Numerical investigation of transitional axisymmetric wakes at supersonic speeds

D. Tourbier, Hermann F Fasel

Research output: Chapter in Book/Report/Conference proceedingConference contribution

5 Citations (Scopus)

Abstract

The spatial evolution of instability waves in the wake of an axisymmetric body with a blunt base is investigated using direct numerical simulations. The body is aligned with the supersonic free stream, In this paper transitional wake flows are considered. For the simulations a numerical method for solving the complete compressible Navier-Stokes equations in a cylindrical coordinate system was developed. In the numerical method a fourth order Runge-Kutta scheme is employed for the time integration. In axial and radial direction fourth-order accurate central-difference approximations are applied that are split into backward and forward differences at different intermediate time stops. The splitting introduces artificial viscosity, which damps mesh frequency oscillations. A pseudo-spectral method is employed in the circumferential direction. Disturbances are generated, either through a circular blowing and suction slot which is located close to the blunt base of the axisymmetric body or are introduced locally in the flow field. In this paper results of comparison calculations with incompress-ible wakes are discussed, and preliminary results for supcrsonic wrakes are presented. For the supersonic case with Mach number M=2.46 the flow was stable with respect to axisymmetric disturbances for the frequencies that have been tested. Even for three-dimensional (helical) disturbances we found no disturbance amplification for disturbances that were introduced directly into the recirculation region.

Original languageEnglish (US)
Title of host publicationAIAA Fluid Dynamics Conference, 1994
PublisherAmerican Institute of Aeronautics and Astronautics Inc, AIAA
StatePublished - 1994
EventAIAA Fluid Dynamics Conference, 1994 - Colorado Springs, United States
Duration: Jun 20 1994Jun 23 1994

Other

OtherAIAA Fluid Dynamics Conference, 1994
CountryUnited States
CityColorado Springs
Period6/20/946/23/94

Fingerprint

Numerical methods
Direct numerical simulation
Blow molding
Navier Stokes equations
Mach number
Amplification
Flow fields
Viscosity

ASJC Scopus subject areas

  • Aerospace Engineering
  • Engineering (miscellaneous)

Cite this

Tourbier, D., & Fasel, H. F. (1994). Numerical investigation of transitional axisymmetric wakes at supersonic speeds. In AIAA Fluid Dynamics Conference, 1994 [AIAA-94-2286] American Institute of Aeronautics and Astronautics Inc, AIAA.

Numerical investigation of transitional axisymmetric wakes at supersonic speeds. / Tourbier, D.; Fasel, Hermann F.

AIAA Fluid Dynamics Conference, 1994. American Institute of Aeronautics and Astronautics Inc, AIAA, 1994. AIAA-94-2286.

Research output: Chapter in Book/Report/Conference proceedingConference contribution

Tourbier, D & Fasel, HF 1994, Numerical investigation of transitional axisymmetric wakes at supersonic speeds. in AIAA Fluid Dynamics Conference, 1994., AIAA-94-2286, American Institute of Aeronautics and Astronautics Inc, AIAA, AIAA Fluid Dynamics Conference, 1994, Colorado Springs, United States, 6/20/94.
Tourbier D, Fasel HF. Numerical investigation of transitional axisymmetric wakes at supersonic speeds. In AIAA Fluid Dynamics Conference, 1994. American Institute of Aeronautics and Astronautics Inc, AIAA. 1994. AIAA-94-2286
Tourbier, D. ; Fasel, Hermann F. / Numerical investigation of transitional axisymmetric wakes at supersonic speeds. AIAA Fluid Dynamics Conference, 1994. American Institute of Aeronautics and Astronautics Inc, AIAA, 1994.
@inproceedings{6104c7d21b764818beb4938826f708d7,
title = "Numerical investigation of transitional axisymmetric wakes at supersonic speeds",
abstract = "The spatial evolution of instability waves in the wake of an axisymmetric body with a blunt base is investigated using direct numerical simulations. The body is aligned with the supersonic free stream, In this paper transitional wake flows are considered. For the simulations a numerical method for solving the complete compressible Navier-Stokes equations in a cylindrical coordinate system was developed. In the numerical method a fourth order Runge-Kutta scheme is employed for the time integration. In axial and radial direction fourth-order accurate central-difference approximations are applied that are split into backward and forward differences at different intermediate time stops. The splitting introduces artificial viscosity, which damps mesh frequency oscillations. A pseudo-spectral method is employed in the circumferential direction. Disturbances are generated, either through a circular blowing and suction slot which is located close to the blunt base of the axisymmetric body or are introduced locally in the flow field. In this paper results of comparison calculations with incompress-ible wakes are discussed, and preliminary results for supcrsonic wrakes are presented. For the supersonic case with Mach number M∞=2.46 the flow was stable with respect to axisymmetric disturbances for the frequencies that have been tested. Even for three-dimensional (helical) disturbances we found no disturbance amplification for disturbances that were introduced directly into the recirculation region.",
author = "D. Tourbier and Fasel, {Hermann F}",
year = "1994",
language = "English (US)",
booktitle = "AIAA Fluid Dynamics Conference, 1994",
publisher = "American Institute of Aeronautics and Astronautics Inc, AIAA",

