Flight Measured Pressure Characteristics Of Aft Facing Steps In High Reynolds Number Flow At Mach Numbers Of 2 20 2 50 And 2 80 And Comparison With Other Data
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Flight Measured Pressure Characteristics Of Aft Facing Steps In High Reynolds Number Flow At Mach Numbers Of 2 20 2 50 And 2 80 And Comparison With Other Data
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Author : Sheryll Goecke Powers
language : en
Publisher:
Release Date : 1978
Flight Measured Pressure Characteristics Of Aft Facing Steps In High Reynolds Number Flow At Mach Numbers Of 2 20 2 50 And 2 80 And Comparison With Other Data written by Sheryll Goecke Powers and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1978 with Drag (Aerodynamics) categories.
Flight Measured Pressure Characteristics Of Aft Facing Steps In High Reynolds Number Flow At Mach Numbers Of 2 20 2 50 And 2 80 And Comparison With Other Data
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Author : National Aeronautics and Space Administration (NASA)
language : en
Publisher: Createspace Independent Publishing Platform
Release Date : 2018-08-22
Flight Measured Pressure Characteristics Of Aft Facing Steps In High Reynolds Number Flow At Mach Numbers Of 2 20 2 50 And 2 80 And Comparison With Other Data written by National Aeronautics and Space Administration (NASA) and has been published by Createspace Independent Publishing Platform this book supported file pdf, txt, epub, kindle and other format this book has been release on 2018-08-22 with categories.
The YF-12 airplane was studied to determine the pressure characteristics associated with an aft-facing step in high Reynolds number flow for nominal Mach numbers of 2.20, 2.50, and 2.80. Base pressure coefficients were obtained for three step heights. The surface static pressures ahead of and behind the step were measured for the no-step condition and for each of the step heights. A boundary layer rake was used to determine the local boundary layer conditions. The Reynolds number based on the length of flow ahead of the step was approximately 10 to the 8th power and the ratios of momentum thickness to step height ranged from 0.2 to 1.0. Base pressure coefficients were compared with other available data at similar Mach numbers and at ratios of momentum thickness to step height near 1.0. In addition, the data were compared with base pressure coefficients calculated by a semiempirical prediction method. The base pressure ratios are shown to be a function of Reynolds number based on momentum thickness. Profiles of the surface pressures ahead of and behind the step and the local boundary layer conditions are also presented. Powers, S. G. Armstrong Flight Research Center NASA-TM-72855, H-956 RTOP 505-06-34...
Aeronautical Engineering
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Author :
language : en
Publisher:
Release Date : 1978
Aeronautical Engineering written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1978 with Aeronautics categories.
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)
Comparison Of Wind Tunnel And Flight Measured Base Pressures From The Sharp Leading Edge Upper Vertical Fin Of The X 15 Airplane For Turbulent Flow At Mach Numbers From 1 5 To 5 0
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Author : Sheryll Goecke Powers
language : en
Publisher:
Release Date : 1971
Comparison Of Wind Tunnel And Flight Measured Base Pressures From The Sharp Leading Edge Upper Vertical Fin Of The X 15 Airplane For Turbulent Flow At Mach Numbers From 1 5 To 5 0 written by Sheryll Goecke Powers and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1971 with Drag (Aerodynamics) categories.
Wing Pressure Distribution And Boundary Layer Data Obtained From C 5a Flight Testing
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Author : Jones F. Cahill
language : en
Publisher:
Release Date : 1974
Wing Pressure Distribution And Boundary Layer Data Obtained From C 5a Flight Testing written by Jones F. Cahill and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1974 with Airplanes categories.
Analyses have been conducted of wing pressure distribution and boundary layer data obtained from flight tests of a C-5 airplane at Reynolds numbers from 35 to 90 million. Results showed that shock locations at high subsonic Mach numbers are as much as 10 to 12 percent chord aft of those measured in previous wind tunnel tests at 7.4 million Reynolds number. No consistent variation in shock location with Reynolds number within the range covered by the flight data can be detected, however. Considered of the boundary layer data in conjunction with the pressure measurements would indicate that this absence of scale effects at high Reynolds number results from the fact that trailing-edge separation is suppressed to the extent that separation at the shock is the dominant factor leading to flow breakdown.
Aircraft Excrescence Drag
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Author : Alec David Young
language : en
Publisher:
Release Date : 1981
Aircraft Excrescence Drag written by Alec David Young and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1981 with Boundary layer categories.
Flight Wing Surface Pressure And Boundary Layer Data Report From The F 111 Smooth Variable Camber Supercritical Mission Adaptive Wing
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Author : Sheryll Goecke Powers
language : en
Publisher:
Release Date : 1997
Flight Wing Surface Pressure And Boundary Layer Data Report From The F 111 Smooth Variable Camber Supercritical Mission Adaptive Wing written by Sheryll Goecke Powers and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1997 with categories.
