Experimental Investigation of the Downstream Influence of Stagnation-Point Mass Transfer

Libby, Paul A.; Cresci, Robert J.

doi:10.2514/8.8852

Cited by 26 publications

(5 citation statements)

References 5 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…In the 1960s and 70s, considerable progress was made in understanding the heat flux and pressure augmentations on a variety of geometries, conditions and coolants. Such geometries include blunt body axisymmetric stagnation point injection [18][19][20][21], distributed injection around blunt bodies [22][23][24][25], and sharp cones with downstream frustum injection [26,27].…”

Section: Introductionmentioning

confidence: 99%

Aerodynamic Effects and Heat Flux Augmentation of a Transpiration Cooled Hypersonic Sharp Leading Edge

Ravichandran

Doherty

McGilvray

et al. 2023

AIAA SCITECH 2023 Forum

View full text Add to dashboard Cite

This paper presents numerical results investigating the aerodynamic and aerothermal effects of mass injection applied to hypersonic sharp leading edges, in the context of active thermal protection systems. A numerical study was carried out using Eilmer to investigate the coupling of leading edge radius and mass injection on heat flux and drag augmentations. Radii from 1 mm to 25 mm were considered at blowing parameters from 0.0 to 1.5 on 2D planar leading edge at a fixed trajectory point. Drag was found to barely change with mass injection, whereas heat flux was found to significantly reduce at the leading edge. The leading edge heat flux distribution could be collapsed, and therefore predicted, straightforwardly. Film cooling predictive methods in literature for other mass injection scenarios were found to collapse the heat flux and concentration comfortably with empirical modifications.

show abstract

Section: Introductionmentioning

confidence: 99%

Aerodynamic Effects and Heat Flux Augmentation of a Transpiration Cooled Hypersonic Sharp Leading Edge

Ravichandran

Doherty

McGilvray

et al. 2023

AIAA SCITECH 2023 Forum

View full text Add to dashboard Cite

show abstract

“…The boundary-layer flow with gas blowing was studied in [6,[8][9][10]. Only few studies [11,12] were conducted in the cases of transitional Knudsen numbers.…”

Section: Introductionmentioning

confidence: 99%

Heat transfer on a hypersonic sphere with gas injection

Riabov¹

2012

AIP Conference Proceedings

View full text Add to dashboard Cite

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.

show abstract

“…The boundary-layer flow with gas blowing was studied by Warren 8 , Libbi and Gresci 9 , and Finley 10 . Only few studies (i.e., Pappas and Lee 11 and Moss 12 ) were conducted in the case of small Reynolds numbers.…”

Section: Introductionmentioning

confidence: 99%

Heat Transfer on a Hypersonic Sphere with Diffuse Rarefied-Gas Injection

Riabov

2004

42nd AIAA Aerospace Sciences Meeting and Exhibit

View full text Add to dashboard Cite

The interaction of a diffusing outgas flow from a sphere nose opposing a hypersonic free stream is studied numerically by 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, 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. Nomenclature d = orifice diameter, 0.002 m f = mole fraction of helium G w = mass injection rate ratio ("blowing" factor) Kn ∞,R = Knudsen number M = Mach number p = pressure, N/m 2 R = sphere radius, 0.015 m Re 0,R = Reynolds number St = Stanton number s = coordinate along a spherical surface T = temperature t w = temperature factor, T w /T 0 x = coordinate along an axis of body symmetry subscripts R = sphere radius as a length-scale parameter w = wall condition 0 = stagnation flow condition ∞ = freestream parameter

show abstract

Experimental Investigation of the Downstream Influence of Stagnation-Point Mass Transfer

Cited by 26 publications

References 5 publications

Aerodynamic Effects and Heat Flux Augmentation of a Transpiration Cooled Hypersonic Sharp Leading Edge

Aerodynamic Effects and Heat Flux Augmentation of a Transpiration Cooled Hypersonic Sharp Leading Edge

Heat transfer on a hypersonic sphere with gas injection

Heat Transfer on a Hypersonic Sphere with Diffuse Rarefied-Gas Injection

Contact Info

Product

Resources

About