Author: Joseph F. WasserbauerPublisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 64
Book Description
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
Author: Joseph F. WasserbauerPublisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 64
Book Description
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
Author: Joseph F. WasserbauerPublisher:
ISBN:
Category :
Languages : en
Pages : 58
Book Description
NASA Technical Note
Author: Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1016
Book Description
Dynamic Response of Mach 2.5 Axisymmetric Inlet with 40 Percent Supersonic Internal Area Contraction
Author: Robert J. BaumbickPublisher:
ISBN:
Category :
Languages : en
Pages : 19
Book Description
Scientific and Technical Aerospace Reports
Author: Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 388
Book Description
Restart and High Response Terminal Shock Control for an Axisymmetric Mixed-compression Inlet with 60-percent Internal Contraction
Author: Michael J. CrosbyPublisher:
ISBN:
Category :
Languages : en
Pages : 24
Book Description
NASA Scientific and Technical Reports
Author: United States. National Aeronautics and Space Administration Scientific and Technical Information DivisionPublisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 966
Book Description
Experimental Dynamic Response of a Two-dimensional, Mach 2.7, Mixed-compression Inlet
Author: Robert J. BaumbickPublisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 36
Book Description
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.
NASA Scientific and Technical Reports and Publications for 1969 - A Selected Listing
Author: United States. National Aeronautics and Space Administration. Scientific and Technical Information DivisionPublisher:
ISBN:
Category : Science
Languages : en
Pages : 956
Book Description
A Selected Listing of NASA Scientific and Technical Reports
Author: United States. National Aeronautics and Space Administration. Scientific and Technical Information DivisionPublisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 962
Book Description
