Flowfield and vehicle parameter influence on hypersonic heat transfer and drag

Zoby, E. V.; Thompson, Richard A.

doi:10.2514/3.26151

Cited by 7 publications

(5 citation statements)

References 20 publications

(9 reference statements)

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“…This is consistent with the observations obtained by Zoby and Thompson. 30 Further, the pressure drag for some blunted bodies may account for nearly 100% of the total drag, as stated in Singh. 31 Second, the viscosity coefficient of the free stream air is very small under the experimental setup in Li.…”

Section: Physical Model and Numerical Methodsmentioning

confidence: 92%

Comparison between novel waverider generated from flow past a pointed von Karman ogive and conventional cone-derived waverider

Ding

Shen

Liu

et al. 2015

Proceedings of the Institution of Mechanical Engineers, Part G:

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This study conducts a comparison between a novel waverider generated from axisymmetric supersonic flow past a pointed von Karman ogive and a conventional cone-derived waverider generated from the axisymmetric supersonic flow past a cone. First, a pointed von Karman ogive is obtained by sharpening the blunt nose of the original von Karman ogive to a point. Then, a cone with the same shock wave radius at the base plane as that of the pointed von Karman ogive when it travels at a designated supersonic speed is designed. Both axisymmetric supersonic flows past the pointed von Karman ogive and the cone are calculated using the method of characteristics, and the two calculated flow fields are employed as the new and conventional basic flow fields of the waveriders, respectively. Second, a novel waverider is generated from the new basic flow field past the pointed von Karman ogive, using the streamline tracing technique, and a conventional cone-derived waverider is generated from the conventional basic flow field past the cone, using the streamline tracing technique. Finally, numerical methods are employed to verify the design procedures of the novel and conventional cone-derived waveriders, and to analyze the differences between both types of waverider. The obtained results show that the novel waverider possesses lower drag and higher lift-to-drag ratios, while the conventional cone-derived waverider has a higher internal volume and volumetric efficiency.

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Section: Physical Model and Numerical Methodsmentioning

confidence: 92%

Comparison between novel waverider generated from flow past a pointed von Karman ogive and conventional cone-derived waverider

Ding

Shen

Liu

et al. 2015

Proceedings of the Institution of Mechanical Engineers, Part G:

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show abstract

“…In conclusion, we note that the calculation of fully turbulent flow past elongated bodies starting from the stagnation point is permissible, since the heat flux values in the region where the laminar-turbulent transition is complete coincide with those corresponding to earlier transition [3,9,10].…”

Section: Discussion Of Resultsmentioning

confidence: 99%

“…The hypersonic turbulent flow past cones with half-angles Ok= 10, 20, and 30 ~ and surface temperatures tw=0.05 , 0.2, 0.6 was calculated for Reoo = 106, 107, 108 and Moo =6, 8,10. The flow equations were integrated from the forward stagnation point over a distance x=2OOR w. Figure 1 shows the calculated plots of the Stanton number St (curve 1) and the friction coefficient Cf (curve 2) against the distance s measured in blunmess radii from the stagnation point along the cone surface:…”

