Dynamic Response of a Mach 2.5 Axisymmetric Inlet with Engine Or Cold Pipe and Utilizing 60 Percent Supersonic Internal Area Contraction
Title | Dynamic Response of a Mach 2.5 Axisymmetric Inlet with Engine Or Cold Pipe and Utilizing 60 Percent Supersonic Internal Area Contraction PDF eBook |
Author | Joseph F. Wasserbauer |
Publisher | |
Pages | 64 |
Release | 1969 |
Genre | Aerodynamics, Supersonic |
ISBN |
Dynamic response of supersonic mixed compression inlet coupled to cold pipe or turbojet engine.
Dynamic Response of a Mach 2.5 Axisymmetric Inlet with Engine Or Cold Pipe and Utilizing 60 Percent Supersonic Internal Area Contraction
Title | Dynamic Response of a Mach 2.5 Axisymmetric Inlet with Engine Or Cold Pipe and Utilizing 60 Percent Supersonic Internal Area Contraction PDF eBook |
Author | Joseph F. Wasserbauer |
Publisher | |
Pages | 58 |
Release | 1969 |
Genre | |
ISBN |
Experimental Investigation of Dynamic Distortion in a Mach 2.50 Inlet with 60 Percent Internal Contraction and Its Effect on Turbojet Stall Margin
Title | Experimental Investigation of Dynamic Distortion in a Mach 2.50 Inlet with 60 Percent Internal Contraction and Its Effect on Turbojet Stall Margin PDF eBook |
Author | James E. Calogeras |
Publisher | |
Pages | 80 |
Release | 1969 |
Genre | |
ISBN |
Terminal-shock and Restart Control of a Mach 2.5, Axisymmetric, Mixed Compression Inlet with 40 Percent Internal Contraction
Title | Terminal-shock and Restart Control of a Mach 2.5, Axisymmetric, Mixed Compression Inlet with 40 Percent Internal Contraction PDF eBook |
Author | Robert J. Baumbick |
Publisher | |
Pages | 24 |
Release | 1974 |
Genre | Aerodynamics, Supersonic |
ISBN |
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.
Dynamic Response of Mach 2.5 Axisymmetric Inlet with 40 Percent Supersonic Internal Area Contraction
Title | Dynamic Response of Mach 2.5 Axisymmetric Inlet with 40 Percent Supersonic Internal Area Contraction PDF eBook |
Author | Robert J. Baumbick |
Publisher | |
Pages | 19 |
Release | 1973 |
Genre | |
ISBN |
Experimental Dynamic Response of a Two-dimensional, Mach 2.7, Mixed-compression Inlet
Title | Experimental Dynamic Response of a Two-dimensional, Mach 2.7, Mixed-compression Inlet PDF eBook |
Author | Robert J. Baumbick |
Publisher | |
Pages | 36 |
Release | 1972 |
Genre | Aerodynamics, Supersonic |
ISBN |
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.
Instantaneous Distortion in a Mach 2.5, 40-percent-internal-contraction Inlet and Its Effect on Turbojet Stall Margin
Title | Instantaneous Distortion in a Mach 2.5, 40-percent-internal-contraction Inlet and Its Effect on Turbojet Stall Margin PDF eBook |
Author | Paul L. Burstadt |
Publisher | |
Pages | 52 |
Release | 1974 |
Genre | Aerodynamics, Supersonic |
ISBN |