Energy Efficient Active Control of the Flow Past Aircraft Wings

Energy Efficient Active Control of the Flow Past Aircraft Wings

Článek recenzovaný mimo WoS a Scopus

cs

Numerical simulations of the flow past a NACA 0015 wing with active control have been performed. The Reynolds number of the flow is 2.5 x 106. The configuration proposed in this study does not follow the conventional active control methodology past wings. Large blowing surfaces and low jet velocity magnitudes are considered and the energy efficiency of such configuration is examined for a number of variants. One major impact on the flow is the diffusion of the tip vortex core in the trailing edge area, but also farther downstream. Strategies for drag reduction and lift increase of the wing are proposed by varying some of the actuation parameters. The present active flow control could be efficient at all angles of attack, while in the same time could be able to reduce significantly the total drag of the wing, increase the total lift or combine effectively those favorable effects for better flight performance. Maximum drag decrease could exceed 40% of the total drag at low angles of attack, with still positive energy income.

Numerical simulations of the flow past a NACA 0015 wing with active control have been performed. The Reynolds number of the flow is 2.5 x 106. The configuration proposed in this study does not follow the conventional active control methodology past wings. Large blowing surfaces and low jet velocity magnitudes are considered and the energy efficiency of such configuration is examined for a number of variants. One major impact on the flow is the diffusion of the tip vortex core in the trailing edge area, but also farther downstream. Strategies for drag reduction and lift increase of the wing are proposed by varying some of the actuation parameters. The present active flow control could be efficient at all angles of attack, while in the same time could be able to reduce significantly the total drag of the wing, increase the total lift or combine effectively those favorable effects for better flight performance. Maximum drag decrease could exceed 40% of the total drag at low angles of attack, with still positive energy income.

active flow control; control surfaces; high Reynolds; wing; blowing; drag reduction

active flow control; control surfaces; high Reynolds; wing; blowing; drag reduction

2012-10-19

VUT v Brně

VUT v Brně

1425-2104

RESEARCH BULLETIN

2012

22

1–22

22