow interaction was observed. Results regarding the pressure recovery and stability characteristics and effects of removing the lower cowl lip… more
Date: August 12, 1952
Creator: Leissler, L. Abbott & Hearth, Donald P.
Item Type: Refine your search to only Report
open access

Influence of a canard-type control surface on the internal and external performance characteristics of nacelle-mounted supersonic diffusers (conical centerbody) at a rearward body station for a Mach number of 2.0

Description: Report presenting an investigation of the effects of the wake resulting from control-surface deflection on the internal performance of two supersonic diffusers and on the engine-body interference drag in the 8- by 6-foot supersonic wind tunnel at Mach number 2.0. Results regarding the internal-flow evaluation, high-pressure-recovery diffuser, and drag evaluation are provided.
Date: August 12, 1952
Creator: Obery, L. J. & Krasnow, H. S.
Item Type: Refine your search to only Report
open access

Calibration of AWS instrument shelter in Langley 300 MPH 7- by 10-foot tunnel

Description: From Summary: "Tests and calibrations of an AWS instrument shelter were made in the Langley 300 MPH 7- by 10-foot tunnel for the Signal Corps, U.S. Army. The behavior of the wind vane, the 3-cup anemometer, and the shelter cover was determined in wind speeds up to 150 miles per hour. It was discovered that the rotational speed of the anenometer was greatly influenced by the location, with respect to the wind direction, of three spacer posts that held two upper bays of instruments above the anen… more
Date: May 12, 1952
Creator: McKee, John W.
Item Type: Refine your search to only Report
open access

A Method for the Design of Sweptback Wings Warped to Produce Specified Flight Characteristics at Supersonic Speeds

Description: Memorandum presenting a method for designing a wing to be self-trimming at a given set of flight conditions. The spanwise distribution of load on the wing is made to be approximately elliptical, in an effort to maintain low wing drag. The procedure is illustrated using several examples.
Date: September 12, 1951
Creator: Tucker, Warren A.
Item Type: Refine your search to only Report
open access

Recent Experimental Flutter Studies

Description: Report presenting some highlights of recent experimental studies of flutter at high speeds. Flutter problems have become more varied with the advent of transonic flight and importance of aeroelasticity, and the flutter field has merged with other aspect of aeroelasticity such as divergence and buffeting. The two main subjects of flutter, classical flutter and stall flutter, are explored in these studies.
Date: June 12, 1951
Creator: Regier, Arthur A. & Martin, Dennis J.
Item Type: Refine your search to only Report
open access

Experimental Investigation of an 0.8 Hub-Tip Radius-Ratio, Nontwisted-Rotor-Blade Turbine

Description: "An experimental investigation of a 0.8 hub-tip radius ratio, nontwisted-rotor-blade turbine designed for a stagnation-pressure ratio of 2.5 and an equivalent mean blade speed of 643 feet per second was made in a cold-air turbine with (a) nontwisted stator blades, and (b) twisted stator blades designed to maintain zero rotor-inlet incidence angles. Turbine efficiencies of the order of 0.85 at the design point were obtained with a nontwisted-rotor-blade turbine with a hub-tip radius ratio of 0.8… more
Date: December 12, 1951
Creator: Silvern, David H. & Slivka, William R.
Item Type: Refine your search to only Report
open access

Flow Separation Ahead of a Blunt Axially Symmetric Body at Mach Numbers 1.76 to 2.10

Description: "The pressure distribution and drag were determined for a spherical-nosed axially symmetric body with thin projecting rods at Mach numbers of 1.76, 1.93, and 2.10. The upstream projection distance of the rods was varied over a wide range to study changes in the character of the flow separation and to determine the variation of drag and pressure distribution with tip projection. Drag coefficients between 0.18 and 0.30 were obtained for most tip projections at each Mach number" (p. 1).
Date: December 12, 1951
Creator: Moeckel, W. E.
Item Type: Refine your search to only Report
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