High-altitude aerothermodynamics

Gusev, V. N.

doi:10.1007/bf01051218

Cited by 11 publications

(9 citation statements)

References 4 publications

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“…The rarefaction factor, which can be characterized by the Knudsen number Kn ∞,R , plays an important role in the flow structure [7,[24][25][26][27] as well as in aerothermodynamics [2,3,7,26,27]. The Stanton number reduces significantly with decreasing the Knudsen number (see Fig.…”

Section: Influence Of the Rarefaction Factor (Knudsen Number Kn ∞R )mentioning

confidence: 99%

“…Numerical and experimental studies [1][2][3] of aerothermodynamics of hypersonic vehicles have shown that the temperature in the spacecraft nose region can be extremely high, and the maximum value of the heat flux occurs at small values of the nose radius R and small Knudsen numbers Kn ∞,R that characterize transitional flow regimes from free-molecule medium to continuum [2][3][4][5]. Mass injection can be considered as an effective way of the reduction of heat transfer to the surface in this area [1][2][3][4][5][6][7][8].…”

Section: Introductionmentioning

confidence: 99%

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Heat transfer on a hypersonic sphere with gas injection

Riabov¹

2012

AIP Conference Proceedings

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The interaction of a diffusing outgas flow from a sphere nose opposing a hypersonic free stream is studied numerically using the direct simulation Monte-Carlo technique under the transitional rarefied-gas-flow regime conditions at Knudsen numbers from 0.016 to 1.5 and blowing factors from 0.15 to 1.5. Strong influences of the blowing factor (the ratio of outgas mass flux to upstream mass flux) and the Knudsen number on the flow structure about a sphere (temperature fields and the configuration of mixing flow zones) and on heat distributions along the spherical surface have been found. At large blowing factors, the injected gas significantly reduces heat flux in wide area near the spherical nose. This effect is more pronounced for light gas (helium) injection in the near-continuum flow.

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Section: Influence Of the Rarefaction Factor (Knudsen Number Kn ∞R )mentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Heat transfer on a hypersonic sphere with gas injection

Riabov¹

2012

AIP Conference Proceedings

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“…Nonmonotone characteristics of drag, lift, and pitch moment had been found in many studies. 108,110,146 An opposite sign of the Magnus (lift) force on a rotating cylinder in rarefied gas flow has been discovered after in-class discussions of the Magnus effect found in continuum. 147 …”

Section: New Applications Of "Old" Ideasmentioning

confidence: 99%

“…137 110 and trust evaluation for supersonic combustion regimes. 117,87 The nonequilibrium thermodynamics approach has been considered in detail in the classroom.…”

mentioning

confidence: 99%

Challenge in the aerospace university classroom

Riabov

2000

38th Aerospace Sciences Meeting and Exhibit

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Challenging problems and research have been considered as vital components of Aerospace Engineering curricula. Some Engineering, Computer Science, and Math Courses in American colleges have been analyzed to find positive factors that would be helpful in mutually beneficial cooperation between colleges and industry. The analysis of traditional and modern applications of the course concepts [design of a hypersonic vehicle, nonequilibrium thermodynamics, anisotropic media and liquid crystals, properties of Martian atmospheric gases, non-monotone aerodynamic coefficients of simple-shape bodies, etc.] and ways of collaboration between industry and universities have been discussed. Students' "mistakes" have been reviewed allowing to generate new research ideas and numerical algorithms, as well as to discover new physical phenomena. Challenge in the classroom allows motivating students in the analysis of modern engineering concepts, developing strong background and research skills, finding unique solutions of new problems, and preparing students for success and surviving in industrial environment.

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“…While aircraft are moving in a low atmosphere, the problems are reduced to the problems that can be solved in the frame of continuum theory or, to be more precise, by application of the Navier-Stokes equations and Euler equations [2,3]. On the transition interval between the free molecular and continuum regimes numerical methods of solving the Boltzmann equation and its model equations are being used with success [4]. To correctly simulate hypersonic flows, the flows must be understood and modeled correctly and this is more true than in the numerical simulation of hypersonic flows.…”

Section: Introductionmentioning

confidence: 99%

Computer Modelling of Aerothermodynamic Characteristics for Hypersonic Vehicles

Khlopkov¹,

Khlopkov²,

Myint³

2014

JAMP

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The purpose of this work is to describe the suitable methods for aerodynamic characteristics calculation of hypersonic vehicles in free molecular flow and the transitional regimes. Moving of the hypersonic vehicles at high altitude, it is necessary to know the behavior of its aerodynamic characteristics for all flow regimes. Nowadays, various engineering approaches have been developed for modelling of aerodynamics of aircraft vehicle designs at initial state. The engineering method that described in this paper provides good results for the aerodynamic characteristics of various geometry designs of hypersonic vehicles in the transitional regime. In this paper present the calculation results of aerodynamic characteristics of various hypersonic vehicles in all range of regimes by using engineering method.

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High-altitude aerothermodynamics

Cited by 11 publications

References 4 publications

Heat transfer on a hypersonic sphere with gas injection

Heat transfer on a hypersonic sphere with gas injection

Challenge in the aerospace university classroom

Computer Modelling of Aerothermodynamic Characteristics for Hypersonic Vehicles

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