Wind Tunnel/flight Data Correlation (u). PDF Download
Are you looking for read ebook online? Search for your book and save it on your Kindle device, PC, phones or tablets. Download Wind Tunnel/flight Data Correlation (u). PDF full book. Access full book title Wind Tunnel/flight Data Correlation (u). by James A. Behal. Download full books in PDF and EPUB format.
Author: James A. Behal
Publisher:
ISBN:
Category : Buffeting (Aerodynamics)
Languages : en
Pages : 506
Get Book Here
Book Description
A program was conducted to obtain data, both steady state and dynamic, from wind tunnel models and full scale flight tests of the RA-5C aircraft. Data were acquired on 0.228 and 0. 125 scale RA-5C inlet models and on a fully instrumented flight test RA-5C aircraft. Interim data reports presenting the data acquired during each test have been published. These data were utilized in this report to develop scaling techniques for correlating small scale model wind tunnel data with full scale flight data. Data presented include duct steady state operating characteristics and pressure distributions in the inlet and at the engine face. Dynamic data are presented in the form of engine face turbulence contour plots, radial turbulence distributions and selected spectral data functions. Data are presented for variations of angle of attack, angle of yaw, Reynolds number, ramp angle, secondary flow rates and inlet diverter width. Brief descriptions of the model and test methods are also presented.
Author: James A. Behal
Publisher:
ISBN:
Category : Buffeting (Aerodynamics)
Languages : en
Pages : 506
Get Book Here
Book Description
A program was conducted to obtain data, both steady state and dynamic, from wind tunnel models and full scale flight tests of the RA-5C aircraft. Data were acquired on 0.228 and 0. 125 scale RA-5C inlet models and on a fully instrumented flight test RA-5C aircraft. Interim data reports presenting the data acquired during each test have been published. These data were utilized in this report to develop scaling techniques for correlating small scale model wind tunnel data with full scale flight data. Data presented include duct steady state operating characteristics and pressure distributions in the inlet and at the engine face. Dynamic data are presented in the form of engine face turbulence contour plots, radial turbulence distributions and selected spectral data functions. Data are presented for variations of angle of attack, angle of yaw, Reynolds number, ramp angle, secondary flow rates and inlet diverter width. Brief descriptions of the model and test methods are also presented.
Author: E. Bloetscher
Publisher:
ISBN:
Category : Balloons
Languages : en
Pages : 220
Get Book Here
Book Description
The Aerodynamic Deployable Decelerator Performance-Evaluation Program (ADDPEP) aims to advance the state of the art by developing the most effective analytical and empirical techniques for designing aerodynamic deployable decelerators and for evaluating these engineering techniques through wind-tunnel and free-flight tests. During ADDPEP Phase 2, two types of decelerators were investigated: large reefed supersonic parachutes and raminflated balloon-type BALLUTEs. The areas investigated included analytical and engineering design, material capabilities, fabrication techniques, and wind-tunnel and free-flight tests. Free-flight tests were performed on a hemisflo parachute having a nominal 16-ft-diameter canopy, a 10-percent extended skirt, and a 14-percent porosity. This design was tested for 200,000-lb opening loads, deployment Mach numbers were 1.50, 1.63, and 1.84 at altitudes of 13,700, 15,500, and 10,500 ft, respectively. The results confirmed that this parachute has excellent aerodynamic characteristics and adequate strength. Five-foot-diameter BALLUTEs, both textile and metal, were fabricated. These were designed for a broad spectrum of deployment conditions ranging from Mach 2.7 at 73,000 ft to Mach 10 at 225,000 ft. The textile BALLUTEs were wind-tunnel and free-flight tested; the metal BALLUTEs were wind-tunnel tested only. Flight tests were limited to Mach 9.7, and wind-tunnel tests to Mach 3. The flight test data supported wind-tunnel data, which indicated that excellent stability and structurally adequate designs can be attained with five-foot-diameter BALLUTEs.
Author: United States. Columbia Accident Investigation Board
Publisher:
ISBN:
Category : Space shuttles
Languages : en
Pages : 348
Get Book Here
Book Description
Author: T. F. Langham
Publisher:
ISBN:
Category : Jet planes, Military
Languages : en
Pages : 64
Get Book Here
Book Description
An analytical study has been conducted to determine the usefulness of rotation-balance aerodynamic data in calculating the steady-state spin motion of a current fighter aircraft configuration. The analysis utilizes a nonlinear six-degree-of-freedom digital computer program to generate time histories of airplane spinning motion. Three aerodynamic data models were formulated and used in the spin analysis. The first model represents the conventional use of static and forced-oscillation data; the second model uses the static and forced-oscillation data but restricts the forced-oscillation data to that component of the total angular rate that is oscillatory; and the third model incorporates rotation-balance data from model 2 and restricts the rotation-balance data to that component of the total angular rate that is steady state. The results indicate a significantly different motion resulting from the three aerodynamic data models when compared to each other and to full-scale flight test steady-state spin motions. The motions produced by the rotation-balance aerodynamic model more closely simulate the motions exhibited during the flight tests. (Author).
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 804
Get Book Here
Book Description
Lists citations with abstracts for aerospace related reports obtained from world wide sources and announces documents that have recently been entered into the NASA Scientific and Technical Information Database.
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1908
Get Book Here
Book Description
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 538
Get Book Here
Book Description
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 544
Get Book Here
Book Description
Author: Robert C. Nelson
Publisher:
ISBN:
Category : History
Languages : en
Pages : 464
Get Book Here
Book Description
This edition of this this flight stability and controls guide features an unintimidating math level, full coverage of terminology, and expanded discussions of classical to modern control theory and autopilot designs. Extensive examples, problems, and historical notes, make this concise book a vital addition to the engineer's library.
Author: Thomas R. Yechout
Publisher: AIAA
ISBN: 9781600860782
Category : Aerodynamics
Languages : en
Pages : 666
Get Book Here
Book Description
Based on a 15-year successful approach to teaching aircraft flight mechanics at the US Air Force Academy, this text explains the concepts and derivations of equations for aircraft flight mechanics. It covers aircraft performance, static stability, aircraft dynamics stability and feedback control.
