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Force And Pressure Characteristics For A Series Of Nose Inlets At Mach Numbers From 159 To 199
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Book Synopsis Force and Pressure Characteristics for a Series of Nose Inlets at Mach Numbers from 1.59 to 1.99 by : L. J. Obery
Download or read book Force and Pressure Characteristics for a Series of Nose Inlets at Mach Numbers from 1.59 to 1.99 written by L. J. Obery and published by . This book was released on 1951 with total page 72 pages. Available in PDF, EPUB and Kindle. Book excerpt: An experimental investigation to determine the external and internal flow characteristics of a typical ram-jet-inlet configuration of an external-compression type utilizing an isentropic spike and a subsonic diffuser was conducted in the NACA Lewis 8- by 6-foot supersonic wind tunnel. The model was investigated of a range of mass-flow ratios at angles of attack up to 10 degrees, free-stream Mach numbers of 1.59, 1.79, and 1.99, and a Reynolds number of approximately 2,400,000 based on inlet diameter.
Book Synopsis Force and Pressure Characteristics for a Series of Nose Inlets at Mach Numbers from 1.59 to 1.99 by : E. Howard
Download or read book Force and Pressure Characteristics for a Series of Nose Inlets at Mach Numbers from 1.59 to 1.99 written by E. Howard and published by . This book was released on 1951 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Force and Pressure Characteristics for a Series of Nose Inlets at Mach Numbers from 1.59 to 1.99 by : Maynard I. Weinstein
Download or read book Force and Pressure Characteristics for a Series of Nose Inlets at Mach Numbers from 1.59 to 1.99 written by Maynard I. Weinstein and published by . This book was released on 1951 with total page 51 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation was conducted in the NACA Lewis 8- by 6-foot supersonic wind tunnel to determine the force and pressure characteristics of an all-external compression inlet having a conical spike and a supersonic cowl lip. Measurements of lift, drag pitching moment, and internal and external pressures were made at free-stream Mach numbers of 1.59, 1.79, and 1.99 for a range of mass-flow ratios and angles of attack to 10 degrees. The average Reynolds number based on inlet diameter was 2,300,000.
Book Synopsis An Investigation of Several NACA 1-series Nose Inlets with and Without Protruding Central Bodies at High-subsonic Mach Numbers and at a Mach Number of 1.2 by : Robert E. Pendley
Download or read book An Investigation of Several NACA 1-series Nose Inlets with and Without Protruding Central Bodies at High-subsonic Mach Numbers and at a Mach Number of 1.2 written by Robert E. Pendley and published by . This book was released on 1950 with total page 58 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation of three NACA 1-series nose inlets, two of which were fitted with protruded central bodies, was conducted in the Langley 8-foot high-speed tunnel. An elliptical-nose body, which had a critical Mach number approximately equal to that of one of the nose inlets, was also tested. Tests were made near zero angle of attack for a Mach number range from 0.4 to 0.925 and for the supersonic Mach number of 1.2. The inlet-velocity-ratio range extended from zero to a maximum value of 1.34. Measurements included pressure distribution, external drag, and total-pressure loss of the internal flow near the inlet. Drag was not measured for the tests at the supersonic Mach number.
Book Synopsis Force and Pressure Tests on Cones with Simulated Ablated Noses at Mach Numbers 8 and 16 by : J. S. Hahn
Download or read book Force and Pressure Tests on Cones with Simulated Ablated Noses at Mach Numbers 8 and 16 written by J. S. Hahn and published by . This book was released on 1972 with total page 262 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Tests of a Small-scale NACA Submerged Inlet at Transonic Mach Numbers by : L. Stewart Rolls
Download or read book Tests of a Small-scale NACA Submerged Inlet at Transonic Mach Numbers written by L. Stewart Rolls and published by . This book was released on 1950 with total page 22 pages. Available in PDF, EPUB and Kindle. Book excerpt: The pressure-recovery characteristics at the vertical center line of an NACA submerged inlet of aspect ratio 5 have been measured in the Mach number range 0.60 to 1.08 by the wing-flow method. The variation of ram-recovery ratio determined from measurements at the center line of the inlet with test station Mach number is presented for mass-flow ratios of 0.30 to 0.60.
Book Synopsis A Method for Designing Low-drag Nose-inlet-body Combinations for Operation at Moderate Supersonic Speeds by : Robert R. Howell
Download or read book A Method for Designing Low-drag Nose-inlet-body Combinations for Operation at Moderate Supersonic Speeds written by Robert R. Howell and published by . This book was released on 1954 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis An Investigation of Several NACA 1-series Nose Inlets with and Without Protruding Central Bodies at High-subsonic Mach Numbers and at a Mach Number of 1.2 by : Robert E. Pendley
Download or read book An Investigation of Several NACA 1-series Nose Inlets with and Without Protruding Central Bodies at High-subsonic Mach Numbers and at a Mach Number of 1.2 written by Robert E. Pendley and published by . This book was released on 1955 with total page 51 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation of three NACA 1-series nose inlets, two of which were fitted with protruded central bodies, was conducted in the Langley 8-foot high-speed tunnel. An elliptical-nose body, which had a critical Mach number approximately equal to that of one of the nose inlets, was also tested. Tests were made near zero angle of attack for a Mach number range from 0.4 to 0.925 and for the supersonic Mach number of 1.2. The inlet-velocity-ratio range extended from zero to a maximum value of 1.34. Measurements included pressure distribution, external drag, and total-pressure loss of the internal flow near the inlet. Drag was not measured for the tests at the supersonic Mach number.
