National Advisory Committee for Aeronautics (NACA) - 295 Matching Results

Search Results

Aerodynamic characteristics and flying qualities of a tailless triangular-wing airplane configuration as obtained from flights of rocket-propelled models at transonic and supersonic speeds

Description: Report discussing a flight investigation of rocket-powered models of a tailless triangular-wing airplane configuration was made through the transonic and low supersonic speed range at the Langley Pilotless Aircraft Research Station at Wallops Island, Va. An analysis of the aerodynamic coefficients, stability derivatives, and flying qualities based on the results obtained from the successful flight tests of three models is presented.
Date: November 1956
Creator: Mitcham, Grady L; Stevens, Joseph E & Norris, Harry P
Partner: UNT Libraries Government Documents Department

Aerodynamic investigation of a parabolic body of revolution at mach number of 1.92 and some effects of an annular supersonic jet exhausting from the base

Description: Report discussing an aerodynamic investigation of a slender pointed parabolic body of revolution was conducted at Mach number of 1.92 with and without the effects of an annular supersonic jet exhausting from the base.
Date: September 1956
Creator: Love, Eugene S
Partner: UNT Libraries Government Documents Department

An air-flow-direction pickup suitable for telemetering use on pilotless aircraft

Description: From Summary: "A free-swiveling vane-type pickup for measuring air flow direction in both the angle-of-attack and angle-of-sideslip directions is described. Test results are presented which indicate that the pickup is aerodynamically stable and has an accuracy, obtained from a bench calibration, of better than 0.3^o under conditions including acceleration up to 20g in any direction, Mach numbers from 0.5 to 2.8, dynamic pressures up to at least 65 psi. Equations and curves which can be used to obtain flow direction at the center of gravity of a maneuvering model are presented."
Date: October 1956
Creator: Ikard, Wallace L.
Partner: UNT Libraries Government Documents Department

Analysis and comparison with theory of flow-field measurements near a lifting rotor in the Langley full-scale tunnel

Description: From Introduction: "The time-averaged flows are considerably simpler to deal with theoretically than are the instantaneous flows, and the results of several theoretical analyses are available (refs. 2 to 6, for example). Several previous experimental investigations (see ref. 7 for a bibliography) have provided some qualitative information on the subject by the use of smoke in flight and in wind tunnels. However, quantitative measurements (refs. 8 to 10) are extremely scarce and, in general, are inadequate either to define the nature of the flow or to check the accuracy of the theoretical calculations."
Date: April 1, 1956
Creator: Heyson, Harry H
Partner: UNT Libraries Government Documents Department

Analysis of a spin and recovery from time histories of attitudes and velocities as determined for a dynamic model of a contemporary fighter airplane in the free-spinning tunnel

Description: From Introduction: "In this paper are presented descriptions of the camera setups and associated equipment, the equations and methods used in determining the model attitudes and motions from the film, and time-history curves of the variables of the spin and recovery investigated. Discussions of the nature of the spin and recovery obtained and of factors ostensibly affecting these motions are included."
Date: April 1, 1956
Creator: Scher, Stanley H
Partner: UNT Libraries Government Documents Department

An analysis of airspeed, altitude, and acceleration data obtained from a twin-engine transport airplane operated over a feeder-line route in the Rocky Mountains

Description: Time-history data of airspeed, altitude, and acceleration obtained with the NACA VGH recorder from a twin-engine airplane operated by a regional feeder airline in the Rocky Mountains are evaluated to determine the magnitude and frequency of occurrence of gusts and gust accelerations and the operating airspeeds and altitudes. The results obtained are compared with the results previously obtained from a representative short-haul and long-haul operation.
Date: October 1, 1956
Creator: Copp, Martin R & Fetner, Mary W
Partner: UNT Libraries Government Documents Department

An analysis of buzzing in supersonic ram jets by a modified one-dimensional nonstationary wave theory

Description: From Introduction: "The buzz or pulsation of axially symmetric supersonic inlets having central bodies has been the subject of investigations since Oswatitsch first observed the phenomenon in 1944 (ref.1). This buzzing is essentially an oscillation of the normal shock along the spike of certain diffusers operating at mass flows below design, and this buzz decreases the performance of the propulsion units appreciably (ref.2). This paper continues the analysis of the buzzing cycle by means of a modified one-dimensional approach."
Date: July 1956
Creator: Trimpi, Robert L
Partner: UNT Libraries Government Documents Department

Analysis of elastic thermal stresses in thin plate with spanwise and chordwise variations of temperature and thickness

Description: From Introduction: "The object of the present paper is to present an approximate method for calculating accurately the thermal stresses in a thin plate with both chordwise and spanwise variations in temperature and chordwise but restricted spanwise variations in thickness."
Date: November 1956
Creator: Mendelson, Alexander & Hirschberg, Marvin
Partner: UNT Libraries Government Documents Department

An analysis of estimated and experimental transonic downwash characteristics as affected by plan form and thickness for wing and wing-fuselage configurations

Description: From Introduction: "The purpose of the present paper is to present summary of the information gleaned from various transonic-bump investigations of wing and wing-fuselage configurations at two representative tail heights and to compare these results with theoretical estimations made in subsonic and supersonic Mach number range."
Date: April 1956
Creator: Weil, Joseph; Campbell, George S & Diederich, Margaret S
Partner: UNT Libraries Government Documents Department

Analysis of laminar incompressible flow on semiporous channels

Description: From Introduction: "Experimental results for flow in a rectangular channel with injection through a porous wall are given in reference 1. As part of the study to guide future experiments, laminar flow in a semiporous channel is investigated herein. In the present investigation, a third-order perturbation solution for laminar incompressible flow in a semiporous channel is presented."
Date: August 1, 1956
Creator: Donoughe, Patrick L
Partner: UNT Libraries Government Documents Department

Analysis of particle motions for a class of three-dimensional incompressible laminar boundary layers

Description: From Introduction: "Results obtained in the experimental investigations of secondary flows in turbomachines (refs. 1 to 3) indicate that information concerning three-dimensional laminar boundary-layer behavior can be of practical value in interpreting and correlating measurements of losses in the turbo-machines for design purposes. Reference 4 gives a theoretical analysis of the overturning (more than mainstream turning) of the three-dimensional laminar boundary layer developed on flat or nearly flat surfaces, under mainstream flows which consist of streamline translates (i.e., the entire streamline pattern can be obtained by translating any particular streamline pattern can be obtained by translating any particular streamline parallel to the leading edge, fig. 1) with constant axial velocity component."
Date: November 1, 1956
Creator: Hansen, Arthur G & Herzig, Howard Z
Partner: UNT Libraries Government Documents Department

Analytical study of modifications to the autopilot of a fighter airplane in order to reduce the response to side gusts

Description: From Introduction: "This study was the basis for the present paper which deals with means for compensating the roll and yaw response to side gusts of a fighter airplane in combination with an autopilot. Results are presented which compare the response to side gusts of the original and compensating autopilots; the responses to commands are presented also."
Date: March 1956
Creator: Mathews, Charles W & Adams, James J
Partner: UNT Libraries Government Documents Department