Freestream disturbance effects on boundary layer instability and transition on the afosr bolt geometry

Heather E. Kostak, Rodney D.W. Bowersox, Gregory R. McKiernan, John Thome, Graham V Candler, Rudolph A. King

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

Abstract

The Air Force Office of Scientific Research (AFOSR) introduced the Boundary Layer Transition (BOLT) flight experiment to assess modern prediction via simulation and ground test. The BOLT test article is a new, complex geometry that involves concave surfaces with highly swept leading edges. This paper compares preliminary results on the same subscale model tested in four hypersonic wind tunnel facilities. Tests were performed in the Boeing/AFOSR Mach 6 Quiet Tunnel at Purdue University, the conventional 20-inch Mach 6 Air tunnel at NASA Langley Research Center, and the conventional ACE and Mach 6 Quiet wind tunnels at Texas A&M University. The measurements across the facilities included thermal imaging and surface mounted high-frequency pressure transducers. University of Minnesota’s CFD analyses of the BOLT geometry were compared to the quiet flow facilities. Systematic similarities and differences were observed in terms of surface heating, stationary streaks, and modal growth.

Original languageEnglish (US)
Title of host publicationAIAA Scitech 2019 Forum
PublisherAmerican Institute of Aeronautics and Astronautics Inc, AIAA
ISBN (Print)9781624105784
DOIs
StatePublished - Jan 1 2019
EventAIAA Scitech Forum, 2019 - San Diego, United States
Duration: Jan 7 2019Jan 11 2019

Publication series

NameAIAA Scitech 2019 Forum

Conference

ConferenceAIAA Scitech Forum, 2019
CountryUnited States
CitySan Diego
Period1/7/191/11/19

Fingerprint

Bolts
Mach number
Boundary layers
Wind tunnels
Geometry
Tunnels
Air
Pressure transducers
Hypersonic aerodynamics
Infrared imaging
NASA
Computational fluid dynamics
Heating
Experiments

Cite this

Kostak, H. E., Bowersox, R. D. W., McKiernan, G. R., Thome, J., Candler, G. V., & King, R. A. (2019). Freestream disturbance effects on boundary layer instability and transition on the afosr bolt geometry. In AIAA Scitech 2019 Forum (AIAA Scitech 2019 Forum). American Institute of Aeronautics and Astronautics Inc, AIAA. https://doi.org/10.2514/6.2019-0088

Freestream disturbance effects on boundary layer instability and transition on the afosr bolt geometry. / Kostak, Heather E.; Bowersox, Rodney D.W.; McKiernan, Gregory R.; Thome, John; Candler, Graham V; King, Rudolph A.

AIAA Scitech 2019 Forum. American Institute of Aeronautics and Astronautics Inc, AIAA, 2019. (AIAA Scitech 2019 Forum).

