Viscous interaction effects on a static pressure probe at m equals 6

Behrens, Wilhelm

doi:10.2514/3.2193

Cited by 19 publications

(2 citation statements)

References 0 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…The Pitot probe used was a standard square-ended probe, approximately 0.2 mm in outside diameter, of the type calibrated by Matthews (1958). The static pressure probe was a slender ( I mm diameter) cone cylinder, identical in shape to the probe extensively calibrated by Behrens (1963). If the stagnation temperature in the jet is assumed constant, then the two pressure measurements are all that is needed for a complete determination of the local mean flow properties.…”

Section: Description Of the Experimentsmentioning

confidence: 99%

Experiments on the instability waves in a supersonic jet and their acoustic radiation

1975

View full text Add to dashboard Cite

An experimental investigation of the instability and the acoustic radiation of the low Reynolds number axisymmetric supersonic jet has been performed. Hot-wire measurements in the flow field and microphone measurements in the acoustic field were obtained from different size jets at Mach numbers of about 2. The Reynolds number ranged from 8000 to 107000, which contrasts with a Reynolds number of 1·3 × 106for similar jets exhausting into atmospheric pressure.Hot-wire measurements indicate that the instability process in the perfectly expanded jet consists of numerous discrete frequency modes around a Strouhal number of 0·18. The waves grow almost exponentially and propagate downstream at a supersonic velocity with respect to the surrounding air. Measurements of the wavelength and wave speed of theSt= 0·18 oscillation agree closely with Tam's theoretical predictions.Microphone measurements have shown that the wavelength, wave orientation and frequency of the acoustic radiation generated by the dominant instability agree with the Mach wave concept. The sound pressure levels measured in the low Reynolds number jet extrapolate to values approaching the noise levels measured by other experimenters in high Reynolds number jets. These measurements provide more evidence that the dominant noise generation mechanism in high Reynolds number jets is the large-scale instability.

show abstract

Section: Description Of the Experimentsmentioning

confidence: 99%

Experiments on the instability waves in a supersonic jet and their acoustic radiation

1975

View full text Add to dashboard Cite

show abstract

“…The conical-tipped probe used in the far wake was identical to that designed and calibrated by Behrens. 35 Although this probe was used for the majority of the static pressure measurements, its tip to orifice length prevented taking measurements near the base of a model, and additional probes were required to obtain data near the base of the larger wedge model. These probes, three in number, consisted of 2-in.…”

Section: Test Apparatus and Experimental Techniquesmentioning

confidence: 99%

Experimental investigation of far wakes behind two-dimensional slender bodies at M sub infinity equals 6

Batt

Kubota

1969

AIAA Journal

View full text Add to dashboard Cite

An experimental investigation has been conducted at M^ = 6 to determine mean flow properties for far wakes behind several two-dimensional slender bodies at zero angle of attack. The adiabatic wall configurations tested included a flat-plate model and two 20° wedge models which differed by a factor of two in base height. The effect of wall temperature was examined by cooling the larger wedge model to a temperature of about two tenths of the freestream stagnation temperature. Freestream Reynolds numbers were varied from 50,000 to 200,000 per in. for each of these four configurations. Profile measurements of total temperature and Pitot pressure were combined with centerline static pressures to determine completely the far-wake flowfield from the wake neck downstream to the linear far wake. The effect of transition on mean flow properties was determined. Comparison of laminar wake data for adiabatic wall models with linear wake theory was favorable. Maximum centerline pressures in the far wake for all configurations were generally 10% higher than the freestream pressure. For the cold wall wedge the maximum centerline enthalpy for all cases occurred two base heights downstream of the model base and was triple the magnitude of the freestream enthalpy. The decay rate of enthalpy was "small" when the far wake was laminar.

show abstract

Free-stream static pressure measurements in the Longshot hypersonic wind tunnel and sensitivity analysis

et al. 2016

View full text Add to dashboard Cite

Viscous interaction effects on a static pressure probe at m equals 6

Cited by 19 publications

References 0 publications

Experiments on the instability waves in a supersonic jet and their acoustic radiation

Experiments on the instability waves in a supersonic jet and their acoustic radiation

Experimental investigation of far wakes behind two-dimensional slender bodies at M sub infinity equals 6

Free-stream static pressure measurements in the Longshot hypersonic wind tunnel and sensitivity analysis

Contact Info

Product

Resources

About