Download or read book Performance and Control of a Full scale Axially Symmetric External internal Compression Inlet from Mach 2 0 to 3 0 written by and published by . This book was released on 1961 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Comparisons of In flight F 111A Inlet Performance for On and Off scheduled Inlet Geometry at Mach Numbers of 0 68 to 2 18 written by Richard A. Martin and published by . This book was released on 1971 with total page 52 pages. Available in PDF, EPUB and Kindle. Book excerpt: In-flight F-111 data on total and static pressure from left inlet during automatically scheduled and manually controlled off-schedule positioning of spike at Mach 0.68 to 2.18.

Download or read book Performance of External compression Bump Inlet at Mach Numbers of 1 5 to 2 0 written by Paul C. Simon and published by . This book was released on 1957 with total page 46 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book NASA Technical Note written by and published by . This book was released on 1971 with total page 450 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Monthly Catalog of United States Government Publications written by United States. Superintendent of Documents and published by . This book was released on 1961 with total page 1248 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Monthly Catalog of United States Government Publications Cumulative Index written by United States. Superintendent of Documents and published by . This book was released on 1978 with total page 1300 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Investigation of the Performance and Control of a Mach 3 0 Two dimensional External internal compression Inlet written by and published by . This book was released on 1961 with total page 38 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Performance of External internal Compression Inlet with Abrupt Internal Turning at Mach Numbers 3 0 to 2 0 written by Leonard J. Obery and published by . This book was released on 1957 with total page 21 pages. Available in PDF, EPUB and Kindle. Book excerpt: An inlet with combined external and internal compression, formed by spike and cowl oblique shocks, and an over-all length of 2.5 inlet diameters was investigated at Mach numbers from 3.0 to 2.0 over a range of angles of attack. At the design Mach number of 3.0 the low angle cowl, which turned the flow supersonically, generated two internal shocks and focused them on the centerbody surface. These compression waves, with their high pressure gradient, were cancelled by abrupt centerbody turning. This investigation showed that with proper boundary-layer control on the centerbody this method of internal compression did not adversely affect the high performance of the inlet.

Download or read book Performance of a Mach 3 0 External internal Compression Axisymmetric Inlet at Mach Numbers from 2 0 to 3 5 written by and published by . This book was released on 1960 with total page 26 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book A Comparison of the Performance of Four Side mounted Inlets Over a Mach Number Range of 0 88 to 2 2 and Angles of Attack to 14 written by Leroy L. Presley and published by . This book was released on 1960 with total page 58 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Monthly Catalog of United States Government Publications written by and published by . This book was released on 1951 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Performance Characteristics of a Wing body Combination with a Two dimensional External internal compression Inlet at Mach 3 5 and 3 0 written by and published by . This book was released on 1960 with total page 38 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Performance of a Mach Number 3 0 Design Axisymmetric Double cone External compression Inlet in the Mach Number Range 1 97 to 0 79 written by Owen H. Davis and published by . This book was released on 1960 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Experimental Investigation of a Large scale Two dimensional Mixed compression Inlet System written by Norman D. Wong and published by . This book was released on 1971 with total page 68 pages. Available in PDF, EPUB and Kindle. Book excerpt: A large-scale, variable-geometry inlet model with a design Mach number of 3.0 was tested at Mach numbers from 1.55 to 3.2. Variable features of the inlet for off-design operation are an adjustable-height ramp system and a translating cowl. This report presents experimental results for a diffuser and boundary-layer bleed configuration which was optimized at the design Mach number. Overall performance was high with throat-mounted vortex generators, which were effective in reducing flow distortion in the subsonic diffuser at the higher Mach numbers.

Download or read book Performance of Three Isentropic All Internal Compression Axisymmetric Inlets Designed for Mach 2 5 written by Bernhard H. Anderson and published by . This book was released on 1960 with total page 34 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Computational Parametric Study of Sidewall compression Scramjet Inlet Performance at Mach 10 written by Scott D. Holland and published by . This book was released on 1993 with total page 20 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Aerodynamic Design of a Dual Flow Mach 7 Hypersonic Inlet System for a Turbine Based Combined Cycle Hypersonic Propulsion System written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-05-22 with total page 90 pages. Available in PDF, EPUB and Kindle. Book excerpt: A new hypersonic inlet for a turbine-based combined-cycle (TBCC) engine has been designed. This split-flow inlet is designed to provide flow to an over-under propulsion system with turbofan and dual-mode scramjet engines for flight from takeoff to Mach 7. It utilizes a variable-geometry ramp, high-speed cowl lip rotation, and a rotating low-speed cowl that serves as a splitter to divide the flow between the low-speed turbofan and the high-speed scramjet and to isolate the turbofan at high Mach numbers. The low-speed inlet was designed for Mach 4, the maximum mode transition Mach number. Integration of the Mach 4 inlet into the Mach 7 inlet imposed significant constraints on the low-speed inlet design, including a large amount of internal compression. The inlet design was used to develop mechanical designs for two inlet mode transition test models: small-scale (IMX) and large-scale (LIMX) research models. The large-scale model is designed to facilitate multi-phase testing including inlet mode transition and inlet performance assessment, controls development, and integrated systems testing with turbofan and scramjet engines. Sanders, Bobby W. and Weir, Lois J. Glenn Research Center SUPERSONIC COMBUSTION RAMJET ENGINES; HYPERSONIC INLETS; ENGINE INLETS; CONTROL SYSTEMS DESIGN; HYPERSONIC FLIGHT; SUPERSONIC SPEED; TURBOFAN ENGINES; TWO PHASE FLOW; PERFORMANCE TESTS