An engineering aerodynamic heating method for hypersonic flow

Riley, Christopher J.; Dejarnette, Fred R.

doi:10.2514/6.1992-499

Cited by 12 publications

(4 citation statements)

References 8 publications

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“…19 This method has been widely used to efficiently model convective heating of aerospace vehicles with reasonable accuracy. [20][21][22][23][24][25] The inviscid flow properties required for Eckert's reference enthalpy method are computed using the local pressure from piston theory in conjunction with isentropic flow relations. 15 Thus, aerodynamic heating computations include the effect of structural deformation on the boundary layer flow.…”

Section: Iiid Aeroheatingmentioning

confidence: 99%

Towards a Coupled Loads-Response-Life Prediction Framework for Hypersonic Structures in Combined Extreme Environments

Sobotka

Oral

Culler

2013

54th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference

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This study presents a novel computational framework to improve life prediction capabilities for hypersonic aerospace platforms where evaluating the performance of these structures in extreme environments remains a challenge. Here, thermo-mechanical loading histories determined from analyses that couple aerodynamic loads and structural deflections drive high-fidelity continuum models of the structural member, and results from the continuum model in turn drive critical-plane models of fatigue crack nucleation and growth. This approach readily enables complex features of the loading, geometry, and material response to be incorporated by the structural response and life predictions. Results shown here demonstrate the capabilities of this framework, including: representative thermomechanical and acoustic loadings from ascent to cruise conditions through to descent, the full structural response history, and damage indications that incorporate the full thermocyclic history. Preliminary studies on a challenge structural panel indicate that the ascent and descent phases of the flight profile represent the primary drivers for large residual deflections (on the order of the skin thickness), that remain present in subsequent flights and that may degrade aerodynamic and structural performance. Furthermore, the highly cyclic and transient response present in the acoustic loading phase contributes strongly to localized fatigue damage. Nomenclature b= compressibility exponent C p = pressure coefficient F c = compressible flow transformation function H = enthalpy k = parameter representing compressibility and heat transfer effects M = Mach number m = viscosity power law exponent, η/η e = (T /T e ) m n = velocity power law exponent, U/U e = (y/δ) (1/n) P r = Prandtl number p = pressurẽ p = rms fluctuating pressure q = ρU 2 /2, dynamic pressure r = P r 1/3 , turbulent flow recovery factor T = temperature U = velocity y = normal distance into boundary layer from wall γ = ratio of specific heats δ = boundary layer thickness δ 1 = boundary layer displacement thickness η = viscosity λ = viscous/velocity power law exponent ρ = density φ(ω) = power spectral density ω = frequency, rad/s Subscripts a = attached flow aw = adiabatic wall e = edge of boundary layer s = separated flow w = wall Superscripts * = reference enthalpy condition

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Section: Iiid Aeroheatingmentioning

confidence: 99%

Towards a Coupled Loads-Response-Life Prediction Framework for Hypersonic Structures in Combined Extreme Environments

Sobotka

Oral

Culler

2013

54th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference

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“…Therefore, calculation of inviscid solution on the thicker body is not a difficult task. Due to this approximate solution, however, the application of Riley's method is limited to the windward surface of simple cones with blunt noses [12,[31][32][33].…”

Section: Viscous-interaction Effectmentioning

confidence: 99%

Calculation of the viscous-interaction effects in the Euler/boundary-layer methods

Parhizkar

Karimian

2008

Proceedings of the Institution of Mechanical Engineers, Part G:

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A simple approach is proposed to incorporate the effect of viscous interaction in the calculation of aerodynamic heating of three-dimensional geometries by Euler/boundary-layer methods. In the present study, aerodynamic heating is calculated from the solution of a set of approximate convective-heating equations along the streamlines. These heating equations are derived using axisymmetric analogue. To determine streamline paths and flow properties along them, Euler equations are solved around the three-dimensional body. The effect of viscous interaction on the aerodynamic heating can be significant, especially if the Reynolds number is low. To incorporate this effect, the whole process should be repeated having considered the boundarylayer thickness all around the body. However, this approach causes different difficulties, and is not cost efficient as well. In the present work, the effect of boundary-layer thickness on the aerodynamic heating is incorporated through the correction of pressure distribution on the surface of the body. This approach of correcting pressure distribution is applied to spherical and elliptical blunted cones in laminar hypersonic flows. It is shown that the heating rates are improved in low Reynolds numbers, where viscous-interaction effect is significant. The present approach can result in a reduction of computational cost, when viscous interaction is significant in calculation of aerodynamic heating.

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“…This model took into account the refraction, reflection, absorption and the scattering of the cell wall and could be used to calculate the radiation heat transfer of the honeycomb-core structure. Riley, DeJarnette [3] obtained the surface heating rates in an engineering method for interactive inviscid-boundary layers in three-dimensional hypersonic flows.…”

Section: Introductionmentioning

confidence: 99%

Analysis on Steady Temperature of Honeycomb-Core Panel Based on Coupled Aerothermal Heating and Honeycomb Conduction

Liang

Liu

et al. 2011

AMR

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A physical model is formulated to evaluate the steady temperature field of honeycomb-core panel. The model takes into account the coupled effect of aerothermal heating and radiate energy from front and rear plate and honeycomb thermal conduction. The equations that are established based on the model are solved in numerical method and the equivalent thermal conductivity is obtained. The model is also used to investigate the effect of coming fluid and the geometric parameters of honeycomb structure on the TPS capacity.

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An engineering aerodynamic heating method for hypersonic flow

Cited by 12 publications

References 8 publications

Towards a Coupled Loads-Response-Life Prediction Framework for Hypersonic Structures in Combined Extreme Environments

Towards a Coupled Loads-Response-Life Prediction Framework for Hypersonic Structures in Combined Extreme Environments

Calculation of the viscous-interaction effects in the Euler/boundary-layer methods

Analysis on Steady Temperature of Honeycomb-Core Panel Based on Coupled Aerothermal Heating and Honeycomb Conduction

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