New Formulas for Standoff Distance in Front of Spacecraft in Hypersonic Flow

Hu, Yumeng; Huang, Haiming; Zhang, Zimao

doi:10.2514/1.a33642

Cited by 7 publications

(6 citation statements)

References 19 publications

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“…Consequently, at an altitude of 70 km, the shock stand-off distance does not increase at higher velocity of 11 km/s. The trend of increment in the shock stand-off distance with flight speed at higher velocity more than 9 km/s has also been observed in other references (Zander et al , 2014; Hu et al , 2016). By using an expansion tunnel facility, Zander et al (2014) observed a tendency that the shock stand-off distance increases with increment in flight velocity.…”

Section: Flow-field Analysis For Hypersonic Flight Conditionsupporting

confidence: 84%

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Evaluation of Fay and Riddell formula under hypersonic flight conditions

Lee

Yang

Kim

2022

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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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Section: Flow-field Analysis For Hypersonic Flight Conditionsupporting

confidence: 84%

“…(2014) observed a tendency that the shock stand-off distance increases with increment in flight velocity. In a separate study,Hu et al (2016) conducted a numerical study to measure the effect of Mach number on the shock stand-off distance and observed that the…”

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confidence: 99%

Evaluation of Fay and Riddell formula under hypersonic flight conditions

Lee

Yang

Kim

2022

HFF

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“…The model proposed in [45] takes into account the geometry of the aircraft head and flow quantities. The approach proposed in [47] allows one to obtain a relation for the standoff distance, the parameters of which are the Mach number and density. The approach is developed in [10], which gives the shock layer thickness as a function of the Mach number and flight altitude, which varies from 25 to 55 km.…”

Section: Resultsmentioning

confidence: 99%

Numerical simulation of hypersonic flow with non-equilibrium chemical reactions around sphere

et al. 2022

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“…Although many near space hypersonic vehicles, such as X-37 (Gülhan et al, 2014), X-51 (Schimisseur, 2015) and Falcon HTVs (Walker et al, 2008), have been succeeded in their missions, the exploration of aerothermodynamic problems is the principle obstacle because the velocities and altitudes at which these vehicles would operate are different, and sometimes more severe (Huang and Huang, 2015;Hu et al, 2016aHu et al, , 2016bLi et al, 2016), than those went through in the past. As future hypersonic vehicle quests to fly higher and faster, the environment surrounding the vehicle could be more dramatically changed (Hu et al, 2016a(Hu et al, , 2016bCai 2016;Yuan et al, 2017) and more difficult to simulate in ground-based test facilities (Doig et al, 2016), which makes the numerical simulations become increasingly important issues (Park et al, 2016;Boyd et al, 2010). Whether the existing numerical methods can apply to higher velocity is an urgent problem to be solved.…”

Section: Introductionmentioning

confidence: 99%

Study on the performance of spatial discretization schemes for hypersonic flow

Huang

2018

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Purpose With the continuous increase of space activities and insight into space exploration, the velocity of near space hypersonic vehicles becomes higher and higher, which leads to the aerothermodynamic phenomenon getting worse around a vehicle; therefore, the exploration of numerical scheme applicability is essential for hypersonic flow simulations. Design/methodology/approach The implicit finite volume schemes are derived from axisymmetric Navier–Stokes equations for chemical equilibrium flow and programmed in Fortran. Taking the atmosphere at 30 km as an example, the performance of spatial discretization schemes such as AUSMPW and AUSMPW+ are analyzed in a range of Mach numbers from 17 to 32. Findings The AUSMPW scheme appears pressure jump near the stagnation if the Mach number is over 18, but AUSMPW+ scheme shows better performance in comparison. Originality/value This study will help the aerothermodynamic design in near space hypersonic vehicles.

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New Formulas for Standoff Distance in Front of Spacecraft in Hypersonic Flow

Cited by 7 publications

References 19 publications

Evaluation of Fay and Riddell formula under hypersonic flight conditions

Evaluation of Fay and Riddell formula under hypersonic flight conditions

Numerical simulation of hypersonic flow with non-equilibrium chemical reactions around sphere

Study on the performance of spatial discretization schemes for hypersonic flow

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