Comparisons of Measured and Modeled Aero-thermal Distributions for Complex Hypersonic Configurations. Sagerman, D., G., Dasque, N., Rumpfkeil, M., P., & Hellman, B. In AIAA Scitech 2017 Forum, 2017. ![Comparisons of Measured and Modeled Aero-thermal Distributions for Complex Hypersonic Configurations [pdf]](https://bibbase.org/img/filetypes/pdf.svg "pdf")
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Website doi abstract bibtex The ability to quickly and accurately predict the thermal signature of a complex geometry is important in the early design stages for any aircraft. Due to the lack of hypersonic facilities with this capability, a recent effort has been made to quantify the ability of the Mach 6 tunnel at Wright-Patterson Air Force Base (WPAFB) for this task. The Mach 6 High Reynolds Number Facility at WPAFB in Dayton, Ohio, has been non-operational for the past twenty years, but a recent resurgence in the need for hypersonic test facilities has led to the reactivation of the tunnel. With its restoration, the facility is to include new capabilities to assess hypersonic aero-thermodynamic effects on bodies in Mach 6 flow. Using temperature sensitive paint (TSP) and three complex geometries commonly used in the hypersonic community, experimental tests were conducted inside the Mach 6 tunnel to capture the temperature contours and some pressure data for these geometries at various angles of attack. These results were then compared to numerical analyses conducted using the panel code CBAero, the Euler code Cart3D, the coupled Euler/Boundary layer solver UNLATCH, and Navier-Stokes solutions from FUN3D. Due to the experiments in the tunnel never reaching steady state since paint adherence was affected after about 10 seconds in the high-speed flow, the comparison to steady numerical analysis proved difficult. As a result, the capabilities of the Mach 6 tunnel, in terms of having a quantifiable measure between the experimental and numerical temperature distributions, could not be assessed and instead general qualitative comparisons were made. Nomenclature a Speed of sound α or AOA Angle of attack C D Drag coefficient C L Lift coefficient C M Pitching moment coefficient C p Pressure coefficient M Mach number T Temperature [Kelvin] ρ Density
@inproceedings{
title = {Comparisons of Measured and Modeled Aero-thermal Distributions for Complex Hypersonic Configurations},
type = {inproceedings},
year = {2017},
websites = {http://arc.aiaa.org},
city = {Grapevine, TX},
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abstract = {The ability to quickly and accurately predict the thermal signature of a complex geometry is important in the early design stages for any aircraft. Due to the lack of hypersonic facilities with this capability, a recent effort has been made to quantify the ability of the Mach 6 tunnel at Wright-Patterson Air Force Base (WPAFB) for this task. The Mach 6 High Reynolds Number Facility at WPAFB in Dayton, Ohio, has been non-operational for the past twenty years, but a recent resurgence in the need for hypersonic test facilities has led to the reactivation of the tunnel. With its restoration, the facility is to include new capabilities to assess hypersonic aero-thermodynamic effects on bodies in Mach 6 flow. Using temperature sensitive paint (TSP) and three complex geometries commonly used in the hypersonic community, experimental tests were conducted inside the Mach 6 tunnel to capture the temperature contours and some pressure data for these geometries at various angles of attack. These results were then compared to numerical analyses conducted using the panel code CBAero, the Euler code Cart3D, the coupled Euler/Boundary layer solver UNLATCH, and Navier-Stokes solutions from FUN3D. Due to the experiments in the tunnel never reaching steady state since paint adherence was affected after about 10 seconds in the high-speed flow, the comparison to steady numerical analysis proved difficult. As a result, the capabilities of the Mach 6 tunnel, in terms of having a quantifiable measure between the experimental and numerical temperature distributions, could not be assessed and instead general qualitative comparisons were made. Nomenclature a Speed of sound α or AOA Angle of attack C D Drag coefficient C L Lift coefficient C M Pitching moment coefficient C p Pressure coefficient M Mach number T Temperature [Kelvin] ρ Density},
bibtype = {inproceedings},
author = {Sagerman, Denton G and Dasque, Nastassja and Rumpfkeil, Markus P and Hellman, Barry},
doi = {10.2514/6.2017-0264},
booktitle = {AIAA Scitech 2017 Forum}
}
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