Hypersonic Materials Challenges

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1 Hypersonic Aerothermochemistry Research Hypersonic Materials Challenges Rodney Bowersox Texas A&M University, College Station, TX May, 2016 College Station, Texas

2 Outline Introduction Laboratory Challenges Acknowledgment Sponsors: AFOSR, AFRL, NASA, NSF, ONR and Private Industry

3 Introduction - Hypersonic Material Challenges - Ablation Excessive thermal loading Viscous effects Shock boundary layer interactions Laminar Transitional Turbulent Cross-hatched roughness Fine-scale roughness Larson and Nachtsheim, NASA 1970.

4 Introduction - Hypersonic Scientific Challenges - Hypersonic viscous flows include: Mechanical nonequilibrium Thermal nonequilibrium Chemical nonequilibrium Fluid-surface coupling Beyond full physics based model free simulations y 0 u e, T e, Y (n)e Thermal Boundary Layer Thickness Velocity Boundary Layer Thickness Hot Gaseous Turbulent Boundary Layer Gas Interface Liquid Layer Solid-Liquid Interface Solid Surface (ρv) w (ρv) L q w q S u = u e Surface Roughness M = 5 T = T e T = T melt x

National Aerothermochemistry Laboratory Team: R. Bowersox, D.

Ejector Hypersonic Boundary Layer Stability and Transition High

5MW Heater Bldg 1268 M6QT BLOW-DOWN TUNNELS ACE Tunnel Laminar

LAB 1 VENOM SHR Tunnel VENOM Bldg 1268a Thermal & Chemical

5 National Aerothermochemistry Laboratory Team: R. Bowersox, D. Donzis, S. North, H. Reed, W. Saric, E. White Established: 2004 by R. Bowersox Sponsors: AFOSR, AFRL, NASA, NSF, ONR and Industry Vacuum Ejector Hypersonic Boundary Layer Stability and Transition High Pressure Air Supply 0.5MW Heater Bldg 1268 M6QT BLOW-DOWN TUNNELS ACE Tunnel Laminar Flame Fac. LAB 1 VENOM SHR Tunnel VENOM Bldg 1268a Thermal & Chemical Non-equilibrium Hypersonic Turbulent Flows Loft with student offices CONTROL ROOM Bldg 1271 INSTRUMENTATION AND MODEL ASSEMBLY Facilities Vent Hood LAB 2 HYPERVELOCITY RESEARCH TUNNEL PULSED HYPERSONIC TUNNELS Hypervelocity Flows Diagnostic Development

NAL - Facilities Facility Name Mach # Test Sec2on Unit Re [10 6 /m] NASA Langley Mach 6 Quiet Tunnel (M6QT) AcJvely-Controlled Expansion (ACE) Tunnel Hypervelocity Research Tunnel (HXT) 5.9 18.

6 NAL - Facilities Facility Name Mach # Test Sec2on Unit Re [10 6 /m] NASA Langley Mach 6 Quiet Tunnel (M6QT) AcJvely-Controlled Expansion (ACE) Tunnel Hypervelocity Research Tunnel (HXT) cm dia 3 11 (quiet) 5 8 Supersonic High-Reynolds Tunnel (SHR) 2.2, 3.0, or 5.0 RepeJJvely Pulsed Hypersonic Test Cells cm 35.6 cm cm dia cm 7.6 cm 2.8 cm, 5.1 cm 10.2 cm x 10.2 cm Up to Run Time / Duty Cycle 40 sec / 2.5 hrs 40 sec / 2.5 hrs ms/ 3 hrs 30 min / 2.5 hrs Hz Mach 6 QT ACE tunnel VENOM2 Pulsed Tunnels SHR HXT

NAL - Instrumentation Advanced diagnostics are used to quantify flow properties ranging from non equilibrium molecular effects to fundamental hydrodynamics Laser/Optical based diagnostics Particle

7 NAL - Instrumentation Advanced diagnostics are used to quantify flow properties ranging from non equilibrium molecular effects to fundamental hydrodynamics Laser/Optical based diagnostics Particle Image Velocimetry (PIV) Vibrationally-excited NO Monitoring (VENOM) Molecular Tagging Velocimetry (MTV) Planar Laser-Induced Fluorescence (PLIF) Dual Plane Coherent Anti-Stokes Raman Spectroscopy (CARS) Raman and Emission Spectroscopy Pressure/Temperature sensitive paint (PSP) Focusing schlieren w/ deflectometry Infrared thermography Conventional Diagnostics Photodissocia;on$laser$2$ Pulse/delay$2$ Multiple-overheat hot-wire anemometry (HWA) Kulite and PCB Pressure Transducers SFM$3$ YAG$2$ YAG$1$ Probe$laser$system$2$ SFM$4$ DYE$3$ Probe$laser$system$2$ DYE$4$ Probe$laser$system$1$ YAG$3$ DYE$2$ DYE$1$ Probe$laser$system$4$ YAG$4$ SFM$2$ SFM$1$ Pulse/delay$1$ Photodissocia;on$laser$1$