}

TY - GEN

T1 - Numerical investigation of transitional axisymmetric wakes at supersonic speeds

AU - Tourbier, D.

AU - Fasel, Hermann F

PY - 1994

Y1 - 1994

N2 - The spatial evolution of instability waves in the wake of an axisymmetric body with a blunt base is investigated using direct numerical simulations. The body is aligned with the supersonic free stream, In this paper transitional wake flows are considered. For the simulations a numerical method for solving the complete compressible Navier-Stokes equations in a cylindrical coordinate system was developed. In the numerical method a fourth order Runge-Kutta scheme is employed for the time integration. In axial and radial direction fourth-order accurate central-difference approximations are applied that are split into backward and forward differences at different intermediate time stops. The splitting introduces artificial viscosity, which damps mesh frequency oscillations. A pseudo-spectral method is employed in the circumferential direction. Disturbances are generated, either through a circular blowing and suction slot which is located close to the blunt base of the axisymmetric body or are introduced locally in the flow field. In this paper results of comparison calculations with incompress-ible wakes are discussed, and preliminary results for supcrsonic wrakes are presented. For the supersonic case with Mach number M∞=2.46 the flow was stable with respect to axisymmetric disturbances for the frequencies that have been tested. Even for three-dimensional (helical) disturbances we found no disturbance amplification for disturbances that were introduced directly into the recirculation region.

AB - The spatial evolution of instability waves in the wake of an axisymmetric body with a blunt base is investigated using direct numerical simulations. The body is aligned with the supersonic free stream, In this paper transitional wake flows are considered. For the simulations a numerical method for solving the complete compressible Navier-Stokes equations in a cylindrical coordinate system was developed. In the numerical method a fourth order Runge-Kutta scheme is employed for the time integration. In axial and radial direction fourth-order accurate central-difference approximations are applied that are split into backward and forward differences at different intermediate time stops. The splitting introduces artificial viscosity, which damps mesh frequency oscillations. A pseudo-spectral method is employed in the circumferential direction. Disturbances are generated, either through a circular blowing and suction slot which is located close to the blunt base of the axisymmetric body or are introduced locally in the flow field. In this paper results of comparison calculations with incompress-ible wakes are discussed, and preliminary results for supcrsonic wrakes are presented. For the supersonic case with Mach number M∞=2.46 the flow was stable with respect to axisymmetric disturbances for the frequencies that have been tested. Even for three-dimensional (helical) disturbances we found no disturbance amplification for disturbances that were introduced directly into the recirculation region.

UR - http://www.scopus.com/inward/record.url?scp=84997724675&partnerID=8YFLogxK

UR - http://www.scopus.com/inward/citedby.url?scp=84997724675&partnerID=8YFLogxK

M3 - Conference contribution

AN - SCOPUS:84997724675

BT - AIAA Fluid Dynamics Conference, 1994

PB - American Institute of Aeronautics and Astronautics Inc, AIAA

ER -