Measurements of supersonic wing tip vortices

Michael K. Smart; Iraj M. Kalkhoran; James Bentson

doi:10.2514/3.12725

Measurements of supersonic wing tip vortices

Michael K. Smart, Iraj M. Kalkhoran, James Bentson

Mechanical and Aerospace Engineering

Research output: Contribution to journal › Article › peer-review

Abstract

An experimental study of supersonic wing tip vortices has been conducted at Mach 2.49 using small-scale fourhole and five-hole conical probes. The study was performed 2.25 chords downstream of a semispan rectangular wing at angles of attack of 5.7 and 10.4 deg. The main objective of the experiments was to determine the Mach number, flow angularity, and total pressure distribution in the core region of supersonic wing tip vortices. A secondary aim was to demonstrate the feasibility of calibrating a conical probe using a computational solution to predict the flow characteristics. Results of the present investigation showed that the numerically generated calibration data can be used for pointed nose four-hole conical probes but were not sufficiently accurate for conventional five-hole probes due to nose bluntness effects. A combination of four-hole conical probe measurements with independent pitot pressure measurements indicated a significant Mach number and total pressure deficit in the core regions of supersonic wing tip vortices, combined with an asymmetric Burger-like" swirl distribution.

Original language	English (US)
Pages (from-to)	1761-1768
Number of pages	8
Journal	AIAA journal
Volume	33
Issue number	10
DOIs	https://doi.org/10.2514/3.12725
State	Published - Oct 1995

ASJC Scopus subject areas

Aerospace Engineering

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10.2514/3.12725

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@article{34062a188fc0452e8abc113978ecdd30,

title = "Measurements of supersonic wing tip vortices",

abstract = "An experimental study of supersonic wing tip vortices has been conducted at Mach 2.49 using small-scale fourhole and five-hole conical probes. The study was performed 2.25 chords downstream of a semispan rectangular wing at angles of attack of 5.7 and 10.4 deg. The main objective of the experiments was to determine the Mach number, flow angularity, and total pressure distribution in the core region of supersonic wing tip vortices. A secondary aim was to demonstrate the feasibility of calibrating a conical probe using a computational solution to predict the flow characteristics. Results of the present investigation showed that the numerically generated calibration data can be used for pointed nose four-hole conical probes but were not sufficiently accurate for conventional five-hole probes due to nose bluntness effects. A combination of four-hole conical probe measurements with independent pitot pressure measurements indicated a significant Mach number and total pressure deficit in the core regions of supersonic wing tip vortices, combined with an asymmetric Burger-like{"} swirl distribution.",

author = "Smart, {Michael K.} and Kalkhoran, {Iraj M.} and James Bentson",

note = "Funding Information: This work was supported by the Air Force Office of Scientific Research under Grant F49620-93-1-0009 and by NASA Lewis Research Center under Grant NAGS-1378. Computing resources were provided by the Pittsburgh Supercomputing Center. The authors are grateful to Frank Marconi for providing the computer code used to generate the calibration curves. The assistance of Lester Orlick, Kuo-Kuang Liu,and Joe Zammit was greatly appreciated during the work. Many useful discussions with Donald P. Rizzetta are acknowledged with appreciation.",

year = "1995",

month = oct,

doi = "10.2514/3.12725",

language = "English (US)",

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AU - Bentson, James

N1 - Funding Information: This work was supported by the Air Force Office of Scientific Research under Grant F49620-93-1-0009 and by NASA Lewis Research Center under Grant NAGS-1378. Computing resources were provided by the Pittsburgh Supercomputing Center. The authors are grateful to Frank Marconi for providing the computer code used to generate the calibration curves. The assistance of Lester Orlick, Kuo-Kuang Liu,and Joe Zammit was greatly appreciated during the work. Many useful discussions with Donald P. Rizzetta are acknowledged with appreciation.

PY - 1995/10

Y1 - 1995/10

N2 - An experimental study of supersonic wing tip vortices has been conducted at Mach 2.49 using small-scale fourhole and five-hole conical probes. The study was performed 2.25 chords downstream of a semispan rectangular wing at angles of attack of 5.7 and 10.4 deg. The main objective of the experiments was to determine the Mach number, flow angularity, and total pressure distribution in the core region of supersonic wing tip vortices. A secondary aim was to demonstrate the feasibility of calibrating a conical probe using a computational solution to predict the flow characteristics. Results of the present investigation showed that the numerically generated calibration data can be used for pointed nose four-hole conical probes but were not sufficiently accurate for conventional five-hole probes due to nose bluntness effects. A combination of four-hole conical probe measurements with independent pitot pressure measurements indicated a significant Mach number and total pressure deficit in the core regions of supersonic wing tip vortices, combined with an asymmetric Burger-like" swirl distribution.

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Measurements of supersonic wing tip vortices

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