A quantitative comparison of leading-edge vortices in incompressible and supersonic flows

Wang, F. Y.; Milanovic, I. M.; Zaman, K. B. M. Q.; United States. National Aeronautics and Space Administration; John A. Volpe National Transportation Systems Center (U.S.)

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A quantitative comparison of leading-edge vortices in incompressible and supersonic flows

2002-01-14
By Wang, F. Y. ; Milanovic, I. M. ; Zaman, K. B. M. Q.

[PDF-1.08 MB]

English

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Alternative Title:

40th AIAA Aerospace Science Meeting & Exhibit, January 14-17, 2002, Reno, NV.
Creators:

Wang, F. Y. ; Milanovic, I. M. ; Zaman, K. B. M. Q.

Wang, F. Y. ; Milanovic, I. M. ; Zaman, K. B. M. Q. Less -
Corporate Creators:

United States. National Aeronautics and Space Administration ; John A. Volpe National Transportation Systems Center (U.S.)

United States. National Aeronautics and Space Administration ; John A. Volpe National Transportation Systems Center (U.S.) Less -
Subject/TRT Terms:

[+]

Angles Of Attack Delta-wing Vortices Flow Flow Characteristics Mathematical Analysis Pressure Sensors Supersonic Flow Vortices Wakes Wake Vortices
Resource Type:

Proceedings
Geographical Coverage:

United States
Corporate Publisher:

American Institute of Aeronautics and Astronautics
Abstract:

When requiring quantitative data on delta-wing vortices for design purposes, low-speed results have often been extrapolated to configurations intended for supersonic operation. This practice stems from a lack of database owing to difficulties that plague measurement techniques in high-speed flows. In the present paper an attempt is made to examine this practice by comparing quantitative data on the nearwake properties of such vortices in incompressible and supersonic flows. The incompressible flow data are obtained in experiments conducted in a low-speed wind tunnel. Detailed flow-field properties, including vorticity and turbulence characteristics, obtained by hot-wire and pressure probe surveys are documented. These data are compared, wherever possible, with available data from a past work for a Mach 2.49 flow for the same wing geometry and angles-of-attack. The results indicate that quantitative similarities exist in the distributions of total pressure and swirl velocity. However, the streamwise velocity of the core exhibits different trends. The axial flow characteristics of the vortices in the two regimes are examined, and a candidate theory is discussed.
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PDF
Collection(s):

Volpe Center
Main Document Checksum:

[+]

urn:sha256:107e644392cf72e08c6cac505392fc16fd6677a52cc9a77f3b07bee67b2da52c
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https://rosap.ntl.bts.gov/view/dot/9651/dot_9651_DS1.pdf
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A quantitative comparison of leading-edge vortices in incompressible and supersonic flows

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