TY - GEN
T1 - Linearized navier-stokes simulations of the spatial stability of a hypersonic boundary-layer on a flared cone
AU - Salemi, Leonardo C.
AU - Fasel, Hermann
N1 - Publisher Copyright: © 2015 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.
PY - 2015
Y1 - 2015
N2 - The linear stability of a hypersonic boundary-layer is investigated for an almost sharp flared cone at Mach 6. Towards this end, a short-duration pulse through a small hole on the surface of the cone is utilized to excite a broad spectrum of frequencies and streamwise wave numbers in an axisymmetric domain. The flow conditions chosen are from the low- enthalpy experiments performed at the Boeing/AFOSR Mach-6 Quiet Tunnel (BAM6QT) at Purdue University.1-3 In the present work, the newly developed version of the Linearized Compressible Navier-Stokes solver (LinCS)4-6 using generalized cylindrical coordinates is introduced. The derivation of the linearized equations is presented along with results which were generated using the Linearized Compressible Navier-Stokes solver (LinCS) and Direct Numerical Simulations (DNS) for the aforementioned conditions. This new version of LinCS was verified for the linear regime with the Parabolized Stability Equations (PSE) results presented in the literature2 and our low amplitude DNS calculations. In addition, our previous DNS results6 for a 5 deg straight cone in a high-enthalpy flow indicated that, in the linear regime, oscillations in the phase speed, growth rate, wave number and N- factor are observed as amplified second mode wave components synchronize with different boundary layer modes(i.e. entropy/vorticity and acoustic modes)7. Also, such oscillations cease before an amplified wave component slows down to the same phase speed as the vorticity/entropy waves. Our present simulations show that a similar phenomenon is also present in the case of a low-enthalpy flow on a flared cone.
AB - The linear stability of a hypersonic boundary-layer is investigated for an almost sharp flared cone at Mach 6. Towards this end, a short-duration pulse through a small hole on the surface of the cone is utilized to excite a broad spectrum of frequencies and streamwise wave numbers in an axisymmetric domain. The flow conditions chosen are from the low- enthalpy experiments performed at the Boeing/AFOSR Mach-6 Quiet Tunnel (BAM6QT) at Purdue University.1-3 In the present work, the newly developed version of the Linearized Compressible Navier-Stokes solver (LinCS)4-6 using generalized cylindrical coordinates is introduced. The derivation of the linearized equations is presented along with results which were generated using the Linearized Compressible Navier-Stokes solver (LinCS) and Direct Numerical Simulations (DNS) for the aforementioned conditions. This new version of LinCS was verified for the linear regime with the Parabolized Stability Equations (PSE) results presented in the literature2 and our low amplitude DNS calculations. In addition, our previous DNS results6 for a 5 deg straight cone in a high-enthalpy flow indicated that, in the linear regime, oscillations in the phase speed, growth rate, wave number and N- factor are observed as amplified second mode wave components synchronize with different boundary layer modes(i.e. entropy/vorticity and acoustic modes)7. Also, such oscillations cease before an amplified wave component slows down to the same phase speed as the vorticity/entropy waves. Our present simulations show that a similar phenomenon is also present in the case of a low-enthalpy flow on a flared cone.
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U2 - 10.2514/6.2015-0838
DO - 10.2514/6.2015-0838
M3 - Conference contribution
SN - 9781624103438
T3 - 53rd AIAA Aerospace Sciences Meeting
BT - 53rd AIAA Aerospace Sciences Meeting
PB - American Institute of Aeronautics and Astronautics Inc, AIAA
T2 - 53rd AIAA Aerospace Sciences Meeting, 2015
Y2 - 5 January 2015 through 9 January 2015
ER -