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Low-Amplitude Damping-in-Pitch Characteristics of Four Tailless Swept Wing-Body Combinations at Mach Numbers From 0.85 to 1.30 as Obtained With Rocket-Powered Models

Description: Report presenting an investigation to determine the damping-in-pitch characteristics of four rocket-powered wing-body combinations for a range of Mach numbers from 0.85 to 1.30. The models were tested at the same center-of-gravity location and had identical bodies. Information about the trim, lift, static longitudinal stability, dynamic longitudinal stability, and drag is provided.
Date: November 24, 1954
Creator: D'Aiutolo, Charles T.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Investigation of Supersonic-Compressor Rotors Designed with External Compression

Description: Report presenting an investigation of the possibility of utilizing the relatively good characteristics of the spike-type diffuser in the supersonic compressor. Results regarding the overall performance, inlet conditions, outlet conditions, entrance flow conditions, and estimated performance of subsonic portion of rotor passage are provided.
Date: September 24, 1954
Creator: Jahnsen, Lawrence J. & Hartmann, Melvin J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Low-Amplitude Damping-in-Pitch Characteristics of Tailless Delta-Wing-Body Combinations at Mach Numbers From 0.80 to 1.35 as Obtained With Rocket-Powered Models

Description: Report of an investigation using three rocket-propelled delta-wing-body combinations for a range of Mach numbers to determine the damping-in-pitch characteristics. All models were statically stable but dynamically unstable at transonic speeds. Information about trim, lift, and drag is also provided.
Date: June 24, 1954
Creator: D'Aiutolo, Charles T.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

The effect of ground on the low-speed aerodynamics control, and control hinge-moment characteristics of a delta-wing-fuselage model with trailing-edge controls

Description: Report presenting an investigation to determine the effect of ground on the low-speed aerodynamic, control, and control hinge-moment characteristics of a 3-percent-thick, delta-wing-fuselage configuration. Aerodynamic forces and moments and hinge-moment data were obtained for a range of angles of attack, ground heights, and a designated Mach and Reynolds number.
Date: September 24, 1954
Creator: Scallion, William I.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Investigation of a Canard Missile Configuration (NACA RM-4) in the Langley 9-Inch Supersonic Tunnel at Mach Numbers of 1.62 and 1.93

Description: Report presenting an investigation in the supersonic tunnel using a canard missile configuration designated as NACA RM-4. Measurements of lift, drag, and pitching moment were made over a range of Mach numbers and angles of attack. The data is presented without analysis.
Date: June 24, 1954
Creator: Grigsby, Carl E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Transonic Aerodynamic and Loads Characteristics of a 4-Percent-Thick Unswept-Wing--Fuselage Combination

Description: Report presenting an investigation in the transonic tunnel to determine the basic aerodynamic and loading characteristics of an unswept-wing-fuselage combination with a wing of aspect ratio 4, taper ratio 0.5, and NACA 65A004 airfoil sections. Force, moment, and pressure measurements were obtained for a range of Mach numbers and angles of attack.
Date: May 24, 1954
Creator: Hieser, Gerald; Henderson, James H. & Swihart, John M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Hinge-Moment, Lift, and Pitching-Moment Characteristics of a Flap-Type Control Surface Having Various Hinge-Line Locations on a 4-Percent-Thick 60 Degree Delta Wing: Transonic Bump Method

Description: Report presenting an investigation in the high-speed tunnel to determine the hinge-moment, lift, and pitching-moment characteristics of a 4-percent-thick 60 degree delta wing with a trailing-edge flap-type control. The purpose of this investigation is to determine the ideal aerodynamic balance of a large part of the control force in order to make aircraft easier to control in the event of power failure.
Date: March 24, 1954
Creator: Thompson, Robert F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Flight Tests of a Man Standing on a Platform Supported by a Teetering Rotor

Description: Report presenting a series of flight tests to determine the flying qualities of a man standing on a platform supported by a teetering rotor. The machine was tested with a free-teetering rotor, a spring-restrained rotor, and a rotor and foot platform isolated from the framework by rubber connections. Results of the different configurations during indoor and outdoor flights are presented.
Date: March 24, 1954
Creator: Hill, Paul R. & Kennedy, T. L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Longitudinal Stability and Drag Characteristics of a Fin Stabilized Body of Revolution With a Fineness Ratio of 12 as Measured by the Free-Fall Method

Description: Report presenting measurements of longitudinal stability and drag characteristics of a fin-stabilized body of revolution with a fineness ratio 12 at low angles of attack using the free-fall method. Information about the data obtained from testing as well as the experimental coefficients related to body normal-force, total longitudinal-force, and body moment with Mach number is provided.
Date: June 24, 1954
Creator: Kurbjun, Max C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Flight Determination of the Buffeting Characteristics of the Bell X-5 Research Airplane at 58.7 Degrees Sweepback

Description: Report presenting flight measurements of the buffeting characteristics of the Bell X-5 airplane at 58.7 degrees of sweepback at a range of Mach numbers and altitudes. Information about tail buffeting and wing buffeting at several angles of attack is provided. The pilot considered the buffeting to be unobjectionable throughout the entire test region.
Date: May 24, 1954
Creator: Briggs, Donald W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

A low-speed investigation of the aerodynamic, control, and hinge-moment characteristics of two types of controls and balancing tabs on a large-scale thin delta-wing-fuselage model

Description: Report presenting a low-speed investigation of the aerodynamic and control characteristics of a 3-percent-thick, 60 degree delta-wing-fuselage configuration in the full-scale tunnel to obtain data at large scale on control configurations of general interest and to determine whether significant Reynolds number effects existed for a very thin wing subject to leading-edge vortex-type flow. Aerodynamic forces, moments, and hinge moments were obtained for several types of controls and flap deflectio… more
Date: March 24, 1954
Creator: Fink, Marvin P. & Cocke, Bennie W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Investigation of effect of increased diffusion of rotor-blade suction-surface velocity on performance of transonic turbine

