Download or read book Wind Tunnel Investigation of Aerodynamic Loads on Weapons Separated from Carriage Under the Wing of a Tactical Fighter Aircraft at Supersonic Speeds written by J. C. Donaldson and published by . This book was released on 1973 with total page 212 pages. Available in PDF, EPUB and Kindle. Book excerpt: Exploratory static-stability tests were made on models of the MK-84 weapon and a modular weapon configuration during simulated weapon separation from the wing of the F-4C Tactical Fighter Aircraft at freestream Mach numbers 1.76, 2.0, and 2.5. Data were obtained with the parent aircraft at zero angle of attack and the weapon at the carriage incidence angle of -1 deg. Supplementary data were obtained for weapon angles of attack of + or - deg. Unit Reynolds number ranged from 4.6 million per ft at M free stream mach number = 1.76 to 6.2 million per ft at M free stream mach number = 2.5. Selected results are presented which show the effects on the weapon aerodynamic loads of free-stream Mach number, weapon angle of attack, weapon axial position, and the presence of other stores. Representative shadowgraph and schlieren photographs of the interference flow field are also presented. (Author).
Download or read book Wind Tunnel Investigation of Aerodynamic Loads on Weapons Separated from Carriage Under The Wing of a Tactical Fighter Aircraft at Supersonic Speeds written by and published by . This book was released on 1973 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: Exploratory static-stability tests were made on models of the MK-84 weapon and a modular weapon configuration during simulated weapon separation from the wing of the F-4C Tactical Fighter Aircraft at freestream Mach numbers 1.76, 2.0, and 2.5. Data were obtained with the parent aircraft at zero angle of attack and the weapon at the carriage incidence angle of -1 deg. Supplementary data were obtained for weapon angles of attack of + or - deg. Unit Reynolds number ranged from 4.6 million per ft at M free stream mach number = 1.76 to 6.2 million per ft at M free stream mach number = 2.5. Selected results are presented which show the effects on the weapon aerodynamic loads of free-stream Mach number, weapon angle of attack, weapon axial position, and the presence of other stores. Representative shadowgraph and schlieren photographs of the interference flow field are also presented. (Author).
Download or read book Wind Tunnel Investigation of Aerodynamic Loads on Weapons Separated from Carriage Under The Wing of a Tactical Fighter Aircraft at Supersonic Speeds written by and published by . This book was released on 1973 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: Exploratory static-stability tests were made on models of the MK-84 weapon and a modular weapon configuration during simulated weapon separation from the wing of the F-4C Tactical Fighter Aircraft at freestream Mach numbers 1.76, 2.0, and 2.5. Data were obtained with the parent aircraft at zero angle of attack and the weapon at the carriage incidence angle of -1 deg. Supplementary data were obtained for weapon angles of attack of + or - deg. Unit Reynolds number ranged from 4.6 million per ft at M free stream mach number = 1.76 to 6.2 million per ft at M free stream mach number = 2.5. Selected results are presented which show the effects on the weapon aerodynamic loads of free-stream Mach number, weapon angle of attack, weapon axial position, and the presence of other stores. Representative shadowgraph and schlieren photographs of the interference flow field are also presented. (Author).
Download or read book External Store Airloads Prediction Technique written by A. R. Rudnicki (Jr.) and published by . This book was released on 1975 with total page 170 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Technical Information Indexes written by United States. Naval Air Systems Command and published by . This book was released on 1975 with total page 148 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book National Aeronautics and Space Administration written by United States. Congress. House. Committee on Appropriations. Subcommittee on HUD-Independent Agencies and published by . This book was released on 1985 with total page 1112 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Technical Abstract Bulletin written by and published by . This book was released on 1978 with total page 156 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1982 with total page 648 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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.
Download or read book Wind tunnel Investigation of the Aerodynamic Characteristics in Pitch and Sideslip at High Subsonic Speeds of a Wing fuselage Combination Having a Triangular Wing of Aspect Ratio 4 written by Paul G. Fournier and published by . This book was released on 1953 with total page 34 pages. Available in PDF, EPUB and Kindle. Book excerpt: The results presented in the present paper are part of a program conducted to investigate the effect of wing plan form on the aerodynamic characteristics in pitch, in sideslip, and during steady roll. This paper presents the aerodynamic characteristics in pitch and sideslip at high subsonic speeds of a wing-fuselage combination having a triangular wing of aspect ratio 4, a leading-edge sweep of angle of 45 degrees, and with an NACA 65A006 airfoil section parallel to the plane of symmetry.