Flight tests were conducted using the advanced fighter technology integration F-111 (AFTI/F-111) aircraft modified with a variable-sweep supercritical mission adaptive wing (MAW). The MAW leading- and trailing-edge variable-camber surfaces were deflected in flight to provide a near-ideal wing camber shape for the flight condition. The MAW features smooth, flexible upper surfaces and fully enclosed lower surfaces, which distinguishes it from conventional flaps that have discontinuous surfaces and exposed or semi-exposed mechanisms. Upper and lower surface wing pressure distributions were measured along four streamwise rows on the right wing for cruise, maneuvering, and landing configurations. Boundary-layer measurements were obtained near the trailing edge for one of the rows. Cruise and maneuvering wing leading-edge sweeps were 26 deg for Mach numbers less than 1 and 45 deg or 58 deg for Mach numbers greater than 1. The landing wing sweep was 9 deg or 16 deg. Mach numbers ranged from 0.27 to 1.41, angles of attack from 2 deg to 13 deg, and Reynolds number per unit foot from 1.4 times 10 to the 6th to 6.5 times 10 the the 6th. Leading-edge cambers ranged from 0 deg to 20 deg down, and trailing-edge cambers ranged from 1 deg up to 19 deg down. Wing deflection data for a Mach number of 0.85 are shown for three cambers. Wing pressure and boundary-layer data are given. Selected data comparisons are shown. Measured wing coordinates are given for three streamwise semispan locations for cruise camber and one spanwise location for maneuver camber.
Mach 3
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Author : Peter W. Merlin
language : en
Publisher:
Release Date : 2002
Mach 3 written by Peter W. Merlin and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 2002 with Aerodynamics, Hypersonic categories.
"During the 1950s, American aircraft designers emphasized configurations that flew increasingly high and fast, a trend that continued for nearly two decades. Then, during the 1070s, efficiency, noise reduction, and fuel economy also became important considerations, in part because military analysts no longer deemed speed and altitude the paramount capabilities necessary to ensure national security. Among the aircraft designs that transitioned from paper to hardware during the high-speed era, the Lockheed Blackbirds hold a unique place. The A-12, YF-12A, M-21, D-21, and SR-71 variants outperformed all other jet airplanes in terms of altitude and speed. To this day, they remain the only production aircraft capable of sustained cruise in excess of Mach 3. Developed in utmost secrecy, they eventually became some of the world's most famous aircraft. Conceived originally as spyplanes, several Blackbirds saw service with the National Aeronautics and Space Administration (NASA) as research platforms. This monograph describes the first major NASA project involving the Blackbirds. Conducted with the U.S. Air Force (USAF) as a partner, the NASA/USAF YF-12 research lasted 10 years, and produced a wealth of data on materials, structures, loads, heating, aerodynamics, and performance for high-speed aircraft."--Preface.
Flight Stability And Automatic Control
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Author : Robert C. Nelson
language : en
Publisher: WCB/McGraw-Hill
Release Date : 1998
Flight Stability And Automatic Control written by Robert C. Nelson and has been published by WCB/McGraw-Hill this book supported file pdf, txt, epub, kindle and other format this book has been release on 1998 with Aerodynamique / Aeronautique / Aerospatial / Automatique / Avion / Commande / Conception / Controle / Navigation / Stabilite categories.
The second edition of Flight Stability and Automatic Control presents an organized introduction to the useful and relevant topics necessary for a flight stability and controls course. Not only is this text presented at the appropriate mathematical level, it also features standard terminology and nomenclature, along with expanded coverage of classical control theory, autopilot designs, and modern control theory. Through the use of extensive examples, problems, and historical notes, author Robert Nelson develops a concise and vital text for aircraft flight stability and control or flight dynamics courses.
Shock Wave Boundary Layer Interactions
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Author : Holger Babinsky
language : en
Publisher: Cambridge University Press
Release Date : 2011-09-12
Shock Wave Boundary Layer Interactions written by Holger Babinsky and has been published by Cambridge University Press this book supported file pdf, txt, epub, kindle and other format this book has been release on 2011-09-12 with Technology & Engineering categories.
Shock wave-boundary-layer interaction (SBLI) is a fundamental phenomenon in gas dynamics that is observed in many practical situations, ranging from transonic aircraft wings to hypersonic vehicles and engines. SBLIs have the potential to pose serious problems in a flowfield; hence they often prove to be a critical - or even design limiting - issue for many aerospace applications. This is the first book devoted solely to a comprehensive, state-of-the-art explanation of this phenomenon. It includes a description of the basic fluid mechanics of SBLIs plus contributions from leading international experts who share their insight into their physics and the impact they have in practical flow situations. This book is for practitioners and graduate students in aerodynamics who wish to familiarize themselves with all aspects of SBLI flows. It is a valuable resource for specialists because it compiles experimental, computational and theoretical knowledge in one place.