Supersonic Skin-Friction Drag with Tangential Wall Slot Fuel Injection and Combustion

Kirchhartz, Rainer; Mee, D. J.; Stalker, R. J.

doi:10.2514/1.j051073

Cited by 32 publications

(12 citation statements)

References 34 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…Skin friction reduction and thermal protection are one of the main techniques for the design of scramjet combustion chamber [2]. Among numerous skin friction/ thermal protection techniques [4,5,6], boundary-layer combustion technique, which use a injection and combustion of flammable gas like hydrogen, attracts worldwide attention because of its excellent skin-friction reduction performance.…”

Section: Introductionmentioning

confidence: 99%

Hydrogen Energy paper 17

2018

Proceeding of 2018 the Fourth International Symposium on Hydrogen Energy, Renewable Energy and Materials

View full text Add to dashboard Cite

Abstract:The improvement of the skin friction/heat transfer prediction theory of compressible turbulent boundary-layer combustion of hydrogen is conducted in this paper. The original theory is improved through two aspects. One is the modification of the relation between surface hydrogen mass fraction and Reynolds number by rebuilding the Kármán momentum integral relation. The other is the change of computational method of Prandtl number by adopting the molecular kinetic theory. The improved theory is used to make prediction of skin friction and heat transfer that are found to be better consistent with experimental results than original theory. In addition, a numerical experiment of boundary-layer combustion is conducted. By comparing the results given by numerical simulation and theoretical prediction, it also found that the improved theory shows better prediction performance than the original theory.

show abstract

Section: Introductionmentioning

confidence: 99%

Hydrogen Energy paper 17

2018

Proceeding of 2018 the Fourth International Symposium on Hydrogen Energy, Renewable Energy and Materials

View full text Add to dashboard Cite

show abstract

“…Tanno et al (2001): this paper documents the development and use of a single component balance to measure the internal skin friction drag acting on an axisymmetric scramjet combustor. See also Chan (2012), Kirchhartz et al (2012), and Rowan and Paull (2006). Mee (2002Mee ( , 2003: this report and paper describe the dynamic calibration of a single component balance using an instrumented impact hammer.…”

mentioning

confidence: 99%

“…Barth et al, 2013;Goyne et al, 2000;Kirchhartz et al, 2012;Stalker, 2005). Due to the risk of inlet unstart and increased drag resulting from higher pressures on the forward facing inlet surfaces, combustion of fuel within a scramjet inlet is undesirable however, viscous drag reduction by way of film cooling may also be possible.…”

mentioning

confidence: 99%

An experimental investigation of an airframe integrated three-dimensional scramjet engine at a Mach 10 flight condition

Doherty¹

View full text Add to dashboard Cite

The University of Queensland in 2014 school of mechanical and mining engineering centre for hypersonics abstract Realisation of the dream of airbreathing access-to-space requires the development of a scramjet engine that produces sufficient net thrust to enable acceleration over a wide Mach number range. With engines that are highly integrated with the airframe, the net performance of a scramjet powered vehicle is closely coupled with the vehicle attitude and is difficult to determine only from component level studies. This work investigates the influence of airframe integration on the performance of an airframe integrated scramjet through the measurement of internal pressure distribution and the direct measurement of the net lift, thrust and pitching moment using a three-component stress wave force balance. The engine chosen as the basis for this study was the Mach 12 rectangularto-elliptical shape-transition (m12rest) scramjet that was developed by Suraweera and Smart (2009) as a research engine for access-to-space applications. The inlet and combustor flowpath were integrated with a slender 6°wedge forebody, streamlined external geometry and three dimensional thrust nozzle. The scale of the engine was chosen so that the entire engine would fit within the core-flow diamond (bi-conic) produced by a Mach 10 facility nozzle. The Mach 10b facility nozzle was chosen because it is the largest nozzle current in use with the t4 Stalker Tube and because the offdesign performance of a scramjet engine is of interest for access-to-space vehicles that must accelerate over a range of Mach numbers.Freejet experiments were conducted within the t4 Stalker Tube. Two trueflight Mach 10 test conditions were used: a high pressure test condition that replicated flight at a dynamic pressure of 48 kPa and a low pressure test condition that replicated flight at a dynamic pressure of 28 kPa. Scaling of the test conditions according to the established binary scaling law was not completed due to facility operational limits.The engine featured two fuel injection stations from which gaseous hydrogen was injected. The first injection station was partway along the length of the inlet while the second injection station was at the start of the combustor behind a rearward facing circumferential step. In addition to investigating inlet-only and step-only injection, a combined scheme where 68 % of the fuel was injected from the step station and 32 % from the inlet station was also investigated.To support the analysis of the experimental results, numerical simulations of the engine with no fuel injection were conducted using the nasa code vulcan. Analysis of the simulations show that the mass capture ratio with respect to the projected inlet area is approximately 60 % at each test condition. The simulations also show that spillage of flow from the slender forebody accounts for just 12 % of the flow through the projected iii inlet area, a small but non-negligible fraction. By integrating the engine surface forces, the drag coefficient with respect ...

