Blunt-Body Wave Drag Reduction Using Focused Energy Deposition

David W. Riggins; Harlan F. Nelson; E. Johnson

doi:10.2514/2.756

Blunt-Body Wave Drag Reduction Using Focused Energy Deposition

David W. Riggins
, Harlan F. Nelson
, E. Johnson

Mechanical and Aerospace Engineering

Missouri University of Science and Technology

Research output: Contribution to conference › Paper › peer-review

Abstract

A parametric computational study of energy deposition upstream of generic two-dimensional and axisymmetric blunt bodies at Mach numbers of 6.5 and 10 is performed utilizing a full Navier-Stokes computational fluid dynamics code. The energy deposition modifies the upstream shock structure and results in large wave drag reduction and very high power effectiveness. Specifically, drag is reduced to values as low as 30% of baseline drag (no energy deposited into flow) and power effectiveness ratios (ratio of thrust power saved to power deposited into the flow) of up to 33 are obtained. The fluid dynamic and thermodynamic bases of the observed drag reduction are examined.

Original language	American English
Pages	1-21
Number of pages	21
DOIs	https://doi.org/10.2514/2.756 https://doi.org/10.2514/6.1998-1647
State	Published - Jan 1 1999
Event	8th AIAA International Space Planes and Hypersonic Systems and Technologies Conference, 1998 - Norfolk, United States Duration: Apr 27 1998 → Apr 30 1998

Conference

Conference	8th AIAA International Space Planes and Hypersonic Systems and Technologies Conference, 1998
Country/Territory	United States
City	Norfolk
Period	4/27/98 → 4/30/98

ASJC Scopus Subject Areas

Space and Planetary Science

Disciplines

Aerospace Engineering
Mechanical Engineering

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10.2514/2.756License: Unspecified
10.2514/6.1998-1647

https://doi.org/10.2514/2.756

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abstract = " A parametric computational study of energy deposition upstream of generic two-dimensional and axisymmetric blunt bodies at Mach numbers of 6.5 and 10 is performed utilizing a full Navier-Stokes computational fluid dynamics code. The energy deposition modifies the upstream shock structure and results in large wave drag reduction and very high power effectiveness. Specifically, drag is reduced to values as low as 30\% of baseline drag (no energy deposited into flow) and power effectiveness ratios (ratio of thrust power saved to power deposited into the flow) of up to 33 are obtained. The fluid dynamic and thermodynamic bases of the observed drag reduction are examined.",

author = "Riggins, \{David W.\} and Nelson, \{Harlan F.\} and E. Johnson",

note = "Publisher Copyright: {\textcopyright} 1998, by D.Riggins, Frederick Nelson, and Eric Johnson.; 8th AIAA International Space Planes and Hypersonic Systems and Technologies Conference, 1998 ; Conference date: 27-04-1998 Through 30-04-1998",

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AU - Nelson, Harlan F.

AU - Johnson, E.

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Y1 - 1999/1/1

N2 - A parametric computational study of energy deposition upstream of generic two-dimensional and axisymmetric blunt bodies at Mach numbers of 6.5 and 10 is performed utilizing a full Navier-Stokes computational fluid dynamics code. The energy deposition modifies the upstream shock structure and results in large wave drag reduction and very high power effectiveness. Specifically, drag is reduced to values as low as 30% of baseline drag (no energy deposited into flow) and power effectiveness ratios (ratio of thrust power saved to power deposited into the flow) of up to 33 are obtained. The fluid dynamic and thermodynamic bases of the observed drag reduction are examined.

AB - A parametric computational study of energy deposition upstream of generic two-dimensional and axisymmetric blunt bodies at Mach numbers of 6.5 and 10 is performed utilizing a full Navier-Stokes computational fluid dynamics code. The energy deposition modifies the upstream shock structure and results in large wave drag reduction and very high power effectiveness. Specifically, drag is reduced to values as low as 30% of baseline drag (no energy deposited into flow) and power effectiveness ratios (ratio of thrust power saved to power deposited into the flow) of up to 33 are obtained. The fluid dynamic and thermodynamic bases of the observed drag reduction are examined.

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M3 - Paper

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T2 - 8th AIAA International Space Planes and Hypersonic Systems and Technologies Conference, 1998

Y2 - 27 April 1998 through 30 April 1998

ER -

Blunt-Body Wave Drag Reduction Using Focused Energy Deposition

Abstract

Conference

ASJC Scopus Subject Areas

Disciplines

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