Description: Report presenting the results of an experimental investigation of a transonic turbine designed for a diffusion parameter of 0.30. The experimental performance of the turbine is compared with the experimental performance obtained for another transonic turbine designed for a diffusion parameter of 0.15. Results regarding the overall performance, survey investigation, and loss patterns are provided.
Date: August 24, 1954
Creator: Wong, Robert Y.; Monroe, Daniel E. & Wintucky, William T.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Investigation of noise field and velocity profiles of an afterburning engine

Description: Report presenting sound pressure levels, frequency spectrum, and jet velocity profiles for an engine-afterburner combination at various values of afterburner fuel-air ratio. Lower sound pressure levels were obtained from a current fighter aircraft with a different afterburner configuration. Results regarding the jet temperature, jet Mach number and velocity, and sound measurements are provided.
Date: September 24, 1954
Creator: North, Warren J.; Callaghan, Edmund E. & Lanzo, Chester D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effects of airfoil profile on the two-dimensional flutter derivatives for wings oscillating in pitch at high subsonic speeds

Description: Report presenting a determination of aerodynamic lift and moment flutter derivatives at high subsonic speeds for a series of two-dimensional airfoils varying in thickness and thickness distribution. An evaluation of the results indicated that wing profile and angle of attack have major effects on flutter derivatives at speeds exceeding the Mach number for steady-state lift divergence. Results regarding lift and moment are provided.
Date: March 24, 1954
Creator: Wyss, John A. & Monfort, James C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Investigation at high subsonic speeds of the pressure distributions on a 45 degree sweptback horizontal tail mounted at 50-percent and 100-percent vertical-tail span

Description: Report presenting an investigation in the high-speed tunnel at high subsonic speeds and several angles of attack of the chordwise pressure distributions in sideslip at six span stations on a 45 degree sweptback, untapered, vertical tail with a 45 degree sweptback horizontal tail mounted at 50-percent and 100-percent vertical-tail span.
Date: November 24, 1954
Creator: Wiley, Harleth G. & Moseley, William C., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Comparison of effects of ailerons and combinations of spoiler-slot-deflector arrangements on spin recovery of sweptback-wing model having mass distributed along the fuselage

Description: Report presenting an investigation in the free-spinning tunnel to determine the effect of lateral-control systems using various combinations of spoilers, slots, and deflectors as compared with ailerons on the spin-recovery characteristics of a model of a 35 degree swept-wing fighter loaded heavily along the fuselage. Testing indicated that the ailerons were favorable for recovery when they were deflected full with the spin. Results regarding the effect of ailerons and two spoiler-slot-deflector… more
Date: November 24, 1954
Creator: Healy, Frederick M. & Klinar, Walter J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Investigation at high subsonic speeds of the effect of adding various combinations of missiles on the aerodynamic characteristics of sweptback and unswept wings combined with a fuselage

Description: Report presenting an investigation at Mach numbers from 0.50 to 0.94 of the effects of two sizes of missiles in several combinations of spanwise and vertical positions on the aerodynamic characteristics of wing-fuselage combinations with a 46.7 degree sweptback wing and an essentially unswept wing. Results regarding the drag characteristics and lift and pitch characteristics are provided.
Date: June 24, 1954
Creator: Silvers, H. Norman & Alford, William J., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

A Study of the Radiation From Laminar and Turbulent Open Propane-Air Flames as a Function of Flame Area, Equivalence Ratio, and Fuel Flow Rate

Description: Report presenting radiation measurements on open propane-air flames to find the extent to which radiant flux intensity can be used to measure the surface area of flames. Turbulent burning velocities calculated using this method and the average surface method are compared. Results regarding the laminar flame intensity measurements at different flow rates and equivalence ratios, filter intensity-ratio method, and surface intensity variations in the flames are provided.
Date: August 24, 1954
Creator: Clark, Thomas P. & Bittker, David A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

The Effect of Some Surface Roughness Elements on the Drag of a Body of Revolution at Supersonic Speeds

Description: "The effects of some rivets, butt joints, and lap joints on the drag of a body of revolution at zero lift at supersonic Mach numbers to 2.1 have been obtained in free flight with rocket-propelled models. The butt joints tested showed no significant effects on the drag. Rivets and lap joints increased the drag of the smooth-body configuration, the forward-facing lap joints contributing the greatest increases" (p. 1).
Date: November 24, 1954
Creator: Hopko, Russell N.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Experimental determination of aerodynamic forces normal to the chord due to rotating stall acting on compressor blading

Description: Report presenting an investigation conducted on an NACA axial-flow single-stage compressor with a 14-inch diameter and a 0.9 hub-tip ratio to determine the magnitude of the blade force variation due to the flow fluctuations caused by rotating stall. Results regarding steady-state blade forces, shapes of steady-state force curves, time variation in weight flow, oscillograms of strain-gage output, and effect of damping are provided.
Date: August 24, 1954
Creator: Johnson, Donald F. & Costilow, Eleanor L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Investigation of Noise Field and Velocity Profiles of an Afterburning Engine

Description: From Summary: "Sound pressure levels, frequency spectrum, and jet velocity profiles are presented for an engine-afterburner combination at various values of afterburner fuel - air ratio. At the high fuel-air ratios, severe low-frequency resonance was encountered which represented more than half the total energy in the sound spectrum. At similar thrust conditions, lower sound pressure levels were obtained from a current fighter air craft with a different afterburner configuration. The lower soun… more
Date: September 24, 1954
Creator: North, Warren J.; Callaghan, Edmund E. & Lanzo, Chester D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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