Effect Of Yaw And Angle Of Attack On Pressure Recovery And Mass Flow Characteristics Of A Rectangular Supersonic Scoop Inlet At A Mach Number Of 2 71
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Effect Of Yaw And Angle Of Attack On Pressure Recovery And Mass Flow Characteristics Of A Rectangular Supersonic Scoop Inlet At A Mach Number Of 2 71
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Author : Raymond J. Comenzo
language : en
Publisher:
Release Date : 1954
Effect Of Yaw And Angle Of Attack On Pressure Recovery And Mass Flow Characteristics Of A Rectangular Supersonic Scoop Inlet At A Mach Number Of 2 71 written by Raymond J. Comenzo and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1954 with Jet engines categories.
Flight Determination Of Drag And Pressure Recovery Of Two Scoop Inlets Located At Maximum Body Diameter Station At Mach Numbers From 0 8 To 1 8
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Author : Leonard W. Putland
language : en
Publisher:
Release Date : 1956
Flight Determination Of Drag And Pressure Recovery Of Two Scoop Inlets Located At Maximum Body Diameter Station At Mach Numbers From 0 8 To 1 8 written by Leonard W. Putland and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1956 with Boundary layer control categories.
Two models each utilizing a scoop inlet located at the maximum-body-diameter station operating mass-flow ratios from 0.76 to 0.96 have been flight tested at an angle of attack of approximately zero degrees over a Mach number range from 0.8 to 1.8, and a Reynolds number range from 2,000,000 to7,000,000 based on body maximum diameter. One of the scoop inlets had a circular cross section with a boundary-layer diverter. The other scoop inlet had a semicircular cross section wrapped partly around the body with a boundary-layer splitter plate ahead of the inlet.
Effects Of Compressibility And Large Angles Of Yaw On Pressure Indicated By A Total Pressure Tube
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Author : Milton D. Humphreys
language : en
Publisher:
Release Date : 1945
Effects Of Compressibility And Large Angles Of Yaw On Pressure Indicated By A Total Pressure Tube written by Milton D. Humphreys and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1945 with Aerodynamics categories.
Summary: The effects of compressibility and angle of yaw on the pressure measured by a round-nose and a flat-nose total-pressure tube have been investigated. The tests were conducted in the Langley rectangular high-speed tunnel at Mach numbers from 0.3 to 0.9 for angles of yaw from 0° to 180°. The results indicated that no error was incurred in the measurement of total pressure by either tube for angles of yaw from 0° to 10° in the Mach number range investigated. At constant Mach numbers, the round-nose tube had a linear variation of total-pressure error with angle of yaw at angles ranging from 50° to 70°. This characteristic is desirable in yaw heads of the Y-type. The flat-nose tube had a nonlinear variation of total-pressure error with angle of yaw in this range.
Transonic Off Design Drag And Performance Of An Axisymmetric Inlet With 40 Percent Internal Contraction On Design
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Author : Richard R. Woollett
language : en
Publisher:
Release Date : 1974
Transonic Off Design Drag And Performance Of An Axisymmetric Inlet With 40 Percent Internal Contraction On Design written by Richard R. Woollett and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1974 with Aerodynamics, Transonic categories.
An experimental investigation determined the drag and pressure performance of an axisymmetric supersonic inlet when operated in the transonic speed range. The inlet configuration was derived from a Mach 2.5 mixed compression inlet design with assumed variable geometry. At typical engine airflows the drag coefficient varied from 0.057 to 0.192 when the Mach number changed from 0.80 to 1.27. The presence of a wing simulator resulted in a sizable increase in total drag at Mach 1.2. This interference drag, which is roughly a 0.1 increase in drag coefficient, originates equally from an increase in both additive and cowl pressure drag.
Experimental Investigation Of The Performance Of A Mach 2 7 Two Dimensional Bifurcated Duct Inlet With 30 Percent Internal Contraction
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Author : Joseph F. Wasserbauer
language : en
Publisher:
Release Date : 1996
Experimental Investigation Of The Performance Of A Mach 2 7 Two Dimensional Bifurcated Duct Inlet With 30 Percent Internal Contraction written by Joseph F. Wasserbauer and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1996 with categories.
An experimental study was conducted to determine the performance of a two-dimensional, mixed-compression bifurcated duct inlet system designed for a free-stream Mach number of 2.7. Thirty percent of the supersonic area contraction occurred internally. A movable ramp was used to vary the contraction ratio for off-design operation. Boundary layer bleed regions were located on the cowl, centerbody, and sidewall surfaces. There were also provisions for vortex generators on the cowl and centerbody of the subsonic diffuser. Data were obtained over the Mach number range of 2.0 to 2.8 and at angles of yaw from 0 deg. to the maximum value prior to inlet un-start. The test at Mach 2.8 was to obtain data for an over- speed condition. The Reynolds number varied from 2.5 to 2.3 million/ft for Mach numbers above 2.5. At Mach numbers of 2.5 and lower, the Reynolds number was set at 2.5 million/ft. Bleed patterns, vortex generator patterns, and ramp position were varied, and three inlet configurations were selected for more extensive study. Two of these configurations had self-starting capability. The self-starting configuration that was developed produced 89 percent total pressure recovery at the compressor face station with 6.8 percent total bleed. The compressor face distortion was about 16 percent. Vortex generators were extremely effective in re-distributing flow but were not as effective in reducing distortion. Excellent flow symmetry was achieved between the separated halves of the inlet, and twin-duct instability was not observed. The ramp tip shock was steeper than expected. This caused the cowl lip shock to be reflected from the ramp instead of being cancelled at the shoulder. However, peak recovery at the throat was still obtained with the ramp near the design position.
