Author: Raymond J. ComenzoPublisher:
ISBN:
Category : Jet engines
Languages : en
Pages : 24
Book Description
Effect of Yaw and Angle of Attack on Pressure Recovery and Mass-flow Characteristics of a Rectangular Supersonic Scoop Inlet at a Mach Number of 2.71
Author: Raymond J. ComenzoPublisher:
ISBN:
Category : Jet engines
Languages : en
Pages : 24
Book Description
The Performance of Conical Supersonic Scoop Inlets on Circular Fuselages
Author: Lowell E. HaselPublisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 16
Book Description
Wind Tunnel Tests of Supersonic Two-dimensional and Half-axisymmetric Inlet Models in a Nonuniform Flow Field at Mach Numbers from 1.5 Through 2.5
Author: Frederick K. HubePublisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 274
Book Description
High Angle of Incidence Implications Upon Air Intake Design and Location for Supersonic Cruise Aircraft and Highly Maneuverable Transonic Aircraft
Author: Starting Phenomena for Hypersonic Inlets with Thick Turbulent Boundary Layers at Mach 6
Author: Theodore J. GoldbergPublisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 68
Book Description
Performance of a Mach Number 3.0 Design Axisymmetric Double-cone External-compression Inlet in the Mach Number Range 1.97 to 0.79
Author: Owen H. DavisPublisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 36
Book Description
Inlet Sensitivity Study for a Supersonic Transport
Author: Robert W. KoenigPublisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 40
Book Description
Some Internal-flow Characteristics at Zero Flight Speed of an Annular Supersonic Inlet and an Open-nose Inlet with Sharp and Rounded Lips
Author: Joseph R. MililloPublisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 30
Book Description
Static tests of an annular conical-shock inlet and an open-nose conical inlet with three lip shapes were conducted at the Langley 8-foot transonic tunnel. Measurements of pressure recovery, surface pressure, and total pressure were made through a mass-flow range extending to choking. The results indicate that the two inlets with thin sharp lips had about the same relatively poor pressure-recovery characteristics and choked at a mass-flow rate of about 78 percent of the theoretical maximum. However, both the pressure recovery and choking mass-flow rate were greatly improved by replacing the sharp lip by two alternate shapes with lip roundness and internal contraction just behind the inlet lip.
Distributed Porous Throat Stability Bypass to Increase the Stable Airflow Range of a Mach 2.5 Inlet with 60 Percent Internal Contraction
Author: Robert Joseph ShawPublisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 52
Book Description
The results of an experimental investigation to increase the stable airflow operating range of a supersonic, mixed-compression inlet with 60-percent internal contraction are presented. Various distributed-porous, throat stability-bypass entrance configurations were tested. In terms of diffuser-exit corrected airflow, a large inlet stable airflow range of about 25 percent was obtained with the optimum configuration if a constant pressure was maintained in the by-pass plenum. The location of the centerbody bleed region had a decided effect on the overall inlet performance. Limited unstart angle-of-attack data are presented.
Investigation of a Mixed Compression Axisymmetric Inlet at Mach Number 5.3
Author: Eldon A. LathamPublisher:
ISBN:
Category : Axial flow
Languages : en
Pages : 44
Book Description