Section: Discussion Of Resultsmentioning

confidence: 99%

Study of turbulent hypersonic flow past elongated blunt-nosed cones

Паламарчук¹,

Tirskii²,

Utyuzhnikov³

et al. 1994

Fluid Dyn

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Axisyrmnetdc turbulent hypersonic perfect-gas flow past slightly blunted cones is considered. The influence of the absorption of the entropy layer, developing on an elongated body, on friction and heat transfer to the body surface is studied using the viscous shock layer model. Correlations are established for the heat flux and the friction coefficient along the cone surface at large distances from the forward stagnation point. The results are presented together with their correlations in the framework of the viscous shock layer model and an approximate model of the boundary layer type, taking into account the entropy layer absorption. A generalization of the Reynolds analogy is obtained.There are many paper.s dealing with the calculation of the friction and heat transfer in flow past blunt bodies within the framework of the classical theory of the turbulent boundary layer (see [1]). The absorption of the entropy layer by the boundary layer may be regarded as the principal second-order effect in boundary layer theory. Approximate methods have been developed to take this effect into account (see [2--6]). It should be noted that the entropy layer is absorbed more rapidly by a turbulent than by a laminar boundary layer, due to the greater boundary layer thickness; in this case the absorption length is 5--50 bluntness radii. In [2--4] the effect of the absorption of the entropy layer by the boundary layer was taken into account by means of additional calculations for the flow parameters at the outer edge of the boundary layer, using the mass flow rate global balance method. The authors of [5] and [6] have proposed a technique based on the mass-average method. All these approaches enable the entropy layer absorption to be taken into account without solving a set of equations more intricate than that of boundary layer theory. All these approaches need theoretical or experimental verification.The similitude criteria for turbulent boundary layers on blunt-nosed cones were analyzed in [4,6]. In [4] the similitude parameters determining the heat transfer to the cone surface were established for the entropy layer absorption regime over the following ranges of the governing parameters: cone half-angle 0k= 10 deg, Reynolds number Re~ =1.0-105--3.1-105, Mach number Mo. =6--8, temperature factor tw=0.40--0.52 (here, tw=Tw/To, T w being the wall temperature and T O --the stagnation temperature). The similitude criteria governing hypersonic flow past slender blunt bodies in the turbulent boundary layer regime were determined in [6].Our aim is to study numerically the problem of hypersonic turbulent flow past blunt-nosed cones using the viscous shock layer model; to estimate the errors of the various approximate theories; and to establish the similitude criteria for the heat transfer at large distances from the bluntness and for the friction at both large and intermediate distances.

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“…This behavior is due to pressure changes related to surface curvature variations induced by blending of the nose (e.g., downstream effects of nose blunting that originate a combining effect of the entropy layer and AoA) and wing sections into the VTO main fuselage [13,16]. Therefore, the comparisons show the effect of local entropy values, thus highlighting, in addition, the fact that the CIRA approximate code considers that the shock layer is rotational only [17]. Indeed, the bow shock produced by the blunted nose facing the flow at AoA generates entropy gradients in the inviscid shock layer, thus resulting in inviscid velocity gradient normal to the VTO surface that the CIRA-SIM code does not take into account for (e.g., the entropy layer) [15,18].…”

Section: Reliability Of Design Activitiesmentioning

confidence: 94%

Preliminary Design of Vertical Takeoff Hopper Concept of Future Launchers Preparatory Program

Pezzella

Marini

Roncioni

et al. 2009

Journal of Spacecraft and Rockets

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This paper deals with the aerodynamic and aerothermodynamic preliminary design activities for the vertical takeoff hopper concept performed in the frame of the Future Launcher Preparatory Programme of the European Space Agency. The reentry scenario with the corresponding loading environment for the proposed vehicle concept is reported and analyzed. The hypersonic aerodynamic and aerothermodynamic characteristics of the vertical takeoff hopper are investigated by means of several engineering analyses and a limited number of computational fluid dynamics simulations in order to assess the accuracy of the simplified design estimations. The results show that the difference between Eulerian computational fluid dynamics and an engineering-based design is smaller than 10% for aerodynamic coefficients, whereas a margin of about 30% has to be taken into account for what concerns the aerothermodynamic results. The final results applicable for the prosecution of the launcher design activity are that, at the condition of peak heating, the vehicle features a nose stagnation point heat flux of about 500 kW=m 2 and an aerodynamic lift-to-drag ratio of about 1.2. Nomenclaturealong wing chord running from leading edge, m D = aerodynamic drag, N F = aerodynamic force, N H = altitude, m L = aerodynamic lift, N/fuselage length, m/chord length M = Mach number/aerodynamic moment, Nm Q = integrated heat load, MJ=m 2 _ q = convective heat flux, kW=m 2 q = dynamic pressure, Pa R = radius of curvature, m Re = Reynolds number Re=m = unit Reynolds number, 1=m S = reference area, m 2 T = temperature, K t = time, s v = velocity, m=s x = distance along vehicle forebody running from nose, m = angle of attack, deg = angle of side slip, deg = leading-edge sweep angle, deg = density, kg=m 3 = fuselage meridian angle, deg Subscripts eff = effective N = nose ref = reference sp = stagnation point WLE = wing leading edge w = wall Y = pitching moment 1 = freestream conditions

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Flowfield and vehicle parameter influence on hypersonic heat transfer and drag

Cited by 7 publications

References 20 publications

Comparison between novel waverider generated from flow past a pointed von Karman ogive and conventional cone-derived waverider

Comparison between novel waverider generated from flow past a pointed von Karman ogive and conventional cone-derived waverider

Study of turbulent hypersonic flow past elongated blunt-nosed cones

Preliminary Design of Vertical Takeoff Hopper Concept of Future Launchers Preparatory Program

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