Data Report for a Test Program to Study Transonic Flow Fields about Aircraft with Application to External Stores. Volume II. Mach Number 0.925 Flow-Field Survey Data for the 4-Percent Thick Wing-Body Combination PDF Download
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Author: Stanley C Perkins (Jr)
Publisher:
ISBN:
Category :
Languages : en
Pages : 249
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Book Description
A test program was conducted to obtain measurements of flow velocities and static pressures in the vicinity of wing-body-store model (representative of a fighter-type aircraft) as well as surface pressures, forces, and moments on the model. Volume II, presents the tabulated flowfield data for the 4-percent thick wing model at Mach number 0.925.
Author: Stanley C Perkins (Jr)
Publisher:
ISBN:
Category :
Languages : en
Pages : 249
Get Book Here
Book Description
A test program was conducted to obtain measurements of flow velocities and static pressures in the vicinity of wing-body-store model (representative of a fighter-type aircraft) as well as surface pressures, forces, and moments on the model. Volume II, presents the tabulated flowfield data for the 4-percent thick wing model at Mach number 0.925.
Author: Stanley C Perkins (Jr)
Publisher:
ISBN:
Category :
Languages : en
Pages : 248
Get Book Here
Book Description
A test program was conducted to obtain measurements of flow velocities and static pressures in the vicinity of wing-body-store model (representative of a fighter-type aircraft) as well as surface pressures, forces, and moments on the model. Volume IV presents the tabulated flowfield data for the 4-percent thick wing model at Mach number 1.025.
Author: Stanley C Perkins (Jr)
Publisher:
ISBN:
Category :
Languages : en
Pages : 249
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Book Description
A test program was conducted to obtain measurements of flow velocities and static pressures in the vicinity of wing-body-store model (representative of a fighter-type aircraft) as well as surface pressures, forces, and moments on the model. Volume III presents the tabulated flowfield data for the 4-percent thick wing model at Mach number 0.975.
Author: Stanley C Perkins (Jr)
Publisher:
ISBN:
Category :
Languages : en
Pages : 337
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Book Description
A test program was conducted to obtain measurements of flow velocities and static pressures in the vicinity of wing-body-store model (representative of a fighter-type aircraft) as well as surface pressures, forces, and moments on the model. Flow velocities and static pressures were also measured near the tunnel walls to provide outer flow field information. Volume V presents the tabulated flow-field data for 6-percent thick wing model.
Author: Stanley C Perkins (Jr)
Publisher:
ISBN:
Category :
Languages : en
Pages : 138
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Book Description
A test program was conducted to obtain measurements of flow velocities and static pressures in the vicinity of wing-body-store model (representative of a fighter-type aircraft) as well as surface pressures, forces, and moments on the model. Flow velocities and static pressures were also measured near the tunnel walls to provide outer flow field information. This report presents the data obtained during the test program conducted in the 4T and 16T Wind Tunnels at Arnold Engineering Development Center. The Flow-field data were obtained at Mach numbers 0.925, 0.975, and 1.025 and constitute the major part of the data. Volume I is a summary report which gives detailed information on the test program and presents uncertainties associated with the various types of data taken in the 4T Wind Tunnel. The volume also presents tunnel-empty and Mach-number surveys, as well as tabulated force and moment and pressure data for the Mach number range 0.80 to 1.15 and angles of attack -2, -5, 0, 2, and 5.
Author: Stanley C Perkins (Jr)
Publisher:
ISBN:
Category :
Languages : en
Pages : 106
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Book Description
A test program was conducted to obtain measurements of flow velocities and static pressures in the vicinity of wing-body-store model (representative of a fighter-type aircraft) as well as surface pressures, forces, and moments on the model. Volume VI presents data obtained for the 4-percent thick wing model in the 16T Wind Tunnel.
Author: S. S. Stahara
Publisher:
ISBN:
Category :
Languages : en
Pages : 247
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Book Description
This volume of the data report presents the flow-field survey data for configurations 21 and 22 at Mach numbers M1 = 0.925, M2 = 0.950, and M3 = 1.05 and angles of attack alpha = 0 deg, 2 deg, and 5 deg. The data were obtained in the 4T Wind Tunnel at Arnold Engineering and Development Center. The tests were performed at a nominal Reynolds number per foot of 3.0 million.
Author: William T Strike (Jr.)
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 92
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Book Description
This test was conducted in support of a program to develop a generalized analytical method for predicting the separation characteristics of stores from a high-speed aircraft (parent body). The tests were conducted in the von Karman Gas Dynamics Facility (VKF), Tunnel A, at nominal Mach numbers of 1.5, 1.76, 2.0, and 2.5 at a nominal free-stream Reynolds number of 4 x 10 to 6th power per foot. The test program involved three phases, namely flow-field surveys using a cone probe rake to determine local flow-field angles and velocity, pressure distributions on the store as it separated from a parent body, and six-component force and moment data on the store. The tests were conducted at angles of attack of zero and five degrees. This document contains a detailed description of the calibration procedure for the 20-deg half-angle cone probes and the method used to evaluate the local flow-field properties from the cone probe surface pressure and pitot pressure measurements. Also included is a comparison of integrated pressure data with the force and moment data obtained on the storebody by a balance. (Author).
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 162
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Book Description
Author: E.H. Dowell
Publisher: Springer Science & Business Media
ISBN: 9401104999
Category : Technology & Engineering
Languages : en
Pages : 724
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Book Description
Aeroelasticity is the study of flexible structures situated in a flowing fluid. Its modern origins are in the field of aerospace engineering, but it has now expanded to include phenomena arising in other fields such as bioengineering, civil engineering, mechanical engineering and nuclear engineering. The present volume is a teaching text for a first, and possibly second, course in aeroelasticity. It will also be useful as a reference source on the fundamentals of the subject for practitioners. In this third edition, several chapters have been revised and three new chapters added. The latter include a brief introduction to `Experimental Aeroelasticity', an overview of a frontier of research `Nonlinear Aeroelasticity', and the first connected, authoritative account of `Aeroelastic Control' in book form. The authors are drawn from a range of fields including aerospace engineering, civil engineering, mechanical engineering, rotorcraft and turbomachinery. Each author is a leading expert in the subject of his chapter and has many years of experience in consulting, research and teaching.