Hypersonic Transition Studies Roadmap Semper, M =

Gas Effects Flared cone in M6QT 2nd Mode,

and Bowersox Axisymmetric Cone at AoA in M6QT 3D

Cone Traveling mode in ACE Kimmel, Borg, Bowersox

Bowersox and Reed Flat Plate Trip growth rates

roughness growth Rates in M6QT White Blunt body

NEXT STEPS HIFIRE&5&in&ACE&at&M&=&6& Base of

5 0 1 10 100 1000 10000 y + Hofferth et al AIAA

8 Hypersonic Transition Studies Roadmap Semper, M = 5.7, Re = 3600 Peltier, M = 4.9, Re = Tichenor, M = 4.9, Re = nd Mode Cross-flow Bypass Real Gas Effects Flared cone in M6QT 2nd Mode, adiabatic Saric Cold wall breakdown in M6QT Saric and Bowersox Axisymmetric Cone at AoA in M6QT 3D cross-flow measurements Saric HiFIRE-5 Elliptic Cone Traveling mode in ACE Kimmel, Borg, Bowersox Environmental disturbance effects in ACE and M6QT Bowersox and Reed Flat Plate Trip growth rates and transition in ACE - Bowersox Cone nose-tip roughness growth Rates in M6QT White Blunt body transient growth in ACE Reshotko and Bowersox NEXT STEPS HIFIRE&5&in&ACE&at&M&=&6& Base of flare 4 aft of exit plane u eff y + Hofferth et al AIAA Paper 2010; Borg et al AIAA Paper 2015; Semper and Bowersox AIAA J (in review); Leidy et al AIAA Paper 2016.

Turbulence Studies Roadmap Equilibrium Mechanical Non- Equilibrium Thermal Non- Equilibrium Chemical Non- Equilibrium Modeling Second order

Modeling Second order transport equations derived Algebraic model with MNE Pressure gradient effect on Reynolds analogy explained Demonstrated

developed Investigate molecular exchange mechanisms (AFOSR) Modeling Second order transport equations derived Low order heat flux model with CNE

Low- Re effects Quantified Low Re Tripped flow in ACE (NASA Pizza Box) Quantified instability growth FPG/roughness effects (M=3,5)

with vibrational TNE Demonstrated increased rate of relaminarization w/ plasma TNE àmne Mach 7 Plasma TNE (AFOSR) True Enthalpy Non- Equilibrium

Modeling 1.6 1.2 Watson (1978) Present Theory M % =%5% M = 5 y/d 0.8 0.4 0.0 0.0 4.0 8.0 12.0 Mach No. dp/dx%<%0%!%decrease% in%reynolds%stress%!

9 Turbulence Studies Roadmap Equilibrium Mechanical Non- Equilibrium Thermal Non- Equilibrium Chemical Non- Equilibrium Modeling Second order transport equations derived Algebraic heat flux model Validated over M = Established near wall scaling for the turbulent Prandtl No. Modeling Second order transport equations derived Algebraic model with MNE Pressure gradient effect on Reynolds analogy explained Demonstrated applicability of second order modeling for FPG Demonstrate for APG Modeling Second order transport equations derived Algebraic model with TNE developed Investigate molecular exchange mechanisms (AFOSR) Modeling Second order transport equations derived Low order heat flux model with CNE Generalize modeling framework Quantified and characterized underlying flow structure for a high Re Mach 3 & 5 BL in SHR Characterized High Mach, Low- Re effects Quantified Low Re Tripped flow in ACE (NASA Pizza Box) Quantified instability growth FPG/roughness effects (M=3,5) Shock-turbulence interaction APG effects at M = 5 Shock BL Interaction (ONR) Turbulent heat flux (VENOM) Quantified subcritical channel flow with vibrational TNE Demonstrated increased rate of relaminarization w/ plasma TNE àmne Mach 7 Plasma TNE (AFOSR) True Enthalpy Non- Equilibrium High temperature Bls to validate modeling Include MNE effects Supersonic Combustion Flows Demonstrate VENOM/ VENOM2 in combusting flow Validate Modeling Watson (1978) Present Theory M % =%5% M = 5 y/d Mach No. dp/dx%<%0%!%decrease% in%reynolds%stress%!"#$%$&'($ $!"#$%$&')$ M = 6 Re/m = 2 x 10 6 Bowersox, JFM 2009; Tichenor et al JFM 2013; Peltier et al Phys. Fluids, 2014; Mai et al, AIAA Paper 2014; Fuller et al JFM 2014.

Current NAL Projects Hypersonic Thermal and Mechanical Loading Stability

cooled cone in M6QT Transient Growth on Orion Capsule Turbulent Flow

nonequilibrium Mechanical nonequilibrium Diagnostic Development Laser

10 Current NAL Projects Hypersonic Thermal and Mechanical Loading Stability and Transition 3D Crossflow on HIFIRE-5 2:1 Elliptic Cone 2 nd Mode on cooled cone in M6QT Transient Growth on Orion Capsule Turbulent Flow Reynolds shear stress and turbulent heat flux modeling Thermal nonequilibrium Mechanical nonequilibrium Diagnostic Development Laser based thermometry and velocimetry Facility Development High Enthalpy Hypervelocity Tunnel

11 Challenges Simulation is beyond a full physics based approach Dearth of empirical data for model development and validation Thermal Environment (Freestream) Chemical Environment (Surface Chemistry) Shear Environment (Roughness Effects) High enthalpy facilities with sufficient run time and accurate freestream chemistry do not exist.

Hypersonics T&E: A University Approach

Hypersonics T&E: A University Approach Dr. Nathan Tichenor and Dr. Rodney Bowersox NDIA 32nd Annual National Test & Evaluation Conference March 7, 2016 San Diego, CA 1 WHY HYPERSONICS T&E? The underlying