Effect Of Downwash On The Estimated Elevator Deflection Required For Trim Of The Xs 1 Airplane At Supersonic Speeds
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Author : James T. Matthews
language : en
Publisher:
Release Date : 1948
Effect Of Downwash On The Estimated Elevator Deflection Required For Trim Of The Xs 1 Airplane At Supersonic Speeds written by James T. Matthews and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1948 with Bell X-1 (Supersonic plane) categories.
This report contains the results of an investigation to determine from linearized theory, which has recently become available, the downwash at supersonic speeds at the tail of the XS-1 airplane and the effect of the downwash on the elevator deflection required for trim. The results are presented in the form of curves showing the variation of downwash angle with angle of attack and elevator deflection required for trim plotted against Mach number. The calculations indicate that increasing up-elevator deflection is required with increasing Mach number (unstable variation) in level flight between Mach numbers of 1.1 and 1.6. A slight reduction in up-elevator deflection occurs between Mach numbers of 1.6 and 2.0. The stabilizer angle has a similar variation, that is, unstable up to a Mach number of about 1.6 and then becoming slightly stable up to a Mach number of 2.0. The reduction of downwash with increasing Mach number is not the main cause of the increase in up-elevator deflection. The main reasons for this trend are that the pitching-moment coefficients due to the wing camber, the wing lift, and the lift of the stabilizer are all in a nose-down direction, and as the Mach number increases, these pitching-moment coefficients apparently decrease less rapidly than the elevator effectiveness.
Experimental Dynamic Response Of A Two Dimensional Mach 2 7 Mixed Compression Inlet
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Author : Robert J. Baumbick
language : en
Publisher:
Release Date : 1972
Experimental Dynamic Response Of A Two Dimensional Mach 2 7 Mixed Compression Inlet written by Robert J. Baumbick and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1972 with Aerodynamics, Supersonic categories.
A test program was conducted on a two-dimensional supersonic inlet. Internal disturbances in diffuser exit mass flow were produced by oscillating overboard bypass doors. Open-loop dynamic responses of shock position, throat exit and diffuser exit static pressures are presented. The steady-state and dynamic coupling between ducts were also obtained. The experimental results from the two-dimensional inlet are compared to results from a similar size axisymmetric inlet and also to a transfer function synthesis program.
Aerodynamics For Engineering Students
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Author : Edward Lewis Houghton
language : en
Publisher:
Release Date : 1978
Aerodynamics For Engineering Students written by Edward Lewis Houghton and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1978 with categories.
Aircraft Design
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Author : Daniel P. Raymer
language : en
Publisher: AIAA (American Institute of Aeronautics & Astronautics)
Release Date : 2006
Aircraft Design written by Daniel P. Raymer and has been published by AIAA (American Institute of Aeronautics & Astronautics) this book supported file pdf, txt, epub, kindle and other format this book has been release on 2006 with Airplanes categories.
Winner of the Summerfield Book Award Winner of the Aviation-Space Writers Association Award of Excellence. --Over 30,000 copies sold, consistently the top-selling AIAA textbook title This highly regarded textbook presents the entire process of aircraft conceptual designfrom requirements definition to initial sizing, configuration layout, analysis, sizing, and trade studiesin the same manner seen in industry aircraft design groups. Interesting and easy to read, the book has more than 800 pages of design methods, illustrations, tips, explanations, and equations, and extensive appendices with key data essential to design. It is the required design text at numerous universities around the world, and is a favorite of practicing design engineers.
The Smell Of Kerosene
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Author : National Aeronautics and Space Administration
language : en
Publisher: Good Press
Release Date : 2023-12-28
The Smell Of Kerosene written by National Aeronautics and Space Administration and has been published by Good Press this book supported file pdf, txt, epub, kindle and other format this book has been release on 2023-12-28 with Transportation categories.
This book puts the reader in the pilot's seat for a "day at the office" unlike any other. The Smell of Kerosene tells the dramatic story of a NASA research pilot who logged over 11,000 flight hours in more than 125 types of aircraft. Donald Mallick gives the reader fascinating first-hand description of his early naval flight training, carrier operations, and his research flying career with NASA. After transferring to the NASA Flight Research Center, Mallick became involved with projects that further pushed the boundaries of aerospace technology. These included the giant delta-winged XB-70 supersonic airplane, the wingless M2-F1 lifting body vehicle, and triple-sonic YF-12 Blackbird. Mallick also test flew the Lunar Landing Research Vehicle and helped develop techniques used in training astronauts to land on the Moon.