Flow phenomena and separation over delta wings with trailing-edge flaps at Mach 6.

Keyes, J. W.; Whitehead, A. H.

doi:10.2514/3.4998

Cited by 28 publications

(3 citation statements)

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“…Although the body will come into the aerodynamic shadow at α = 6.5 • , it can be seen from figure 13 that, even at α = 12 • , the normal force experienced by the wing plus body is less than that of the plain wing by 8%. This clearly demonstrates that, as inferred by Whitehead and Keyes [3], the leeward vortices generate a high pressure region in the re-attachment zone over the bodies. Therefore, it is obvious that the assumption made by the previous investigators that the lee-side body does not affect the force data once they come into the aerodynamic shadow region is not valid.…”

Section: Interference Of Lee-side Bodiessupporting

confidence: 73%

“…A considerable amount of work has been done by many investigators [1][2][3][4][5][6] wanting to understand the complex flow phenomena occurring on the lee side of delta wings at hypersonic speeds. These investigators have performed flow visualization, pressure and heat transfer measurements.…”

Section: Introductionmentioning

confidence: 99%

“…From these measurements it has become clear that the flow on the leeward side of a delta wing is dominated by vortices and the re-attaching flow generates a high shear region. Whitehead and Keyes [3] have studied flow over a 70 • sweep delta wing at α = 10 • with a trailing edge flap (15% chord) deflected up by 30 • towards the leeward side at M ∞ = 6.0. Surface pressure measurements has been performed on the wing and flap region on the lee side.…”

Section: Introductionmentioning

confidence: 99%

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Thin flat balances for testing thin delta wings at hypersonic speeds

Ramesh¹

2001

Meas. Sci. Technol.

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This paper concerns the design and development of two special novel thin internal strain gauge balances for testing thin slab delta wings at hypersonic speeds. Of the two balances, one is a thin three-component balance and the other is a thin six-component balance. Unlike the conventional balances, which are circular in cross section, the balances discussed here are flat and have rectangular cross sections. Here, the design philosophy and the metallic architecture of these balances are discussed in detail. This paper is divided into three parts wherein the first part deals with the thin three-component balance the second part addresses the thin six-component balance and, in the third part, typical results obtained using these two balances are presented. The thin three-component balance has a thickness of 2.5 mm and can be housed inside a wing as thin as 6 mm. Because of its thinness, the axial output exhibited non-linear interaction from the normal force loading. Hence, combined loading is performed. In order to deduce the second-order coefficients, a new method has been proposed and a comparison with the existing method shows that this is better than the previous method. This balance has been used to generate aerodynamic data on thin slab delta wings with and without lee-side balance housing bodies. In this way, it is demonstrated that the lee-side bodies do interfere even when they come into the aerodynamic shadow of the wing. The thin six-component balance has a thickness of 4 mm and can be housed inside an 8 mm thick wing. Although this balance is also thin, it exhibited excellent linearity in all the bridges. In spite of this, it is subjected to several possible combinations of combined loading and the `work back' loads are calculated using the linear coefficients. The work back loads agree very well with the applied loads. Hence, linear coefficients have been used for the purpose of data reduction. The effects of flap deflection on the aerodynamic characteristics of thin slab delta wings have been studied using this balance. All the experiments were conducted at Mach 8.2 and a Reynolds number of 2.13×106.

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Section: Interference Of Lee-side Bodiessupporting

confidence: 73%