Download or read book NASA SP written by and published by . This book was released on 1986 with total page 544 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Advisory Group for Aerospace Research and Development Index of Publications written by North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development and published by . This book was released on 1980 with total page 446 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Government Reports Announcements Index written by and published by . This book was released on 1977 with total page 210 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Aeronautical Engineering written by and published by . This book was released on 1991 with total page 1036 pages. Available in PDF, EPUB and Kindle. Book excerpt: A selection of annotated references to unclassified reports and journal articles that were introduced into the NASA scientific and technical information system and announced in Scientific and technical aerospace reports (STAR) and International aerospace abstracts (IAA).
Download or read book The Benefits and Risks Associated with Use of the Wind Tunnel in Safe Separation Flight Test written by and published by . This book was released on 2003 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt: Flight test demonstrating safe separation of stores from aircraft has gained greater importance since World War II. With the expansion of aircraft flight envelopes, the impact of the aircraft flow field on store separation has also expanded. At best the store fell away from the aircraft; at worst it could tumble or hit the aircraft causing significant structural damage. Early safe separation flight test programs took a simple approach, starting slow and in straight and level flight and then in small increments, building up to supersonic straight path dives. Unfortunately, this approach required a great deal of stores as well as numerous flights. As the cost of operating test aircraft and weapons has increased, this approach has become increasingly expensive. Wind tunnels have been used with great success since the dawn of aviation as a tool to engineer new concepts in aerodynamics. Once only the domain for flow visualization of airfoils, they have matured into a system that can test high angles of attack at full scale to small scale hypersonic flow. From this growth has emerged the capability to model the flow field around an aircraft and predict the separation characteristics of weapons from the aircraft. By using the wind tunnel to find the worst-case separation characteristics, flight test engineers could reduce the build up necessary and the number of flights required. This was seemingly the answer to the need of program managers as the way to reduce risk and cost. This thesis examined the results of two modern safe separation programs, the Mk-82 Joint Direct Attack Munition (JDAM) and the GBU-24B/B Low Level Laser Guided Bomb, for the technical and cost impact of the wind tunnel. This examination has shown that the realities of flight test and the limitations of wind tunnel predictions have combined to reduce the wind tunnel effectiveness in providing a cost savings to safe separation programs. For the JDAM, the wind tunnel was able to significantly reduce the number of flights required to demonstrate safe separation, but weapon umbilical failures required more flights to be added back into the program. The GBU-24B/B on the U.S. Navy's new Super Hornet aircraft is in jeopardy of failing to meet fleet operational requirements as a result of waiting for wind tunnel data. In contrast, the GBU-24B/B program conducted on the older Hornet was completed without the wind tunnel in significantly less time and cost. Program managers and engineers must weigh the benefits of having wind tunnel data with the risks that come with the wind tunnel. In some cases, the wind tunnel may come at a higher a price and require more time than a conventional flight test program without wind tunnel predictions.
Download or read book From Archangel to Senior Crown written by Peter W. Merlin and published by AIAA (American Institute of Aeronautics & Astronautics). This book was released on 2008 with total page 240 pages. Available in PDF, EPUB and Kindle. Book excerpt: The Lockheed Blackbirds hold a unique place in the development of aeronautics. In their day, the A-12, YF-12, M-21, D-21, and SR-71 variants outperformed all other jet airplanes in terms of altitude and speed. Now retired, they remain the only production aircraft capable of sustained Mach 3 cruise and operational altitudes above 80,000 feet.This is the first book to address the technical aspects of these incredible aircraft. The author describes the design evolution of the Blackbird, from the Archangel to the Senior Crown (the Air Force's SR-71.) He describes in detail the construction and materials challenges faced by Lockheed, as well as the Blackbird's performance characteristics and capabilities.A NASA historian, the author describes NASA's role in using the aircraft as a flying laboratory to collect data on materials, structures, loads, heating, aerodynamics, and performance for high-speed aircraft. The reader will benefit from the technical and programmatic lessons learned.This volume was produced in cooperation with the National Aeronautics and Space Administration.
Download or read book International Aerospace Abstracts written by and published by . This book was released on 1986 with total page 918 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Wind Tunnel flight Data Correlation u written by James A. Behal and published by . This book was released on 1971 with total page 692 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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.
