Computational Investigation and Simulation of Aerothermodynamics of Reentry Vehicles

Papadopoulos, Periklis; Subrahmanyam, Prabhakar

doi:10.2514/6.2005-3206

Cited by 3 publications

(3 citation statements)

References 3 publications

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“…The total enthalpy h 0 = h ∞ + V 2 /2, where h ∞ is the local enthalpy of the atmosphere. However, for reentry, h ∞ is usually smaller than V 2 /2, and can be neglected (Papadopoulos and Subrahmanyam, 2005).…”

Section: Modelsmentioning

confidence: 99%

Trajectory optimization for hypersonic boost‐glide missile considering aeroheating

Cui

Rong

2009

Aircraft Engineering and Aerospace Technology

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PurposeThe purpose of this paper is to optimize the downrange for hypersonic boost‐glide (HBG) missile under near‐real condition, and to validate the suitability of proposed wall cooling materials.Design/methodology/approachThe trajectory optimization problem is characterized by a boost phase followed by a glide phase. A multi‐phase trajectory optimization tool is adopted to optimize the downrange. The associated optimal control problem has been solved by selecting a direct shooting method. The dynamics has been transcribed to a set of nonlinear constraints and the arising nonlinear programming problem has been solved through a sequential quadratic programming solver. An aerothermodynamics analysis method is introduced to calculate the aerodynamic heating at nose, leading edge, and ventral centerline regions.FindingsHBG missile is suitable for long‐range attack, and the optimal trajectory solved is a novel boost‐glide‐skip trajectory, i.e. boost firstly, glide secondly, and skip at last. The proposed wall materials are valid.Originality/valueThis paper provides further study on the methods of trajectory design and aerothermodynamics analysis for HBG missile.

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Section: Modelsmentioning

confidence: 99%

Trajectory optimization for hypersonic boost‐glide missile considering aeroheating

Cui

Rong

2009

Aircraft Engineering and Aerospace Technology

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“…Because of its rigorous theoretical basis as well as simplicity, F–R has been extensively used as a reference value for hypersonic aerothermal heating (Zuppardi and Verde, 1998), not only for numerical estimation of the reentry flight (Park and Balakrishnan, 1985; Yamamoto and Yoshioka, 1995; Park et al , 1998; Cheatwood et al , 2001; Park, 2001; Papadopoulos and Subrahmanyam, 2005; Cassell et al , 2011) but also for flow-field characterization in hypersonic ground test facilities (Olivier, 1993; Chadwick, 1997; Carlson, 1999; Kuchi-ishi et al , 2003; Marineau and Hornung, 2009; Saravanan et al , 2009; Schrijer and Bannink, 2010; Flaherty and Austin, 2011; Srinivasan et al , 2016; Bensassi et al , 2017; Saiprakash et al , 2019).…”

Section: Introductionmentioning

confidence: 99%

Evaluation of Fay and Riddell formula under hypersonic flight conditions

Lee

Yang

Kim

2022

HFF

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Purpose The Fay and Riddell (F–R) formula is an empirical equation for estimating the stagnation-point heat flux on noncatalytic and fully catalytic surfaces, based on an assumption of equilibrium. Because of its simplicity, the F–R has been used extensively for reentry flight design as well as ground test facility applications. This study aims to investigate the uncertainties of the F-R formula by considering velocity gradient, chemical species at the boundary layer edge, and the thermochemical nonequilibrium (NEQ) behind the shock layer under various hypersonic NEQ flow environments. Design/methodology/approach The stagnation-point heat flux calculated with the F–R formula was evaluated by comparison with thermochemical NEQ calculations and existing flight experimental values. Findings The comparisons showed that the F–R underestimated the noncatalytic heat flux, because of the chemical composition at the surface. However, for fully catalytic heat flux, the F–R results were similar to values of surface heat flux from thermochemical NEQ calculations, because the F–R formula overestimates the diffusive heat flux. When compared with the surface heat flux results obtained from flight experimental data, the F–R overestimated the fully catalytic heat flux. The error was 50% at most. Originality/value The results provided guidelines for the F–R calculations under hypersonic flight conditions and for determining the approximate error range for noncatalytic and fully catalytic surfaces.

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“…Για την σύγκριση των αποτελεσµάτων παρατίθενται επίσης αντίστοιχες καµπύλες µέσω των πολυωνυµικών εξισώσεων STW [135] σε κανονικοποιηµένες τιµές των µεγεθών και των µεταβλητών εύρους καµπύλης ξεκινώντας από την ακραία (ελάχιστη) τιµή -7,0 και καταλήγοντας στην ανώτερη (µέγιστη) τιµή 3,0. Όπως είναι προφανές, παρατηρείται ταύτιση των αποτελεσµάτων της παρούσας θερµοδυναµικής µεθοδολογίας για την εύρεση των µεταβαλλόµενων θερµοδυναµικών ιδιοτήτων του αέρα στις υψηλές θερµοκρασίες, σε σχέση µε τα αντίστοιχα αποτελέσµατα της διεθνούς βιβλιογραφίας [61,113,119,141] .…”

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Ροές Υψηλών Ταχυτήτων Και Θερμοδυναμική Αερίων Σε Υψηλές Θερμοκρασίες

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Computational Investigation and Simulation of Aerothermodynamics of Reentry Vehicles

Cited by 3 publications

References 3 publications

Trajectory optimization for hypersonic boost‐glide missile considering aeroheating

Trajectory optimization for hypersonic boost‐glide missile considering aeroheating

Evaluation of Fay and Riddell formula under hypersonic flight conditions

Ροές Υψηλών Ταχυτήτων Και Θερμοδυναμική Αερίων Σε Υψηλές Θερμοκρασίες

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