HyHypervelocity Testing of a Dual-mode Scramjet

Smayda, Michael; Vogel, Patrick D.; Schultz, Ian A.; Hanson, Ronald K.; Foelsche, Robert; Tsai, Ching‐Yi; Cresci, Daniel; Goyne, Christopher P.

doi:10.2514/6.2012-481

Cited by 3 publications

(7 citation statements)

References 7 publications

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“…Results refer to two test cases available in the literature for typical propulsive applications: the first is from Lorrain [6] and the second is from Smayda et al [47]. All simulations have been made considering the same grid for the different solvers, thus allowing a grid-independent comparison.…”

Section: Test Casesmentioning

confidence: 99%

Numerical Modeling and Simulation of Supersonic Flows in Propulsion Systems by Open-Source Solvers

Hoste

Casseau

Fossati

et al. 2017

21st AIAA International Space Planes and Hypersonics Technologies Conference

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Two open-source solvers, Eilmer and hyFoam, are here considered for their performance in simulating high-speed flows in different flow conditions and geometric configurations typical of propulsive systems at supersonic speeds. The goal is to identify the open-source platform providing the best compromise between accuracy, flexibility and computational cost to eventually simulate the flow fields inside ramjet and scramjet engines. The differences in terms of discretization and solution methods of the selected solvers are discussed in terms of their impact on solution accuracy and computational efficiency and in view of the aerothermodynamic analysis and design of future transatmospheric propulsive systems. In this work steady state problems are considered. Numerical results of two scramjet type engines demonstrated a similar predictive capability of both codes in non-reacting conditions. These results highlight their potential to be considered for further characterization of overall engine performance. * PhD Candidate, AIAA Student Member. † Lecturer, AIAA Member . ‡ Senior Lecturer.

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Section: Test Casesmentioning

confidence: 99%

Numerical Modeling and Simulation of Supersonic Flows in Propulsion Systems by Open-Source Solvers

Hoste

Casseau

Fossati

et al. 2017

21st AIAA International Space Planes and Hypersonics Technologies Conference

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“…It can be noticed that the oblique shock wave produced at the ramp impinge at roughly the same position as in Figure 11. The slight difference in clarity is due to Smayda's computational domain using 14 million elements [4], whereas the computational domain in Figure 12a uses 190,000 elements which was found to be sufficient while saving on computational cost as used in the overall project study. The use of 190,000 elements was justified by mesh convergence study illustrated below in Figure 12b, which shows that after 190,000 elements, there were no significant change to the results.…”

Section: Computational Fluid Dynamics (Cfd) Setup Validationmentioning

confidence: 99%

“…The boundary conditions included for a varied Mach number range at absolute, ambient total pressure of 109,000 Pa and equivalent total temperature of 227.13 K. Figure 11 displays the static pressure contours of the scramjet designed by Smayda et al [4]. Here the shock placement and structure can be compared along with the performance in terms of compression achieved (i.e., increase in static pressure).…”

Section: Computational Fluid Dynamics (Cfd) Setup Validationmentioning

confidence: 99%

“…Furthermore, it contains the shock trains, which are unavoidable 'back-ground waves' encountered in supersonic pressure-gain flows restricted in a duct, with the isolator preventing interaction of the combustor and inlet, else the heat from the combustion can propagate upstream and significantly affect the operation of the inlet [10]. Equation (4) relates the temperature at the combustor entrance (T3) to the freestream temperature (T0) [2]: The kinetic energy efficiency can be used to quantify the performance of the compression system and usually for simplification the equation can be assumed to be an adiabatic process, which can be seen in Equation (1):…”

Section: Isolatormentioning

confidence: 99%

“…Work done by Smayda et al [4] was used as a means of validating the CFD setup on ANSYS Fluent (Canonsburg, PA, USA), in addition to the data comparison between theoretical and CFD results. Since it is difficult to find a complete list of CFD setup for hypersonic flow problems, further research papers and tutorials were used [1,18,19].…”

Section: Computational Fluid Dynamics (Cfd) Setup Validationmentioning

confidence: 99%

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A Scramjet Compression System for Hypersonic Air Transportation Vehicle Combined Cycle Engines