Book Synopsis Handbook of Supersonic Aerodynamics by : Johns Hopkins University. Applied Physics Laboratory
Download or read book Handbook of Supersonic Aerodynamics written by Johns Hopkins University. Applied Physics Laboratory and published by . This book was released on 1950 with total page 428 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book NASA SP. written by and published by . This book was released on 1962 with total page 796 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Flight Stability and Automatic Control by : Robert C. Nelson
Download or read book Flight Stability and Automatic Control written by Robert C. Nelson and published by WCB/McGraw-Hill. This book was released on 1998 with total page 441 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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.
Book Synopsis Hypersonic and High Temperature Gas Dynamics by : John David Anderson
Download or read book Hypersonic and High Temperature Gas Dynamics written by John David Anderson and published by AIAA. This book was released on 1989 with total page 710 pages. Available in PDF, EPUB and Kindle. Book excerpt: This book is a self-contained text for those students and readers interested in learning hypersonic flow and high-temperature gas dynamics. It assumes no prior familiarity with either subject on the part of the reader. If you have never studied hypersonic and/or high-temperature gas dynamics before, and if you have never worked extensively in the area, then this book is for you. On the other hand, if you have worked and/or are working in these areas, and you want a cohesive presentation of the fundamentals, a development of important theory and techniques, a discussion of the salient results with emphasis on the physical aspects, and a presentation of modern thinking in these areas, then this book is also for you. In other words, this book is designed for two roles: 1) as an effective classroom text that can be used with ease by the instructor, and understood with ease by the student; and 2) as a viable, professional working tool for engineers, scientists, and managers who have any contact in their jobs with hypersonic and/or high-temperature flow.
Book Synopsis Introduction to Aircraft Flight Mechanics by : Thomas R. Yechout
Download or read book Introduction to Aircraft Flight Mechanics written by Thomas R. Yechout and published by AIAA. This book was released on 2003 with total page 666 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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.
Book Synopsis Airframe & Powerplant Mechanics by :
Download or read book Airframe & Powerplant Mechanics written by and published by . This book was released on 2023 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis AIAA Journal by : American Institute of Aeronautics and Astronautics
Download or read book AIAA Journal written by American Institute of Aeronautics and Astronautics and published by . This book was released on 2006 with total page 1382 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Aeronautical Enginnering: A Cumulative Index to a Continuing Bibliography (supplement 312) by :
Download or read book Aeronautical Enginnering: A Cumulative Index to a Continuing Bibliography (supplement 312) written by and published by . This book was released on 1994 with total page 392 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Facing the Heat Barrier by : T. A. Heppenheimer
Download or read book Facing the Heat Barrier written by T. A. Heppenheimer and published by . This book was released on 2006 with total page 364 pages. Available in PDF, EPUB and Kindle. Book excerpt: Hypersonics is the study of flight at speeds where aerodynamic heating dominates the physics of the problem. Typically this is Mach 5 and higher. Hypersonics is an engineering science with close links to supersonics and engine design. Within this field, many of the most important results have been experimental. The principal facilities have been wind tunnels and related devices, which have produced flows with speeds up to orbital velocity. Why is it important? Hypersonics has had two major applications. The first has been to provide thermal protection during atmospheric entry. Success in this enterprise has supported ballistic-missile nose cones, has returned strategic reconnaissance photos from orbit and astronauts from the Moon, and has even dropped an instrument package into the atmosphere of Jupiter. The last of these approached Jupiter at four times the speed of a lunar mission returning to Earth. Work with re-entry has advanced rapidly because of its obvious importance. The second application has involved high-speed propulsion and has sought to develop the scramjet as an advanced airbreathing ramjet. Scramjets are built to run cool and thereby to achieve near-orbital speeds. They were important during the Strategic Defense Initiative, when a set of these engines was to power the experimental X-30 as a major new launch vehicle. This effort fell short, but the X-43A, carrying a scramjet, has recently flown at Mach 9.65 by using a rocket. Atmospheric entry today is fully mature as an engineering discipline. Still, the Jupiter experience shows that work with its applications continues to reach for new achievements. Studies of scramjets, by contrast, still seek full success, in which such engines can accelerate a vehicle without the use of rockets. Hence, there is much to do in this area as well. For instance, work with computers may soon show just how good scramjets can become. NASA SP-2007-4232
