Fundamental physics experiments increase our understanding of more complex problems and provide important data for improving and validating physical models.
Fundamental Inlet Bleed Experiments (FIBE)
Accurate prediction of bleed flow models relies heavily upon understanding how the bleed orifice flow coefficient changes based on operating conditions.
A series of fundamental inlet bleed experiments were conducted at NASA’s Glenn Research Center. This work’s goals were to provide a comprehensive experimental database and a better understanding of how bleed systems can be improved through better modeling, alternate bleed configurations, and bleed placement within supersonic and hypersonic inlets.
The Phase I experiment obtained flow coefficient data for 90 and 20-degree single bleed holes.
- Davis, D.O., et al., “Research on Supersonic Inlet Bleed,” NASA TM 2012-217620, Aug 2012. Also AIAA-2012-0272.
The Phase II experiment obtained flow coefficient data for 21 configurations of a single bleed hole. Interactions between the design parameters of hole diameter, hole inclination angle, and thickness-to-diameter and the interactions between the flow parameters of pressure ratio and Mach number upon the flow coefficient were examined, and a preliminary statistical model was developed.
- Eichorn, M.B., et al., “Effect of Boundary-Layer Bleed Hole Inclination Angle and Scaling on Flow Coefficient Behavior,” NASA TM 2013-217843, Feb 2013. Also AIAA-2013-0424.
Microramp/Microvane Flow Control
A combination of experimental and numerical work has been conducted at NASA’s Glenn Research Center to determine the effectiveness of microramp and microvane flow control devices on shock-wave boundary-layer interaction.
- Hirt, S.M., et al., “Experimental Investigation of the Application of Microramp Flow Control to an Oblique Shock Interaction,” NASA/TM-2009-215630, Nov 2009. Also AIAA-2009-919.
- Hirt, S.M., et al., “Micro-Ramp Flow Control for Oblique Shock Interactions: Comparisons of Computational and Experimental Data,” NASA/TM-2012-217242, Aug 2012. Also AIAA-2010-4973.
- Hirt, S.M., et al., “Experimental Study of Boundary Layer Flow Control Using an Array of Ramp-Shaped Vortex Generators,” NASA/TM-2012-217616, Aug 2012. Also AIAA-2012-741.
- Vyas, M.A., et al.,“Experimental Investigation of Normal Shock Boundary-Layer Interaction with Hybrid Flow Control,” AIAA-2012-0048, Jan 2012.
- Zaman, K.B.M.Q, et al., “Boundary Layer Flow Control by an Array of Ramp-Shaped Vortex Generators,” NASA/TM-2012-217437, Apr 2012.
- Hirt, S.M., and Vyas M.A., “Effects of Hybrid Flow Control on a Normal Shock Boundary-Layer Interaction,” AIAA-2013-0014, Jan 2013.
Mixing Layer Experiments
NASA has funded a series of compressible planar mixing layer experiments to obtain high-quality data for turbulence model validation. This database is available to all.
- Dutton, J.C., Elliott, G.S., and Kim, K., “Compressible Mixing Layer Experiments for CFD Validation,” AIAA-2019-2847, Jun 2019.
Turbulent Heat Flux (THX) Thermal Mixing
A number of benchmark turbulent heat transport experiments were performed at NASA’s Glenn Research Center. Detailed measurements of velocity and temperature were obtained. This data will be used to validate and improve turbulence models for thermal mixing flows.
The Phase I test investigated measurement techniques within a small-scale tunnel cooling flow configuration.
- Wernet, M.P., “A Dual-Plane PIV Study of Turbulent Heat Transfer Flows,” NASA/TM-2016-219074, Mar 2016.
The Phase II test investigated thermal transport within a subsonic axisymmetric jet.
- Locke, R.J., et al., “Rotational Raman-Based Temperature Measurements in a High-Velocity Turbulent Jet,” NASA/TM-2017-219504/REV1, Dec 2017.
The Phase III test involved a single large injector cooling hole to study fundamental physics.
- Wernet, M.P., et al., “PIV and Rotational Raman-Based Temperature Measurements for CFD Validation in a Single Injector Cooling Flow,” NASA/TM-2018-219739 (Corrected Copy), Sep 2019.
The Phase IV test involved three patches of smaller cooling holes in a staggered pattern representative of a realistic application. This multi-hole configuration is the focus of the 2021 AIAA Propulsion Aerodynamic Workshop.
- Wernet, M.P., et al., “PIV and Rotational Raman-Based Temperature Measurements for CFD Validation of a Perforated Cooling Flow – Part 1,” NASA TM 2019-220227/Part1/Rev1, Mar 2020.
The Phase V test investigated the turbulent heat transport within a supersonic axisymmetric jet.
- Report to be published soon.
Axisymmetric Shock-Wave Boundary-Layer Interaction (SWBLI)
Shock-wave boundary-layer interaction is prominent in supersonic inlets, yet high-quality validation data is difficult to find. Documenting experiments performed in rectangular wind tunnels can be quite challenging due to the three-dimensional interaction that occurs in the corner regions. To overcome this issue, an experiment was conducted at NASA’s Glenn Research Center using an axisymmetric configuration. The data obtained will be used to improve numerical simulations further.
- Davis, D.O., “CFD Validation Experiment of a Mach 2.5 Axisymmetric Shock-Wave/Boundary-Layer Interaction,” NASA TM-2015-218841, Sep 2015.