Numerical investigations of HSCT inlet unstart transient at angle of attack

GeCheng Zha, Doyle D. Knight, Donald Smith

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

4 Citations (Scopus)

Abstract

The unstart transient of a High Speed Civil Transport (HSCT) mixed compression axisymmetric inlet at Mach 2 and 2° angle of attack was investigated numerically by using a 3D time accurate Navier- Stokes solver. The Baldwin-Lomax algebraic turbulence model and an extrapolation uniform mass bleed boundary condition for the slot bleed were employed. It is observed that, when an angle of attack is imposed, the flow on the leeward side has a stronger compression than that at zero angle of attack. The strong compression reduces the Mach number upstream of the terminal shock and therefore makes the shock move upstream first on the leeward side. The initial shock motion starts with the bifurcation of the terminal shock. The lower part of the split shock is stable due to the centerbody bleed while the top part of the shock continues to travel upstream. When the terminal shock on the leeward side passes the bleed region, a separation is induced by the shock/boundary layer interaction on the shoulder of the inlet centerbody and the entire inlet is brought to unstart. The overall computed flow field phenomena agree qualitatively with the experimental observations.

Original languageEnglish (US)
Title of host publication34th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit
PublisherAmerican Institute of Aeronautics and Astronautics Inc, AIAA
ISBN (Print)9780000000002
StatePublished - 1998
Externally publishedYes
Event34th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, 1998 - Cleveland, United States
Duration: Jul 13 1998Jul 15 1998

Other

Other34th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, 1998
CountryUnited States
CityCleveland
Period7/13/987/15/98

Fingerprint

Angle of attack
Mach number
Turbulence models
Extrapolation
Flow fields
Boundary layers
Boundary conditions

ASJC Scopus subject areas

  • Energy Engineering and Power Technology
  • Electrical and Electronic Engineering
  • Mechanical Engineering
  • Control and Systems Engineering
  • Aerospace Engineering

Cite this

Zha, G., Knight, D. D., & Smith, D. (1998). Numerical investigations of HSCT inlet unstart transient at angle of attack. In 34th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit [A98-3583] American Institute of Aeronautics and Astronautics Inc, AIAA.

Numerical investigations of HSCT inlet unstart transient at angle of attack. / Zha, GeCheng; Knight, Doyle D.; Smith, Donald.

34th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit. American Institute of Aeronautics and Astronautics Inc, AIAA, 1998. A98-3583.

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

Zha, G, Knight, DD & Smith, D 1998, Numerical investigations of HSCT inlet unstart transient at angle of attack. in 34th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit., A98-3583, American Institute of Aeronautics and Astronautics Inc, AIAA, 34th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, 1998, Cleveland, United States, 7/13/98.
Zha G, Knight DD, Smith D. Numerical investigations of HSCT inlet unstart transient at angle of attack. In 34th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit. American Institute of Aeronautics and Astronautics Inc, AIAA. 1998. A98-3583
Zha, GeCheng ; Knight, Doyle D. ; Smith, Donald. / Numerical investigations of HSCT inlet unstart transient at angle of attack. 34th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit. American Institute of Aeronautics and Astronautics Inc, AIAA, 1998.
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