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

Kostak, HE, Bowersox, RDW, McKiernan, GR, Thome, J, Candler, GV & King, RA 2019, Freestream disturbance effects on boundary layer instability and transition on the afosr bolt geometry. in AIAA Scitech 2019 Forum. AIAA Scitech 2019 Forum, American Institute of Aeronautics and Astronautics Inc, AIAA, AIAA Scitech Forum, 2019, San Diego, United States, 1/7/19. https://doi.org/10.2514/6.2019-0088
Kostak HE, Bowersox RDW, McKiernan GR, Thome J, Candler GV, King RA. Freestream disturbance effects on boundary layer instability and transition on the afosr bolt geometry. In AIAA Scitech 2019 Forum. American Institute of Aeronautics and Astronautics Inc, AIAA. 2019. (AIAA Scitech 2019 Forum). https://doi.org/10.2514/6.2019-0088
Kostak, Heather E. ; Bowersox, Rodney D.W. ; McKiernan, Gregory R. ; Thome, John ; Candler, Graham V ; King, Rudolph A. / Freestream disturbance effects on boundary layer instability and transition on the afosr bolt geometry. AIAA Scitech 2019 Forum. American Institute of Aeronautics and Astronautics Inc, AIAA, 2019. (AIAA Scitech 2019 Forum).
@inproceedings{105d755ae65745138a3fa7e2332ab958,
title = "Freestream disturbance effects on boundary layer instability and transition on the afosr bolt geometry",
abstract = "The Air Force Office of Scientific Research (AFOSR) introduced the Boundary Layer Transition (BOLT) flight experiment to assess modern prediction via simulation and ground test. The BOLT test article is a new, complex geometry that involves concave surfaces with highly swept leading edges. This paper compares preliminary results on the same subscale model tested in four hypersonic wind tunnel facilities. Tests were performed in the Boeing/AFOSR Mach 6 Quiet Tunnel at Purdue University, the conventional 20-inch Mach 6 Air tunnel at NASA Langley Research Center, and the conventional ACE and Mach 6 Quiet wind tunnels at Texas A&M University. The measurements across the facilities included thermal imaging and surface mounted high-frequency pressure transducers. University of Minnesota’s CFD analyses of the BOLT geometry were compared to the quiet flow facilities. Systematic similarities and differences were observed in terms of surface heating, stationary streaks, and modal growth.",
author = "Kostak, {Heather E.} and Bowersox, {Rodney D.W.} and McKiernan, {Gregory R.} and John Thome and Candler, {Graham V} and King, {Rudolph A.}",
year = "2019",
month = "1",
day = "1",
doi = "10.2514/6.2019-0088",
language = "English (US)",
isbn = "9781624105784",
series = "AIAA Scitech 2019 Forum",
publisher = "American Institute of Aeronautics and Astronautics Inc, AIAA",
booktitle = "AIAA Scitech 2019 Forum",

}

TY - GEN

T1 - Freestream disturbance effects on boundary layer instability and transition on the afosr bolt geometry

AU - Kostak, Heather E.

AU - Bowersox, Rodney D.W.

AU - McKiernan, Gregory R.

AU - Thome, John

AU - Candler, Graham V

AU - King, Rudolph A.

PY - 2019/1/1

Y1 - 2019/1/1

N2 - The Air Force Office of Scientific Research (AFOSR) introduced the Boundary Layer Transition (BOLT) flight experiment to assess modern prediction via simulation and ground test. The BOLT test article is a new, complex geometry that involves concave surfaces with highly swept leading edges. This paper compares preliminary results on the same subscale model tested in four hypersonic wind tunnel facilities. Tests were performed in the Boeing/AFOSR Mach 6 Quiet Tunnel at Purdue University, the conventional 20-inch Mach 6 Air tunnel at NASA Langley Research Center, and the conventional ACE and Mach 6 Quiet wind tunnels at Texas A&M University. The measurements across the facilities included thermal imaging and surface mounted high-frequency pressure transducers. University of Minnesota’s CFD analyses of the BOLT geometry were compared to the quiet flow facilities. Systematic similarities and differences were observed in terms of surface heating, stationary streaks, and modal growth.

AB - The Air Force Office of Scientific Research (AFOSR) introduced the Boundary Layer Transition (BOLT) flight experiment to assess modern prediction via simulation and ground test. The BOLT test article is a new, complex geometry that involves concave surfaces with highly swept leading edges. This paper compares preliminary results on the same subscale model tested in four hypersonic wind tunnel facilities. Tests were performed in the Boeing/AFOSR Mach 6 Quiet Tunnel at Purdue University, the conventional 20-inch Mach 6 Air tunnel at NASA Langley Research Center, and the conventional ACE and Mach 6 Quiet wind tunnels at Texas A&M University. The measurements across the facilities included thermal imaging and surface mounted high-frequency pressure transducers. University of Minnesota’s CFD analyses of the BOLT geometry were compared to the quiet flow facilities. Systematic similarities and differences were observed in terms of surface heating, stationary streaks, and modal growth.

UR - http://www.scopus.com/inward/record.url?scp=85068458548&partnerID=8YFLogxK

UR - http://www.scopus.com/inward/citedby.url?scp=85068458548&partnerID=8YFLogxK

U2 - 10.2514/6.2019-0088

DO - 10.2514/6.2019-0088

M3 - Conference contribution

AN - SCOPUS:85068458548

SN - 9781624105784

T3 - AIAA Scitech 2019 Forum

BT - AIAA Scitech 2019 Forum

PB - American Institute of Aeronautics and Astronautics Inc, AIAA

ER -