National Center for Hypersonic Combined Cycle Propulsion Update Presentation on June 16 th , 2011

1. Hypervelocity Combustion Regime PIs: Dan Cresci, Ron Hanson, Jack Edwards, Chris Goyne Research Staff: C.Y. Tsai, Jay Jeffries Graduate Students: Michael Smayda, Ian Schultz, Chris Goldenstein, Patrick Vogel AFSOR-NASA Hypersonics Fundamental Research Review National Center for Hypersonic Combined Cycle Propulsion Update Presentation on June 16th, 2011

2. Outline • Goals and Objectives • Approach • Roadmap • Test Plan • Analysis Plan • Schedule • Research results • Experiments • Diagnostics • Modeling • Collaboration • Questions

3. Goals and Objectives

4. Experimental Focus Areas • Focus Area 1 • Measurement of reacting flow turbulence statistics and novel fuel-air mixing and flame holding schemes through the development and application of advanced diagnostics • implement the Tunable diode laser absorption spectroscopy (TDLAS) measurements of temperature, velocity, pressure and several species (H2O, O2, CO2 and selected hydrocarbons) in HYPULSE for measurement in the pulsed, hypervelocity facility • Focus Area 2 • Development of benchmark data sets with quantified experimental uncertainty for the purposes of developing accurate RANS, hybrid LES/RANS, and LES models • extend the experimental data set to Mach 7 and Mach 10 • generate quantitative data sets for model development/validation

5. Experimental Focus Areas

6. Approach

7. Roadmap • Hypervelocity Regime • Mach 5 - 10 2009 2010 2011 2012 2013 2014 Design model Define diagnostics • Build/install model • Mach 5 testing Experiments • Mach 7 testing Mach 10 testing Dual Mode Exp. TDLAS/wall pressures and temperatures/flow visualization Define diagnostics Diagnostics Modeling RANS RANS/LES-RANS

8. Test Plan • Test Facility • HyPulse Reflected Shock Tunnel (RST) Operation • Nozzles: AR 35 for Mach 5, AR175 for Mach 7, and AR225 for Mach 10 • Test Article • Hy-V Engine-A Flowpath • New cowl piece with side wall windows, optical access and heat flux measurements on top wall • Instrumentation • PCB, heat flux gauge, schlieren, fuel plume image • TDLAS • Test Conditions • Mach 5-q1500 psf: dry air, Tt=2230 R, Mn=5.2, test time= 12 ms • Mach 7-q1000 psf: dry air, Tt= 3850 R, Mn=7.3, test time= 6 ms • Mach 10-q1000 psf: dry air, Tt= 6950 R, Mn=6.9, test time= 3 ms • Fuel: Silane Fuel Mixture (20%SiH4-80% H2 by volume); ER= 0 to 0.6

9. Analysis Plan(Experimental Data Sets to be Acquired for Model Development/Validation) • Raw Data • Axial pressure profile at body wall centerline • Axial heat flux profile at cowl wall centerline • Schlieren images at isolator and combustor (Mach 7 & 10 only) • FPI (Fuel Plume Image) at combustor centerline • Vertical profile of PIW (Path Integrated Water) concentration and temperature at selected axial locations • Reduced Data • Fuel jet penetration • Axial mixing efficiency profile • Axial combustion efficiency profile • For CFD Model Validation • Turbulence model: pressure data, temperature & heat flux profiles; separation; shock pattern; boundary layer thickness • Mixing/Ignition model: mixing/combustion efficiency • Combustion chemistry/kinetics: combustion efficiency

10. Schedule

11. Schedule • Year 1 (8/1/09 – 7/31/10) • Establish test objectives • Define diagnostics requirements • Define test configuration (adapting existing hardware) • Collaborate with diagnostic team • Define diagnostic plan • Based on current test series, additional diagnostics point will be determined and incorporated • Year 2 (8/1/10 – 7/31/11) • Design • Fabrication • Instrumentation        In Progress In Progress

12. Schedule (continued) • Year 3 (8/1/11 – 7/31/12) • Model installation • Checkouts • Testing series #1 (~1 month) • Year 4 (8/1/12 – 7/31/13) • Testing series #2 (~1 month) • Year 5 (8/1/13 – 7/31/14) • Testing series #3 (~1 month)

13. Research ResultsExperiments

14. Hypulse Test Facility • The NASA HYPULSE facility at GASL has been used for various airbreathing propulsion tests • Multi-mode facility operations allow simulations from Mach 5 to 25 in a single facility with rapid turn around time • Short duration nature allows uncooled hardware • Agreement between X43 flight and HYPULSE data has validated the use of pulse test technique for aeropropulsion testing Hyper-X Scramjet Model Mach 7, 10, 15 GASL 6.5” Dia. Mach 8 Gun-Launched Projectile NASA GTX Mach 7, 10

15. Leverage SDPTE (Hy-V) Program 1 2 3 4 5 DMSJ flowpath geometries for a) original University of Virginia direct connect rig and b) Hypulse Flowpath A

16. Leverage SDPTE (Hy-V) Program Prediction of Flight Performance - Thrust - Combustor pressure - Isolator pressure - Inlet operability - Heat flux • Resolve ground testing issues related to the duration of the test flow and related to test medium effects on dual-mode scramjet engine performance TBIV • UVa Direct-connect tests • Long duration • Clean & vitiated HYPULSE • ATK Ground Tests • Medium & short duration • Clean & vitiated • Flight • Medium duration • Atmospheric air

