Wind Tunnel Pressure Measuring Techniques

Bynum, D S; Ledford, R. L.; Smotherman, W. E.

doi:10.21236/ad0714565

Cited by 7 publications

(2 citation statements)

References 11 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…The transducers were calibrated using a deadweight tester. 31 The data were recorded and stored by means of a high-speed data acquisition system (National Instruments P CI − 6251), via a signal conditioner (National Instruments SCXI − 1520). The system had the capability of collecting data at a frequency up to 50 kHz.…”

Section: Methodsmentioning

confidence: 99%

Compressible Flow Structures Interaction with a Two-Dimensional Ejector: A Cold-Flow Study

Zare‐Behtash

Kontis

2009

Journal of Propulsion and Power

View full text Add to dashboard Cite

An experimental study has been conducted to examine the interaction of compressible flow structures such as shocks and vortices with a 2-D ejector geometry using a shock tube facility.Three diaphragm pressure ratios of P 4 /P 1 = 4, 8, and 12 have been employed, where P 4 is the driver gas pressure and P 1 is the pressure within the driven compartment of the shock tube. These lead to incident shock Mach numbers of M s = 1.34, 1.54, and 1.66, respectively. The length of the driver section of the shock tube was 700 mm. Air was used for both the driver and driven gases.

show abstract

Section: Methodsmentioning

confidence: 99%

Compressible Flow Structures Interaction with a Two-Dimensional Ejector: A Cold-Flow Study

Zare‐Behtash

Kontis

2009

Journal of Propulsion and Power

View full text Add to dashboard Cite

show abstract

“…The time lag in the tubing is due to the viscosity, elasticity, mass of the air enclosed in the tube, inertia, material of which the tube is made and the condition of the inside surface of the tube. The lag due to the viscosity and elasticity of the air depends chiefly on the length and diameter of the tube and the time rate of change of the initial pressure (22,23) . All of the tubes that were used in this investigation have the same length and diameter.…”

Section: Experimental Set-upmentioning

confidence: 99%

Experimental investigation of flowfield over an iced aerofoil

Manshadi¹,

Esfeh

2016

Aeronaut. j.

View full text Add to dashboard Cite

Wind-tunnel measurements were used to study the characteristics of the unsteady separation bubbles on a NACA 0015 aerofoil with simulated two-dimensional leading-edge glaze ice accretions. The unsteadiness present in the iced-aerofoil flowfield was determined using measurements of the time-dependent aerofoil surface pressure distribution at Reynolds number of 1.0 × 106. Additionally, the unsteady flow features were investigated through the power spectrum of the stream-wise velocity fluctuations using a hot-wire anemometry. The results showed that the highest value of root-mean-square fluctuation of the surface pressure consistently occurred upstream of the mean shear-layer reattachment location. Spectral analysis of stream-wise velocity fluctuations near reattachment location revealed evidence of the regular frequency at Strouhal numbers of 0.5-0.63. Moreover, the low-frequency oscillations associated with shear-layer flapping was also identified in the wake velocity spectra on the order of 10 Hz that resulted in Strouhal numbers of 0.0186-021.

show abstract

Fundamentals of Flow Field Measurement Techniques

Weyer¹

1985

Thermodynamics and Fluid Mechanics of Turbomachinery

View full text Add to dashboard Cite

Wind Tunnel Pressure Measuring Techniques

Abstract: This document has been approved for public release and sale; its distribution is unlimited.

Cited by 7 publications

References 11 publications

Compressible Flow Structures Interaction with a Two-Dimensional Ejector: A Cold-Flow Study

Compressible Flow Structures Interaction with a Two-Dimensional Ejector: A Cold-Flow Study

Experimental investigation of flowfield over an iced aerofoil

Fundamentals of Flow Field Measurement Techniques

Contact Info

Product

Resources

About