Aerothermodynamic Performance Analysis of Hypersonic Flow on Power Law Leading Edges

Santos, Wilson F. N.; Lewis, Mark J.

doi:10.2514/1.9550

Cited by 16 publications

(9 citation statements)

References 14 publications

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“…General studies of what constitutes aerodynamically "sharp" vs. "blunt" leading edge geometries for high speed vehicles have been conducted 11 . Specific to waverider-based vehicle configurations, the impacts from hemi-cylindrical and powerlaw body leading edges on performance have been examined [12][13][14][15][16] . O'Brien and Lewis 13 employed power-law curve finite leading edge geometries and showed blunt body-like pressure gradient behavior very close to the stagnation point.…”

Section: Introductionmentioning

confidence: 99%

Integration of Optimized Leading Edge Geometries Onto Waverider Configurations

Rodi

2015

53rd AIAA Aerospace Sciences Meeting

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Most popular waverider design approaches produce vehicles that have sharp leading edges. Manufacturing and/or thermal limits require that some degree of finite radius be employed at the leading edge. Earlier research has produced an optimized leading edge generation process suitable for high speed vehicles such as waveriders. In that effort, Bezier Curves were employed to represent the candidate leading edge cross sectional geometries which were then optimized using a number of cost functions including: minimum peak heating, minimum total heating, minimum drag, and minimum pressure gradient.In the current work, Bezier Curve leading edges have been optimized to reduce the peak leading edge laminar heating for use on waverider-based vehicles designed for three typical hypersonic applications: a Mach 5 Air-Breathing Missile, a Mach 10 Hypersonic Cruise Vehicle, and a Mach 20 Boost-Glide Vehicle. These leading edge geometries have been incorporated onto the vehicles and the resulting integrated aerodynamic performance has been quantified and compared to similar vehicles with conventional hemi-cylindrical leading edge configurations. The largest drag reduction was for the Mach 5 missile, where a 6.2% reduction was predicted when using optimized leading edges on both the inlet and fins. Nomenclature h = altitude n = power law body exponent q = local convective heating rate qbar = freestream dynamic pressure r = power law body local radius r b = power law body base radius r CL = leading edge centerline radius r swept = radius for a swept leading edge t = independent parameter in the Bezier Curve equation C p = pressure coefficient D = drag L = lift, streamwise length of waverider on a given osculating plane M = freestream Mach number X = streamwise distance from the waverider's nose, also streamwise distance on a leading edge Y = spanwise distance from the centerline of the waverider, also vertical distance on a leading edge Z = vertical distance on the waverider measured from a waterline datum θ = leading edge wedge angle θ c = cone angle of power law body on the osculating plane λ loc = local leading edge sweep angle φ = leading edge position angle, measured from the most forward point on a leading edge

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Section: Introductionmentioning

confidence: 99%

Integration of Optimized Leading Edge Geometries Onto Waverider Configurations

Rodi

2015

53rd AIAA Aerospace Sciences Meeting

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“…According to Santos and Lewis, 18 the round leading edge ͑circular cylinder͒, shown in Fig. 1, provides a shock detachment ⌬ / ϱ of 1.645 at the same flow conditions.…”

Section: B Shock-wave Standoff Distancementioning

confidence: 99%

“…[12][13][14][15][16][17][18] Through the use of the direct simulation Monte Carlo ͑DSMC͒ method, they found that the stagnation point heating behavior for power-law leading edges with finite radius of curvature, n =1/ 2, followed that predicted for classical blunt body in that the heating rate is inversely proportional to the square root of curvature radius at the stagnation point. For those power-law leading edges with zero radii of curvature, n Ͼ 1 / 2, it was found that the stagnation point heating is not a function of the curvature radius at the vicinity of the leading edges, but agreed with the classical blunt body behavior predicted by the continuum flow far from the stagnation point.…”

Section: Introductionmentioning

confidence: 99%

“…A great deal of experimental and theoretical works [4][5][6][7][8][9][10][11][12][13][14][15][16][17][18][19][20] has been carried out previously on power-law forms representing blunt geometries. The major interest in these works is twofold: ͑1͒ for Refs.…”

Section: Introductionmentioning

confidence: 99%

“…4-7, the interest had gone into finding solutions to the hypersonic small disturbance form of the inviscid adiabatic-flow equations, since the equations of motion for hypersonic flow over slender bodies can be reduced to simpler form by incorporating the hypersonic slenderbody approximations; 21 ͑2͒ for Refs. [8][9][10][11][12][13][14][15][16][17][18][19][20], the interest has gone into considering the power-law shape as possible candidate for blunting geometries of hypersonic leading edges, such as hypersonic waverider vehicles.…”

Section: Introductionmentioning

confidence: 99%

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Physical and computational aspects of shock waves over power-law leading edges

Santos

2008

Physics of Fluids

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Computations using the direct simulation Monte Carlo ͑DSMC͒ method are presented for hypersonic flow on power-law shaped leading edges. The primary aim of this paper is to examine the geometry effect of such leading edges on the shock-wave structure. The sensitivity of the shock-wave shape, shock-wave thickness, and shock-wave standoff distance to shape variations of such leading edges is investigated by using a model that classifies the molecules in three distinct classes: ͑1͒ undisturbed freestream, ͑2͒ reflected from the boundary, and ͑3͒ scattered, i.e., molecules that had been indirectly affected by the presence of the leading edge. The analysis showed that, for power-law shaped leading edge with exponent between 2 / 3 and 1, the shock wave follows the body shape. It was found that, at the vicinity of the nose, the shock-wave power-law exponent is 1 / 2. Far from the nose, calculations showed that the shock-wave shape is in surprising qualitative agreement with that predicted by the hypersonic small disturbance theory for the flow conditions considered.

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