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 National Center for Hypersonic Combined Cycle Propulsion Update Presentation on June 16 th, 2011 AFSOR-NASA Hypersonics Fundamental Research Review

2. National Center for Hypersonic Combined Cycle Propulsion 2 Outline Goals and Objectives Approach –Roadmap –Test Plan –Analysis Plan Schedule Research results –Experiments –Diagnostics –Modeling Collaboration Questions

3. National Center for Hypersonic Combined Cycle Propulsion 3 Goals and Objectives

4. National Center for Hypersonic Combined Cycle Propulsion 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 (H 2 O, O 2, CO 2 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. National Center for Hypersonic Combined Cycle Propulsion 5 Experimental Focus Areas FOCUS AREADUAL INLET RIGDUAL-MODE SCRAMJET (DMSJ) SCRAMJET Mach 3 - 4Mach 4 - 6Mach 5 - 10 NASA Glenn (conducted in collaboration with NASA) University of Virginia Supersonic Combustion Facility NASA HYPULSE at ATK GASL High-speed inlet Low-speed inlet IsolatorCombustor 1) Turbulence- chemistry interaction and the advancement of fuel-air mixing, flame holding and diagnostics ---CARS and Rayleigh PLIF TDLAS (Tomographic and LOS) PIV Schlieren High freq. press. TDLAS (LOS) High freq. press Heat flux Schlieren Fuel Plume Image 2) Benchmark data sets for RANS, hybrid LES/RANS, and LES models High freq. press. Low freq. press. Schlieren High freq. press. Low freq. press. Schlieren PIV Schlieren High freq. press. Low freq. press. CARS and Rayleigh PLIF TDLAS (Tomographic and LOS) PIV Schlieren High freq. press. Low freq. press. TDLAS (LOS) High freq. press Heat flux Schlieren Fuel Plume Image 3) Performance improvements and control of mode- transition High freq. press. Low freq. press. High freq. press. Low freq. press. High freq. press. Low freq. press. High freq. press. Low freq. press. -

6. National Center for Hypersonic Combined Cycle Propulsion 6 Approach

7. National Center for Hypersonic Combined Cycle Propulsion 7 Roadmap Hypervelocity Regime –Mach 5 - 10 200920102011201220132014 Experiments Modeling Diagnostics Design model Define diagnostics Build/install model Mach 5 testing Mach 7 testingMach 10 testing RANS RANS/LES-RANS Define diagnostics TDLAS/wall pressures and temperatures/flow visualization Dual Mode Exp.

8. National Center for Hypersonic Combined Cycle Propulsion 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 8

9. National Center for Hypersonic Combined Cycle Propulsion 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 9

10. National Center for Hypersonic Combined Cycle Propulsion 10 Schedule

11. National Center for Hypersonic Combined Cycle Propulsion 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

12. National Center for Hypersonic Combined Cycle Propulsion 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. National Center for Hypersonic Combined Cycle Propulsion 13 Research Results Experiments

14. National Center for Hypersonic Combined Cycle Propulsion 14 Hypulse Test Facility Hyper-X Scramjet Model Mach 7, 10, 15 NASA GTX Mach 7, 10 GASL 6.5” Dia. Mach 8 Gun-Launched Projectile 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

15. National Center for Hypersonic Combined Cycle Propulsion Leverage SDPTE (Hy-V) Program DMSJ flowpath geometries for a) original University of Virginia direct connect rig and b) Hypulse Flowpath A 15 53124

16. National Center for Hypersonic Combined Cycle Propulsion Leverage SDPTE (Hy-V) Program ATK Ground Tests - Medium & short duration - Clean & vitiated TBIV HYPULSE UVa Direct-connect tests - Long duration - Clean & vitiated Flight - Medium duration - Atmospheric air 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 16

17. National Center for Hypersonic Combined Cycle Propulsion 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 17

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

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

20. National Center for Hypersonic Combined Cycle Propulsion 20 HyPulse Engine Cowl/Sidewall Radia tion heate r Samp le Panel Super sonic Nozzl e 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.

21. National Center for Hypersonic Combined Cycle Propulsion HyPulse Engine Sidewall Windows HyPulse engine window locations are consistent with those in UVa’s Dual Mode Engine 21

22. National Center for Hypersonic Combined Cycle Propulsion Fuel Plume Imaging (FPI) Setup 22 Mie Scattering of SiO 2 particles Produced in-situ from Silane combustion (SiH 4 + 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. National Center for Hypersonic Combined Cycle Propulsion Test Setup and Optical Access at Mach 5 Combustor schlieren is not available at Mach 5 Combustor centerline FPI available 23

24. National Center for Hypersonic Combined Cycle Propulsion 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 24

25. National Center for Hypersonic Combined Cycle Propulsion Mach 5 Flight 25

26. National Center for Hypersonic Combined Cycle Propulsion Mach 5 Flight Simulation 26 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. National Center for Hypersonic Combined Cycle Propulsion Mach 5 Test Conditions 27

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

29. National Center for Hypersonic Combined Cycle Propulsion Expected Engine Pressure Profile for the Mach 5 Conditions 29 20% Silane-80% H 2 fuel mixture will be used as the engine fuel to ensure auto- ignition Combustor pressure: 10-20 psia for ER=0.30

30. National Center for Hypersonic Combined Cycle Propulsion Mach 7 Flight 30

31. National Center for Hypersonic Combined Cycle Propulsion Mach 7 Flight Simulation 31 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. National Center for Hypersonic Combined Cycle Propulsion Mach 7 Test Conditions 32

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

34. National Center for Hypersonic Combined Cycle Propulsion Mach 10 Flight Simulation 34 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. National Center for Hypersonic Combined Cycle Propulsion 35 Research Results Diagnostics

36. National Center for Hypersonic Combined Cycle Propulsion 36 Stanford TDLAS Measurements Non-intrusive measurement strategy for data to validate CFD models Spatially and temporally-resolved measurements of T and H 2 O –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 Supersonic Air Exhaust Optical Fibers 5 Beam Paths H 2 Fuel Injector Ramp L~1”

37. National Center for Hypersonic Combined Cycle Propulsion 37 Research Results Modeling

38. National Center for Hypersonic Combined Cycle Propulsion 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 (SiH 2, SiH 3, SiH 4, SiH 2 O, HSiO, SiO, SiO 2 ) 23 additional reactions –Comparisons with TDLAS line-of-sight measurements, wall pressure, wall heat transfer In Progress

39. National Center for Hypersonic Combined Cycle Propulsion 39 Simulations of HYPULSE Experiments Mesh generation (11.6 M cells, ½ plane symmetry) Forebody / inlet Isolator Combustor / nozzle Closeup of inlet Closeup of combustor

40. National Center for Hypersonic Combined Cycle Propulsion 40 Simulations of HYPULSE Experiments X-Y Centerplane mesh Forebody / inlet Isolator Combustor / nozzle Closeup of inlet mesh Closeup of combustor mesh

41. National Center for Hypersonic Combined Cycle Propulsion 41 Collaboration

42. National Center for Hypersonic Combined Cycle Propulsion 42 SDPTE (Hy-V) Test Program

43. National Center for Hypersonic Combined Cycle Propulsion 43 SDPTE (Hy-V) Test Program Advanced Propulsion Test Technology (APTT)

44. National Center for Hypersonic Combined Cycle Propulsion 44 Questions ?

45. National Center for Hypersonic Combined Cycle Propulsion 45 Backup slides