Dynamic analysis of wind tunnel data from an isentropic relaxed compression inlet

Kathleen M. Tacina, Stefanie M. Hirt, Timothy R. Conners, Jason M Merret, Donald C. Howe

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

Abstract

A family of five axisymmetric external compression inlets was tested at Mach 1.97 in the 1-ft × 1-ft supersonic wind tunnel at the NASA Glenn Research Center. AU five inlets shared the same external compression surface; they differed only in subsonic diffuser geometry. The external compression surface used an isentropic relaxed compression design developed by Gulfstream Aerospace Corporation. Steady-state pressure data were recorded on the inlet centerbody, on the cowl, and at two pitot pressure rakes located at the aerodynamic interface plane (AIP). High frequency dynamic pressure data were recorded at one static pressure tap on the inlet centerbody and at a pitot probe on the AIP. Schlieren images were also recorded. This paper analyzes the dynamic pressure data from three of the inlet models.

Original languageEnglish (US)
Title of host publicationCollection of Technical Papers - 43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference
Pages762-783
Number of pages22
StatePublished - Dec 10 2007
Event43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference - Cincinnati, OH, United States
Duration: Jul 8 2007Jul 11 2007

Publication series

NameCollection of Technical Papers - 43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference
Volume1

Other

Other43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference
CountryUnited States
CityCincinnati, OH
Period7/8/077/11/07

Fingerprint

centerbodies
dynamic pressure
wind tunnels
dynamic analysis
wind tunnel
aerodynamics
supersonic wind tunnels
compression
rakes
static pressure
diffusers
taps
probes
geometry
probe

ASJC Scopus subject areas

  • Space and Planetary Science

Cite this

Tacina, K. M., Hirt, S. M., Conners, T. R., Merret, J. M., & Howe, D. C. (2007). Dynamic analysis of wind tunnel data from an isentropic relaxed compression inlet. In Collection of Technical Papers - 43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference (pp. 762-783). (Collection of Technical Papers - 43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference; Vol. 1).

Dynamic analysis of wind tunnel data from an isentropic relaxed compression inlet. / Tacina, Kathleen M.; Hirt, Stefanie M.; Conners, Timothy R.; Merret, Jason M; Howe, Donald C.

Collection of Technical Papers - 43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference. 2007. p. 762-783 (Collection of Technical Papers - 43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference; Vol. 1).

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

Tacina, KM, Hirt, SM, Conners, TR, Merret, JM & Howe, DC 2007, Dynamic analysis of wind tunnel data from an isentropic relaxed compression inlet. in Collection of Technical Papers - 43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference. Collection of Technical Papers - 43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference, vol. 1, pp. 762-783, 43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference, Cincinnati, OH, United States, 7/8/07.
Tacina KM, Hirt SM, Conners TR, Merret JM, Howe DC. Dynamic analysis of wind tunnel data from an isentropic relaxed compression inlet. In Collection of Technical Papers - 43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference. 2007. p. 762-783. (Collection of Technical Papers - 43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference).
Tacina, Kathleen M. ; Hirt, Stefanie M. ; Conners, Timothy R. ; Merret, Jason M ; Howe, Donald C. / Dynamic analysis of wind tunnel data from an isentropic relaxed compression inlet. Collection of Technical Papers - 43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference. 2007. pp. 762-783 (Collection of Technical Papers - 43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference).
@inproceedings{f0957703bf8040c896b66014f5cf596d,
title = "Dynamic analysis of wind tunnel data from an isentropic relaxed compression inlet",
abstract = "A family of five axisymmetric external compression inlets was tested at Mach 1.97 in the 1-ft × 1-ft supersonic wind tunnel at the NASA Glenn Research Center. AU five inlets shared the same external compression surface; they differed only in subsonic diffuser geometry. The external compression surface used an isentropic relaxed compression design developed by Gulfstream Aerospace Corporation. Steady-state pressure data were recorded on the inlet centerbody, on the cowl, and at two pitot pressure rakes located at the aerodynamic interface plane (AIP). High frequency dynamic pressure data were recorded at one static pressure tap on the inlet centerbody and at a pitot probe on the AIP. Schlieren images were also recorded. This paper analyzes the dynamic pressure data from three of the inlet models.",
author = "Tacina, {Kathleen M.} and Hirt, {Stefanie M.} and Conners, {Timothy R.} and Merret, {Jason M} and Howe, {Donald C.}",
year = "2007",
month = "12",
day = "10",
language = "English (US)",
isbn = "1563479036",
series = "Collection of Technical Papers - 43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference",
pages = "762--783",
booktitle = "Collection of Technical Papers - 43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference",

}

TY - GEN

T1 - Dynamic analysis of wind tunnel data from an isentropic relaxed compression inlet

AU - Tacina, Kathleen M.

AU - Hirt, Stefanie M.

AU - Conners, Timothy R.

AU - Merret, Jason M

AU - Howe, Donald C.

PY - 2007/12/10

Y1 - 2007/12/10

N2 - A family of five axisymmetric external compression inlets was tested at Mach 1.97 in the 1-ft × 1-ft supersonic wind tunnel at the NASA Glenn Research Center. AU five inlets shared the same external compression surface; they differed only in subsonic diffuser geometry. The external compression surface used an isentropic relaxed compression design developed by Gulfstream Aerospace Corporation. Steady-state pressure data were recorded on the inlet centerbody, on the cowl, and at two pitot pressure rakes located at the aerodynamic interface plane (AIP). High frequency dynamic pressure data were recorded at one static pressure tap on the inlet centerbody and at a pitot probe on the AIP. Schlieren images were also recorded. This paper analyzes the dynamic pressure data from three of the inlet models.

AB - A family of five axisymmetric external compression inlets was tested at Mach 1.97 in the 1-ft × 1-ft supersonic wind tunnel at the NASA Glenn Research Center. AU five inlets shared the same external compression surface; they differed only in subsonic diffuser geometry. The external compression surface used an isentropic relaxed compression design developed by Gulfstream Aerospace Corporation. Steady-state pressure data were recorded on the inlet centerbody, on the cowl, and at two pitot pressure rakes located at the aerodynamic interface plane (AIP). High frequency dynamic pressure data were recorded at one static pressure tap on the inlet centerbody and at a pitot probe on the AIP. Schlieren images were also recorded. This paper analyzes the dynamic pressure data from three of the inlet models.

UR - http://www.scopus.com/inward/record.url?scp=36749082346&partnerID=8YFLogxK

UR - http://www.scopus.com/inward/citedby.url?scp=36749082346&partnerID=8YFLogxK

M3 - Conference contribution

AN - SCOPUS:36749082346

SN - 1563479036

SN - 9781563479038

T3 - Collection of Technical Papers - 43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference

SP - 762

EP - 783

BT - Collection of Technical Papers - 43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference

ER -