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Hypersonic control flap effectiveness

Published online by Cambridge University Press:  04 July 2016

D. Kumar  and
J. L. Stollery
D. Kumar
Affiliation:
College of Aeronautics, Cranfield University, Cranfield, UK
J. L. Stollery
Affiliation:
College of Aeronautics, Cranfield University, Cranfield, UK
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Summary

The effects of flap deflection, configuration incidence and leading edge bluntness on boundary layer separation and transition have been studied experimentally. A quasi two-dimensional flat plate equipped with a full span trailing edge control flap has been employed for these tests.

The studies have been carried out in a hypersonic gun tunnel at M∞ = 8·2 and Re∞/cm = 9·0 × 104. The flap deflection angles studied were in the range 0° ≤ β ≤ 30°. The incidence range was from zero to α = 10° (positive α is nose down). Leading edge bluntness effects were simulated by the introduction of a hemi-cylindrical leading edge.

The flow structure was studied using high speed Schlieren photography as well as surface pressure and heat transfer measurements. Liquid crystals were employed to study the threedimensionality of the flow structure for selected configurations. Analytical theories have been developed to estimate the flap pressure and heat transfer levels for the sharp and blunt configurations. These are compared against experimental measurements.

Type
Research Article
Information
The Aeronautical Journal , Volume 100 , Issue 996 , July 1996 , pp. 197 - 208
Copyright
Copyright © Royal Aeronautical Society 1996 

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