2018

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This paper proposes a compression system for a scramjet, to be used as part of a combined cycle engine on a hypersonic transport vehicle that can achieve sustained flight at 8 Mach 8. Initially research into scramjet compression system and shock wave interaction was conducted to establish the foundation of the scramjet inlet and isolator sections. A Computational Fluid Dynamics (CFD) campaign was conducted, where the shock structure and flow characteristics was analysed between Mach 4.5-8. The compression system of a scramjet is of crucial importance in providing air at suitable Mach number, pressure and temperature to the combustion chamber. The use of turbojet engines in over-under configuration with the scramjet was investigated as well as the study of a combined cycle scramjet-ramjet configuration. It was identified that locating the scramjet in the centre with a rotated ramjet on either side, where its ramps make up the scramjet wall was the most optimal configuration, as it mitigated the effect of the oblique shocks propagating from the scramjet walls into the adjacent ramjet. Furthermore, this meant that the forebody of the vehicle could solely be used as the compression surface by the scramjet. In this paper, the sizing of the scramjet combustion chamber and nozzle were modified to match the flow properties of the oncoming flow with the purpose of producing the most optimum scramjet configuration for the cruise speed of Mach 8. CFD simulations showed that the scramjet inlet did not provide the levels of compression and stagnation pressure recovery initially required. However, it was found that the scramjet provided significantly more thrust than the drag of the aircraft at sustained Mach 8 flight, due to its utilisation of a very aerodynamic vehicle design.

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Hypersonic scramjet testing via TDLAS measurements of temperature and column density in a reflected shock tunnel

Schultz

Goldenstein

Strand

et al. 2014

52nd Aerospace Sciences Meeting

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A wavelength-multiplexed two-color TDLAS sensor probing transitions near 1.4 µm was developed to measure H2O temperature and column density simultaneously across three lines-of-sight in a ground-based model scramjet combustor. High-enthalpy scramjet conditions equivalent to Mach 10 flight were generated with a reflected shock tunnel. The sensor hardware development and optical engineering to overcome noisy combustor conditions including short test time, beam steering, and mechanical vibration are discussed. A new scanned wavelength-modulation spectroscopy (WMS) technique was used to acquire the complete spectral lineshape while maintaining the high signal-to-noise ratio characteristic of WMS measurements. Two combusting flow experiments were conducted and the results compared with steady-state CFD calculations, with both the simulations and the measurements finding formation of H2O from H2 combustion during the test time. To our knowledge, this work represents the first use of WMS in a reflected shock tunnel and the first use of scanned-WMS in a scramjet combustor. Nomenclature I 0 = incident spectral intensity, W/cm 2 s −1 I t = transmitted spectral intensity, W/cm 2 s −1 ν = optical frequency, cm −1 α = absorbance L = optical path length, cm n i = number density of absorbing species, molecules/cm 3 S n = transition linestrength, cm −1 /molecule cm −2 φ = lineshape function T = temperature, K P = pressure, atm χ = gas mole fraction vector χ i = gas mole fraction of species i A = integrated absorbance, cm −1 N i = column density, molecules/cm −2 σ i = column density (mass basis), kg/cm −2 ρ i = density of absorbing species i, kg/m −3 Q = partition function of absorption transition AIAA SciTech h = Planck constant, J·s c = speed of light, cm/s E = lower state energy of absorption transition, cm −1 k = Boltzmann constant, J/K ν 0 = line-center frequency of absorption transition, cm −1 I 0 = average laser intensity, W/cm 2 s −1 i n = intensity sinusoid amplitude (n=1, 2) ψ n = intensity sinusoid phase shifts (n=1, 2) ν = laser center frequency, cm −1 a n = wavelength scan and modulation depths (n=1, 2) Ψ n = wavelength sinusoid phase shifts (n=1, 2) f s = laser scan frequency, Hz f m = laser modulation frequency, Hz Φ = fuel-air equivalence ratio θ = angle of attack γ = heat capacity ratio c P /c V

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HyHypervelocity Testing of a Dual-mode Scramjet

Cited by 3 publications

References 7 publications

Numerical Modeling and Simulation of Supersonic Flows in Propulsion Systems by Open-Source Solvers

Numerical Modeling and Simulation of Supersonic Flows in Propulsion Systems by Open-Source Solvers

A Scramjet Compression System for Hypersonic Air Transportation Vehicle Combined Cycle Engines

Hypersonic scramjet testing via TDLAS measurements of temperature and column density in a reflected shock tunnel

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