Investigation of the leeward side of a delta wing at hypersonic speeds.

Cross, E. J.; Hankey, W. L.

doi:10.2514/3.29559

Cited by 16 publications

(3 citation statements)

References 2 publications

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“…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%

“…Cross and Hankey [1] have studied the leeward side flow over a flat plate delta wing with sharp leading edges swept back by 75 • at Mach number 10 and summarized that, up to α = 7 • , the flow on the leeward side was fully attached and, at moderate angles of attack of up to 20 • , the flow was attached partly over a small region, followed by shock induced flow separation and formation of vortices which cause the flow to re-attach along the centreline on the leeward 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: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Thin flat balances for testing thin delta wings at hypersonic speeds

Ramesh¹

2001

Meas. Sci. Technol.

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“…The authors further make the following statement: "It is reasonable to assume that if the flap were replaced by a fuselage for housing purposes, the high pressure region induced by the vortex system at reattachment could adversely affect the performance of a hypersonic vehicle." Cross and Hankey' 5 ) have studied the lee-ward side flow over a flat-plate delta wing with sharp leading edges swept back by 75° at Mach number ten, and summarized that up to a = 7°, the flow on the lee-ward side was fully attached and at moderate angles of attack up to 20°, the flow was attached partly over a small region, followed by shock induced flow separation and vortex formations which cause the flow to reattach along the centreline on the leeward side.…”

Section: Introductionmentioning

confidence: 99%

On the aerodynamic characteristics of thin slab delta wings at hypersonic speeds — part 1: interference of lee side bodies

et al. 2000

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An experimental investigation on the interference effect of lee-side balance housing bodies on the longitudinal aerodynamic characteristics of thin slab delta wings has been made using a special and novel thin three-component balance. This study has been conducted using wings with a t/c of 0.053 and sweep of 76°, 70° and 65° for three different lee-side bodies viz:Body (A), Body (B) and Body (C) of which Body (C) is the smallest. The testing was carried out at Mach number of 8·2, Reynolds number of 2·13 ˘ 106 and incidence of –4° to 12°. For the smallest body (Body (C)) tested, at the incidence at which this body first goes into the aerodynamic shadow of the wing (α = 6·5°), the difference in CN, CA, CM and L/D between the wing-body and the plain wing is around by 22%, 12%, 75% and 35% respectively. This difference decreases with increase in incidence and at the highest angle-of-attack up to which testing was done (α = 12°), the. corresponding values of CN, CA, CM and L/D are around 9%, 12%, 15% and 4% respectively. Contrary to the assumption in the literature pertinent to force measurements on thin slab delta wings, the interference of the lee-side bodies are found to be appreciable even after they come into the aerodynamic shadow of the wing.

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Aerodynamic characteristics of a delta wing in hypersonic flow

Kiselev¹,

Маслов²,

Shiplyuk³

1994

J Appl Mech Tech Phys

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In space programs there has been a marked interest lately in the construction of a high-altitude aerospace vehicle (ASV) capable of making shuttle flights to earth orbits for the delivery of various payloads (including spaceship units and components). The various geometries and assembly configurations of such a vehicle are a topic of ongoing discussion among developers at conferences and in print, ground tests are being performed on models, and mathematical model computations are in progress.The actual conditions of flow past an ASV cannot be fully modeled by ground-based wind tunnel research, so that mathematical modeling plays a fundamental role in determining the vehicle aerodynamic characteristics, and experimental data are used to verify the mathematical models. The Hermes aerodynamic research program utilizes test configurations and test regimes discussed in [1]. Considering the complexity of the experiments, it is important to perform measurements under various conditions (on different test facilities using several different methods) so that reliable data can be obtained.Here EXPERIMENTAL APPARATUS AND PROCEDUREThe investigations at Moo = 20.6 are carried out in the T-327 nitrogen wind tunnel at the Institute of Theoretical and Applied Mechanics, Siberian Branch of the Russian Academy of Sciences (ITPM SO RAN) [2]. The apparatus has a working section in the form of a pressure chamber, and flow is generated by means of a conical nozzle with an orifice diameter of 220 mm. Off-model three-component strain gauges equipped with an innovative cooling system, are used for the measurements. The ranges of the measurements are as follows: longitudinal force X = 0 to 0.5 N; normal force Y = -0.5 N to 0.5 N; longitudinal (pitching) moment M z = -0.05 N.m to 0.05 N.m. According to the results of numerous static calibration runs, the measurement error limits expressed in percentages of the measurement ranges are 0.5% for X, 0.5% for Y, and 0.25% for M z. More detailed information about the balance and the procedure for balance experiments in the T-327 may be found in [3, 4], and the results of control model tests (a sphere, a truncated cone, and AGARD models HB-1 and HB-2) are given in [5].The experiments at Mo. = 8.0 are carried out in the T-236 wind tunnel at ITPM SO RAN. The ranges of the modeled parameters are Mo, = 6-16 and (Reynolds number at unit length) Re 1 = (50-700)-105 m -I. A resistance heater capable of reliably heating the air in the prechamber to 800 K is used for the operating regimes Moo = 6-10. The apparatus has an Eifel chamber and is equipped with interchangeable profiled nozzles having orifice diameters of 200 ram, which impart a high degree of uniformity to the flow core. The overall dimensions of the tested models are 50 • 50 • 150 ram.An off-model three-component balance using silicon resistance strain gauges has been developed and fabricated for the T-326 wind tunnel, along with the analog balance of the kind used in the T-327, but engineered for large loads [6]. The balances are equipped with...

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Investigation of the leeward side of a delta wing at hypersonic speeds.

Cited by 16 publications

References 2 publications

Thin flat balances for testing thin delta wings at hypersonic speeds

Thin flat balances for testing thin delta wings at hypersonic speeds

On the aerodynamic characteristics of thin slab delta wings at hypersonic speeds — part 1: interference of lee side bodies

Aerodynamic characteristics of a delta wing in hypersonic flow

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