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Book Results of a 0 2 scale B 1 Inlet Verification Model Test at Transonic and Supersonic Mach Numbers

Download or read book Results of a 0 2 scale B 1 Inlet Verification Model Test at Transonic and Supersonic Mach Numbers written by John F. Riddell and published by . This book was released on 1972 with total page 250 pages. Available in PDF, EPUB and Kindle. Book excerpt: Results are presented of a wind tunnel investigation of a 0.2-scale model of the left-hand dual-inlet air induction system of the B-1 aircraft. The test was conducted at Mach numbers from 0.55 to 2.3 over an angle-of-attack range from -2 to 13 deg and yaw angles of -6 to 6 deg. Inlet performance in terms of compressor-face total-pressure recovery, total-pressure distortion and turbulence index is presented as a function of engine-face mass-flow ratio for various inlet geometries and model attitudes. Generally, increasing angle of attack caused greated decreases in the performance of the inboard inlet at supersonic Mach numbers and of the outboard inlet at subsonic Mach numbers. Noticeable effects occurred when the structural mode control vanes were varied at the subsonic Mach number at low angles of attack and at negative yaw. (Author).

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

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 34 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Book Investigation of a Mixed Compression Axisymmetric Inlet at Mach Number 5 3

Download or read book Investigation of a Mixed Compression Axisymmetric Inlet at Mach Number 5 3 written by Eldon A. Latham and published by . This book was released on 1972 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Book Performance Summary and Analysis of a Mach 3 0 Design Axisymmetric All external compression Double cone Inlet Mach Number Range 3 0 to 0 8

Download or read book Performance Summary and Analysis of a Mach 3 0 Design Axisymmetric All external compression Double cone Inlet Mach Number Range 3 0 to 0 8 written by John L. Allen and published by . This book was released on 1960 with total page 24 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Book Tests of a Small scale NACA Submerged Inlet at Transonic Mach Numbers

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 Experimental Dynamic Response of a Two dimensional Mach 2 7 Mixed compression Inlet

Download or read book Experimental Dynamic Response of a Two dimensional Mach 2 7 Mixed compression Inlet written by Robert J. Baumbick and published by . This book was released on 1972 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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.

Book Results of a 0 2 Scale B 1 Inlet Verification Model Test at Transonic and Supersonic Mach Numbers

Download or read book Results of a 0 2 Scale B 1 Inlet Verification Model Test at Transonic and Supersonic Mach Numbers written by and published by . This book was released on 1972 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: Results are presented of a wind tunnel investigation of a 0.2-scale model of the left-hand dual-inlet air induction system of the B-1 aircraft. The test was conducted at Mach numbers from 0.55 to 2.3 over an angle-of-attack range from -2 to 13 deg and yaw angles of -6 to 6 deg. Inlet performance in terms of compressor-face total-pressure recovery, total-pressure distortion and turbulence index is presented as a function of engine-face mass-flow ratio for various inlet geometries and model attitudes. Generally, increasing angle of attack caused greated decreases in the performance of the inboard inlet at supersonic Mach numbers and of the outboard inlet at subsonic Mach numbers. Noticeable effects occurred when the structural mode control vanes were varied at the subsonic Mach number at low angles of attack and at negative yaw. (Author).

Book Monthly Catalog of United States Government Publications Cumulative Index

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 1976 with total page 1408 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Book Terminal shock and Restart Control of a Mach 2 5 Axisymmetric Mixed Compression Inlet with 40 Percent Internal Contraction

Download or read book Terminal shock and Restart Control of a Mach 2 5 Axisymmetric Mixed Compression Inlet with 40 Percent Internal Contraction written by Robert J. Baumbick and published by . This book was released on 1974 with total page 24 pages. Available in PDF, EPUB and Kindle. Book excerpt: Results of experimental tests conducted on a supersonic, mixed-compression, axisymmetric inlet are presented. The inlet is designed for operation at Mach 2.5 with a turbofan engine (TF-30). The inlet was coupled to either a choked orifice plate or a long duct which had a variable-area choked exit plug. Closed-loop frequency responses of selected diffuser static pressures used in the terminal-shock control system are presented. Results are shown for Mach 2.5 conditions with the inlet coupled to either the choked orifice plate or the long duct. Inlet unstart-restart traces are also presented. High-response inlet bypass doors were used to generate an internal disturbance and also to achieve terminal-shock control.

Book Aerodynamic and acoustic performance of high Mach number inlets

Download or read book Aerodynamic and acoustic performance of high Mach number inlets written by and published by . This book was released on 1977 with total page 84 pages. Available in PDF, EPUB and Kindle. Book excerpt: