PLIF Visualization of Active Control of Hypersonic Boundary Layers Using Blowing

Bathel, Brett F.; Danehy, Paul M.; Inman, Jennifer A.; Alderfer, David W.; Berry, Scott A.

doi:10.2514/6.2008-4266

Cited by 19 publications

(8 citation statements)

References 8 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…Specific-heat values for NO, I 2 , and Kr were taken from the National Institute of Standards and Technology/Joint-Army-Navy-Air Force tables [39]. The viscosity is calculated based on kinetic theory from the Chapman-Cowling relationship, which is also found in the work of Hollis [38]: μ 2.6693 10 6 MT p…”

Section: B Governing Equationsmentioning

confidence: 99%

Investigation of Gas Seeding for Planar Laser-Induced Fluorescence in Hypersonic Boundary Layers

Arisman¹,

Johansen²,

Bathel³

et al. 2016

AIAA Journal

View full text Add to dashboard Cite

Section: B Governing Equationsmentioning

confidence: 99%

Investigation of Gas Seeding for Planar Laser-Induced Fluorescence in Hypersonic Boundary Layers

Arisman¹,

Johansen²,

Bathel³

et al. 2016

AIAA Journal

View full text Add to dashboard Cite

“…Seed ing of nitric oxide into the reaction con trol system (RCS) jets of the Orion Crew Exploration Vehicle is an example of this type of gas seed ing strategy.v Another example of intent ional blowing is the use of jets for active conlrol of hypersonic boundary layers. 12 If gaseous injection is not being studied then injection through a port nomlal to the fl ow on the model surface can be used. In th is case.…”

mentioning

confidence: 99%

Numerical investigation of PLIF gas seeding for hypersonic boundary layer flows

Johanson

Danehy

2012

50th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

Self Cite

View full text Add to dashboard Cite

Numerica l simula tions of gas-seeding strategies required for planar lase r-induced fluorescence ( PL.lF) in a Mach 10 air fl ow were performed. The work was performed to und ersta nd and qua ntify adve rse effects associated with gas seedin g a nd to compare different fl ow rates and differe nt t)"pes of seed gas. The gas was injec ted through a slot near the lea ding edge of a fl at plate wedge model used in NASA La ngl ey Resea rch Ce nter's 3 1-Inch Mach 10 Air Tunnel fac ility. Nitric ox ide, krypton, a nd iodin e gases were simulated at va rio us inj ection rates. Simulation results s howing the deflection of the velocity fi eld for each of the cases are presented. Streamwise distributions of veloc ity and concentration boundary layer thicknesses as well as ve rtical distributions of veloc ity, temperature, and mass distributions are presen ted for each of the cases. Rela tive me rits of the differe nt seedin g stra tegies are disc ussed. J. IntroductionT HE injection and dispersion ofa seed gas upstream of a fluid dynamic phenomenon is a common strategy when performing non-intrusive measurements. The use ofa seed gas as a fluid tracer is useful in flow visualization applications since the seeded gas convects through the velocity fie ld and marks fluid fl ow struclUres. Depending on the applicat ion, either uniform or loca lized seeding is required. In studies using planar laser-induced fluorescence (PLl F), for example, un iform seeding is preferred where quantitative measurements like temperature or velocity arc requ ired, while loca l seedi ng may be more advantageous when flow visualization is required, particu larly in applications in volving blowing. Although gas seeding can be avoided in some applications where the fluorescence species forms naturally in the flow, such as in combustion flows (hydroxyl radical, OH) or in high enthalpy wind tunn els (ni tric ox ide. NO), it is often unavoidable. Examples of when localized seed ing is required for PUF flow visualizmion include the study of fuel-air mixing for supersonic combustion ramjet (SCRAMJET) engines l and the study of reaction control system jet interactions wi th hypersonic crossflows associated spacecraft en tTy vehicles. . 3The strategy of seeding tracer gas into a flow to enable PUF measuremen ts has recently been used to study laminar-IO-Iurbulenttran si tion in hypersonic boundary layers. 4 -9 NASA's interest in this fluid dynamic problem is main ly motivated 10 further understand the increase in the surface heating that accompany the transit ion to turbulence du ring the atmospher ic entry of spacecraft vehicles. 10 Figure I shows a sample resul t from an NO PUF experiment where a 20 degree wedge is positioned in a hypersonic flow . I The wedge has a 0.81-mm thick, II -mm wide slot located approximately 29.4 mm downSlfeam of the leading edge where NO gas is injected. In thi s particu lar test, a Boundary Layer Transition Detailed Test Objective (BLT DTO) shaped-trip was used to cause the flow to tran sition to turbulence. Th e laser shee...

show abstract

“…Seeding of NO into the reaction control system jets of the Orion Multi-Purpose Crew Vehicle is an example of this type of gas-seeding strategy [3,4]. Another example of intentional blowing is the use of jets for active control of hypersonic boundary layers [6]. If gaseous injection is not being studied, then injection through a port normal to the flow on the model surface can be used.…”

mentioning

confidence: 98%

“…The relative merits of the different seeding strategies are discussed. The results from a custom solver based on OpenFOAM version 2.2.1 are compared against results obtained from ANSYS® Fluent version 6 T HE tracking of a tracer species is a common method to facilitate flow visualization and to obtain quantitative measurements of flow variables. The tracer follows the flow and can then be imaged, revealing flow structures for further analysis.…”

mentioning

confidence: 99%

Investigation of Gas Seeding for Planar Laser-Induced Fluorescence in Hypersonic Boundary Layers

Arisman

Johansen²,

Bathel

et al. 2015

AIAA Journal

View full text Add to dashboard Cite

Numerical simulations of the gas-seeding strategies required for planar laser-induced fluorescence in a Mach 10 (approximately Mach 8.2 postshock) airflow were performed. The work was performed to understand and quantify the adverse effects associated with gas seeding and to assess various types of seed gas that could potentially be used in future experiments. In prior experiments, NO and NO2 were injected through a slot near the leading edge of a flatplate wedge model used in NASA Langley Research Center's 31 in. Mach 10 air tunnel facility. In this paper, nitric oxide, krypton, and iodine gases were simulated at various injection rates. Simulations showing the deflection of the velocity boundary layer for each of the cases are presented. Streamwise distributions of velocity and concentration boundary-layer thicknesses, as well as vertical distributions of velocity, temperature, and mass distributions, are presented for each of the cases. A comparison between simulated streamwise velocity profiles and experimentally obtained molecular tagging velocimetry profiles using a nitric oxide seeding strategy is performed to verify the influence of such a strategy on the boundary layer. The relative merits of the different seeding strategies are discussed. The results from a custom solver based on OpenFOAM version 2.2.1 are compared against results obtained from ANSYS® Fluent version 6.3. Nomenclature c p = specific heat at constant pressure, kJ∕kg∕K D i;j = binary diffusion coefficient, m 2 ∕s D i;m = diffusion coefficient of species i into the mixture, m 2 ∕s h i = sensible enthalpy of species i, kJ∕kg h s = sensible enthalpy, kJ∕kg I = identity matrix J i = diffusion flux of species i, kg∕m 2 ∕s Kn = Knudsen number k = thermal conductivity, W∕m∕K Ma = Mach number M i = molar mass of species i, kg∕kmol P = pressure, Pa P inf = freestream pressure, Pa P stag = stagnation pressure, Pa P w = wall pressure, Pa R = ideal gas constant, J∕K∕mol Re = Reynolds number R i = mass source of species i S h = enthalpy source, kJ∕s∕m 3 T = temperature, K T stag = stagnation temperature, K t = time, s U = velocity, m∕s U e = boundary-layer edge velocity, m∕s W z = wedge width, mm w c = species mass fraction of interest x = distance from leading edge, m x slot = length of seed slot, mm Y i = mass fraction of species i α = thermal conductivity divided by specific heat at constant pressure, kg∕m∕s β = oblique shock angle δ = boundary-layer thickness, m δ c = concentration boundary-layer thickness, m θ plate = plate angle of attack μ = viscosity, kg∕m∕s ρ = density, kg∕m 3 σ i;j = average species collision diameter, m τ = viscous stress tensor, Pa Ω d = diffusion collision integral Ω v = viscous collision integral

show abstract

PLIF Visualization of Active Control of Hypersonic Boundary Layers Using Blowing

Cited by 19 publications

References 8 publications

Investigation of Gas Seeding for Planar Laser-Induced Fluorescence in Hypersonic Boundary Layers

Investigation of Gas Seeding for Planar Laser-Induced Fluorescence in Hypersonic Boundary Layers

Numerical investigation of PLIF gas seeding for hypersonic boundary layer flows

Investigation of Gas Seeding for Planar Laser-Induced Fluorescence in Hypersonic Boundary Layers

Contact Info

Product

Resources

About