Author: Shimer Zane PinckneyPublisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 44
Book Description
A Short Static-pressure Probe Design for Supersonic Flow
Author: Shimer Zane PinckneyPublisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 44
Book Description
Pressure Probe Designs for Dynamic Pressure Measurements in a Supersonic Flow Field
Author: PRESSURE PROBE DESIGNS FOR DYNAMIC PRESSURE MEASUREMENTS IN A SUPERSONIC FLOW FIELD... NASA/TM-2001-211096... DEC. 6, 2001
Author: A Short Static Probe with Good Incidence Characteristics at Supersonic Speed
Author: I. S. DonaldsonPublisher:
ISBN:
Category :
Languages : en
Pages : 17
Book Description
Tests carried out on a short static probe at supersonic speeds between Mach numbers of 1.1 and 2.5 are described. The probe consists of a 50 deg included angle cone-cylinder having sensing holes 0.88 calibres aft of the cone-cylinder junction. The tests show that at zero incidence the probe measures a pressure (approximately independent of Mach number) of 0.793 times the local static pressure. They also show that, at up to 18 deg incidence in any pitch plane, the pressure measured is 0.763 plus or minus 0.03 times the local static pressure. For a limited Mach number range near a Mach number of 1.6, this accuracy can be maintained to incidences over 30 deg. Of particular interest is the fact that relatively small internal differences between externally identical probes appear to have a significant effect on the incidence characteristics and in some respects can improve the performance. (Author).
NASA Technical Note
Author: Needle Static-pressure Probes Insensitive to Flow Inclination in Supersonic Air Streams
Author: L. W. WALTEREvaluation of Probes for Measuring Static Pressure in Supersonic and Hypersonic Flows
Author: J. Don GrayPublisher:
ISBN:
Category :
Languages : en
Pages : 43
Book Description
Pertinent facts in the literature have been examined regarding the aerodynamic characteristics of static-pressure measuring probes in order to assess the relative merits and limitations of cone-cylinder, sharp-cone, and planar (disk) probles. The effects of Mach number, angle of attack, orifice location, and Reynolds number on the inferred local pressures were all evaluated at Mach numbers up to 8. It is concluded that the planar probe and sharp-cone probe (if properly designed) are equally more accurate than the cone-cylinder probe at supersonic and hypersonic speeds. However, the cone-cylinder is judged to be superior for use at Mach numbers below 4. Details of a recommedned procedure to correct for the effects of viscous interaction (all probes) and angle of attack (planar probes only) are included. (Author).
NASA Technical Paper
Author: Investigation of Axially Symmetric and Two-dimensional Multinozzles for Producing Supersonic Streams
Author: Eli ReshotkoPublisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 42
Book Description
Mach 6 Flow Field Surveys Beneath the Forebody of an Airbreathing Missile
Author: Patrick J. JohnstonPublisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 160
Book Description