17. Leverage SDPTE (Hy-V) Program • Engine tests at Mach 5 &7 conditions have been completed • Test rig is currently available and has been disassembled awaiting cowl modifications

18. Leverage SDPTE (Hy-V) Program • SDPTE Program conducted by UVa, ATK GASL and Va Tech. • Funded by APTT Program, TRMC M5 Facility Nozzle Test Article Jet Stretcher Flowpath A Flowpath B • HYPULSE Capabilities: • NASA Facility at ATK GASL • Mach 5 to Mach 25 • Nozzle exit diam. Approx. 26” • Test time 10-15 ms. Pedestal Assembly 18

19. NCHCCP Program • NCHCCP Program conducted by UVa, ATK GASL, Stanford and NCSU • Funded by AFOSR, NASA M5 Facility Nozzle Test Article Flowpath A Flowpath B Removed for NCHCCP Program • Flowpath A Instrumentation: • 52 Pressure measurements • 21 Heat flux measurements • 5 original, 16 new • No Thermocouples Pedestal Assembly 19

20. HyPulse Engine Cowl/Sidewall • New engine cowl piece will be built • Sidewall windows and top wall optical & heat flux gauge inserts will be added • Top wall HFG and optical inserts are interchangeable. Radiation heater Supersonic Nozzle Sample Panel

21. HyPulse Engine Sidewall Windows • HyPulse engine window locations are consistent with those in UVa’s Dual Mode Engine

22. Fuel Plume Imaging (FPI) Setup • Mie Scattering of SiO2 particles • Produced in-situ from Silane combustion (SiH4 + Air) • Uniform distribution, combustion tracking, particle size less certain • Produced using dry seeder in fuel system • 1 μm diameter powder, mixing tracking, uniform distribution less certain • Reference AIAA -96-2222 for additional information Laser: Nd: YAG Laser; Wavelength: 532 nm Energy: 120 mJ per pulse per laser Repetition Rate: 15 x 2 Hz; Pulse width: 3-5 ns Camera: Asynchronous ~50 μsec shutter; 1300 x 1030 CCD

23. Test Setup and Optical Access at Mach 5 • Combustor schlieren is not available at Mach 5 • Combustor centerline FPI available

24. Test Setup and Optical Access at Mach 7 & 10 • Mach 7 & 10 nozzle is 26” longer • Both combustor schlieren and FPI are available at Mach 7 & 10

25. Mach 5 Flight

26. Mach 5 Flight Simulation • Hypulse M5 test conditions match the Mn, Ps & Ht at the cowl lip for flight at Mach 5.0, q1500 psf and 0 deg AoA

27. Mach 5 Test Conditions

28. Expected Nozzle Plenum and Exit Pressures Profiles for the Mach 5 Conditions • Steady state test duration up to 12 ms is available at Mach 5 • Nozzle core flow size is about 12 inches

29. Expected Engine Pressure Profile for the Mach 5 Conditions • 20% Silane-80% H2 fuel mixture will be used as the engine fuel to ensure auto-ignition • Combustor pressure: 10-20 psia for ER=0.30

30. Mach 7 Flight

31. Mach 7 Flight Simulation • Hypulse M7 test conditions match the Mn, Ps & Ht at the cowl lip for flight at Mach 7.0, q1000 psf and 0 deg AoA

32. Mach 7 Test Conditions

33. Expected Nozzle Plenum and Exit Pressures Profiles for the Mach 7 Conditions • Steady state test duration up to 8 ms for Mach 7 • Nozzle core flow size about 16 inches

34. Mach 10 Flight Simulation • Hypulse M10 test conditions match the Mn, Ps & Ht at the cowl lip for flight at Mach 10.0, q1000 psf and 4 deg AoA

35. Research ResultsDiagnostics

36. Stanford TDLAS Measurements 5 Beam Paths H2 Fuel Injector Ramp Optical Fibers Supersonic Air Exhaust L~1” • Non-intrusive measurement strategy for data to validate CFD models • Spatially and temporally-resolved measurements of T and H2O • Simultaneous measurements for 5 locations on 1” flow duct • Made possible through use of miniaturized optics • Sequential HyPulse runs for sensor data at different axial locations to match measurement locations with UVa’s direct connect tunnel

37. Research ResultsModeling

38. CFD Analysis – NCSU • NCSU team • Commenced late May, 2011 (Patrick Vogel hired ¼ time to perform this work) • Mesh generation using GridGen • Steady and possibly unsteady RANS simulations of reactive flow in HYPULSE inlet / combustor / nozzle • Kinetics of silane / hydrogen mixtures (Jachimowski and Mclain, NASA TP 2129, 1983) • 7 additional species (SiH2, SiH3, SiH4, SiH2O, HSiO, SiO, SiO2) • 23 additional reactions • Comparisons with TDLAS line-of-sight measurements, wall pressure, wall heat transfer   In Progress

39. Simulations of HYPULSE Experiments • Mesh generation (11.6 M cells, ½ plane symmetry) Combustor / nozzle Isolator Forebody / inlet Closeup of combustor Closeup of inlet

40. Simulations of HYPULSE Experiments • X-Y Centerplane mesh Combustor / nozzle Isolator Forebody / inlet Closeup of combustor mesh Closeup of inlet mesh

41. Collaboration

42. SDPTE (Hy-V) Test Program

43. SDPTE (Hy-V) Test Program Advanced Propulsion Test Technology (APTT)

44. Questions ?

45. Backup slides