show abstract

“…Compared with the level measured with no hydrogen injection, maximum reductions in skin friction coefficient of approximately 77% for high total enthalpy and 60% for low total enthalpy were recorded. Recently, Kirchhartz et al [6] carried out a wind-tunnel experiment on boundary-layer combustion using a practical supersonic combustor model, and they validated the effectiveness of skinfriction reduction by boundary-layer combustion for a practical supersonic chamber. The aforementioned experiments on boundarylayer combustion only studied the skin-friction reduction function of boundary-layer combustion, whereas the associated physical mechanisms of skin-friction reduction by boundary-layer combustion need to be verified by theoretical analysis or numerical methods.…”

mentioning

confidence: 99%

“…However, available studies on the drag reduction of scramjet engines are relatively scarce. Among the overall internal viscous drag of a scramjet engine, the portion generated in the combustion chamber could take more than half of the total viscous drag [6] because of the high wall shear stress on its walls. Consequently, the development of a flow control technique to reduce the viscous drag of supersonic compressible turbulent boundary layers in the scramjet chamber is of great significance for the enhancement of the thrust-to-drag ratio.…”

mentioning

confidence: 99%

Combustion Heat-Release Effects on Supersonic Compressible Turbulent Boundary Layers

et al. 2015

View full text Add to dashboard Cite

Influences of heat release by the hydrogen combustion in supersonic turbulent boundary layers are numerically studied using Reynolds-averaged Navier-Stokes equations. The adopted Reynolds-averaged Navier-Stokes methodology is first validated by comparing the numerical results with the existing experimental data. Studies on the effects of the flame perpendicular position inside the boundary layer reveal that, while the flame is restricted around the edge of the boundary layer, the heat release may slightly reduce rather than increase the wall heat flux because of the suppression effect on the turbulent energy transport due to heat release. However, as the flame moves toward the wall, the skin-friction reduction effect would not be obviously strengthened, but the wall heat flux could be dramatically enhanced by the increase of near-wall chemical reactions. At a given hydrogen mass flow rate, the injection scheme with a higher injection height and a lower injection velocity could be helpful to achieve a larger skinfriction reduction while maintaining a lower wall heat flux. Finally, analysis of the heat-release effects on the velocity law of the wall shows that van Driest's velocity law largely deviates from the computational results, whereas White's velocity law remains close to the numerical results within a region of approximately y < 300. Nomenclature B = law-of-the-wall constant (5.0) c f = local skin friction coefficient c p = specific heat at constant pressure, J∕kg · K D = mass diffusivity, m 2 ∕s E = total energy, J∕kg H = total enthalpy, J∕kg h s = static enthalpy for species s, J∕kg h = hydrogen injection height at the entrance, m k = turbulent kinetic energy, m 2 ∕s 2 M = Mach number Pr = Prandtl number Pr t = turbulent Prandtl number p = pressure, MPa q w = local heat flux, MW∕m 2 r= Pr 1∕3 , recovery factor Sc t = turbulent Schmidt number T = temperature, K u = velocity, m∕s u τ = friction velocity, m∕s Y hw = hydrogen mass fraction at the wall Y s = mass fraction of species s δ = boundary-layer thickness, m κ = von Kármán constant (0.41) λ = molecular thermal conductivity, W∕m · K μ = molecular viscosity, N · s∕m 2 μ t = turbulent eddy viscosity, N · s∕m 2 ρ = density, kg∕m 3 τ = shear stress, N∕m 2 ω = specific turbulent dissipation, 1∕s _ ω = mass production per unit volume per unit time, kg∕m 3 · s Subscripts e = edge of boundary layer j = jet s = species s w = wall ∞ = freestream Superscripts t = turbulent = Reynolds averagẽ = Favrè average

show abstract

Supersonic Skin-Friction Drag with Tangential Wall Slot Fuel Injection and Combustion

Cited by 32 publications

References 34 publications

Hydrogen Energy paper 17

Hydrogen Energy paper 17

An experimental investigation of an airframe integrated three-dimensional scramjet engine at a Mach 10 flight condition

Combustion Heat-Release Effects on Supersonic Compressible Turbulent Boundary Layers

Contact Info

Product

Resources

About