![External Interference Effects of Flow Through Static-pressure Orifices of Airspeed Head at Several Supersonic Mach Numbers and Angles of Attack [with List of References] PDF](https://books.google.com/books/content/images/frontcover/GS5oQwAACAAJ?fife=w150-h200)
Author: Publisher:
ISBN:
Category : Air-speed indicators
Languages : en
Pages : 14
Book Description
External Interference Effects of Flow Through Static-pressure Orifices of Airspeed Head at Several Supersonic Mach Numbers and Angles of Attack [with List of References]
![External Interference Effects of Flow Through Static-pressure Orifices of Airspeed Head at Several Supersonic Mach Numbers and Angles of Attack [with List of References] PDF](https://books.google.com/books/content/images/frontcover/GS5oQwAACAAJ?fife=w80-h100)
Author: Monthly Catalog of United States Government Publications
Author: United States. Superintendent of DocumentsPublisher:
ISBN:
Category : Government publications
Languages : en
Pages : 1714
Book Description
February issue includes Appendix entitled Directory of United States Government periodicals and subscription publications; September issue includes List of depository libraries; June and December issues include semiannual index.
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
Aerodynamic Interference Effects Caused by Parallel-staged Simple Aerodynamic Configurations at Mach Numbers of 3 and 6
Author: John P. DeckerPublisher:
ISBN:
Category : Launch vehicles (Astronautics)
Languages : en
Pages : 92
Book Description
Aerodynamic characteristics effected by parallel- staged simple aerodynamic configurations at Mach numbers of 3 and 6.
Interference Effects Due to Relative Proximity of Static-pressure Probes in Supersonic Flow
Author: J. L. LindseyPublisher:
ISBN:
Category :
Languages : en
Pages : 53
Book Description
An experimental investigation was conducted in a supersonic wind tunnel to determine the minimum critical spacing for no mutual interference of two cone-cylinder-type static-pressure probes designed for simultaneous pressure measurement in supersonic flow. Tests made over a Mach Number range of approximately 1.9 through 3.4 indicate that the minimum critical spacing is predominately a function of Mach Number and static-orifice location. Probe cone-angle and probe diameter variations produce minor effects. A theoretical study of static-orifice location was also made. Results indicate that the generally recommended position of six to ten probe diameters aft of the cone shoulder is suitable for pressure measurement at Mach Numbers as high as approximately 3.5; however, higher velocities require static-orifice locations at greater distances from the cone shoulder. (Author).
Jet Effects on Cylindrical Afterbodies Housing Sonic and Supersonic Nozzles which Exhaust Against a Supersonic Stream at Angles of Attack from 90 ̊to 180 ̊
Author: Lovick O. HaymanPublisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 54
Book Description
Surface Flow Angles on an Ogive Cylinder at Angle of Attack in Supersonic Flow
Author: Harold R. VaughnPublisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 40
Book Description
The surface flow angle was measured on an ogive cylinder at angles of attack and at supersonic Mach numbers. The results are compared with potential theory which is shown to be inadequate unitl modified.
Local Flow Measurement at the Inlet Spike Tip of a Mach 3 Supersonic Cruise Airplane
Author: Harold J. JohnsonJet effects on annular base pressure and temperature in a supersonic stream
Author: Milton A. BeheimPublisher:
ISBN:
Category : Gases at high temperatures
Languages : en
Pages : 52
Book Description
Interaction of a Side Jet with a Supersonic Main Stream
Author: Clarence Albert PiercePublisher:
ISBN:
Category :
Languages : en
Pages : 49
Book Description
An experimental investigation was conducted in the University of Michigan Supersonic Wind Tunnel to explore the main characteristics of the flow and pressure field generated by a supersonic jet directed at 90 deg to the body into the 1.90-Mach-number tunnel stream. In particular, a study was made of the spreading characteristics of the jet and its gross effect on the normal fore, drag, and moment of the cone-cylinder body, from which the jet issued. The phenomenon was investigated as a function of the pressure ratio, P sub o/P sub s (jet stagnation pressure to tunnel static pressure), angle of attack of the body, and jet-nozzle geometry. Within a relatively short distance from the exit, the normal jet was turned in the direction parallel to the free stream even at pressure ratios of over 50. Simultaneously, it spread in all directions, mixing violently with the free stream. Optical evidence suggests that fringes of the jet are in contact with the cylinder. This may have practical implications for the use of hot side-control jets on bodies. The interaction resulted in regions of both high and low pressure over the body. The normal force on the body was decreased below the nominal jet side-thrust value, and the drag was increased above the no-jet value. A moment which depends on the geometry, particularly the length of the body, was generated about the nominal center of gravity of the body.