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Capt Barry Croker Executive Officer to the AFRL Vice Commander Air Force Research Laboratory

ON THE DESIGN OF HYPERSONIC INLETS 3rd Symposium on Integrating CFD & Experiments in Aerodynamics USAFA, CO 20-21 June, 2007. Capt Barry Croker Executive Officer to the AFRL Vice Commander Air Force Research Laboratory. Acknowledgements.

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Capt Barry Croker Executive Officer to the AFRL Vice Commander Air Force Research Laboratory

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  1. ON THE DESIGN OF HYPERSONIC INLETS3rd Symposium on Integrating CFD & Experiments in AerodynamicsUSAFA, CO20-21 June, 2007 Capt Barry Croker Executive Officer to the AFRL Vice CommanderAir Force Research Laboratory

  2. Acknowledgements • Dr. Datta GaitondeMs. Heidi MeicenheimerMr. Pete KutschenreuterAir Vehicles Directorate, AFRL • Dr. John SchmisseurAFOSR • DoD HPCMO, ASC MSRC

  3. Overview • USAF High Speed Vision • Hypersonic Design Process • JAWS Inlet Program • Design Methodology • CFD Verification & Validation • Experimental Test Program • Conclusions

  4. USAF High Speed Mission Future Capabilities: • Prompt Global Strike • Long Range Strike • Operationally Responsive Access to Space Hypersonic flight will enable unparalleled global reach and power

  5. Challenges of High Speed Flight Balance engine/airframe over entire speed regime Boundary layer transition on external surfaces and inlet Shock/boundary layer interactions Mass capture, contraction limits in inlet Nozzle over-expansion at transonic speeds External burning ignition and flame-holding Isolator performance and operability Cowl lip drag and heat transfer Nozzle recombination losses Fuel injection drag, mixing and heat transfer Key enabling technologies need to be developed to make sustained hypersonic flight feasible!

  6. AFRL Design Core Competency “…to establish a core-competency in hypersonic vehicle inlet design…” EngineeringDesign Tools Experimental Ground Testing High-Fidelity CFD

  7. Engineering Design SHOCK BOX Invisicid Streamtracing

  8. Computational Verification AVUSDesign Space Exploration2nd Order Unstructured RANS + SA or BL FDL3DIHigh-Fidelity Analysis3rd Order Structured RANS + k- • EulerStream Trace VerificationShock Location • TurbulentViscous CorrectionsNonlinear Effects

  9. Centerline X-Y Plane

  10. 2D Centerline X-Y Plane

  11. 2D Centerline X-Y Plane

  12. JAWS Inward-Turning, Circular Cross Section M = 5 - 10Q  = 1000-1500 psf

  13. Planar Shock Topology Y X Z Quarter-Section Rectangular Analogy Secondary Reflection Secondary Shock Primary Reflection Primary Shock Full Topology

  14. Inviscid Results Mach Number along X-Z Centerline Plane

  15. Inviscid Results Mach Number along X-Y Centerline Plane

  16. Viscous Correction Boundary layer momentum thickness accounted for through each shock

  17. Turbulent Results Mach Number along X-Y Centerline Plane

  18. Turbulent Results Mach Number along X-Z Centerline Plane

  19. Comparison of Results Mach Number along X-Y Centerline Plane Invisicid Viscous

  20. Comparison of Results Mach Number at Exit Plane Invisicid Viscous

  21. Swept-Shock Boundary Layer Interaction Isosurface of TKE in Boundary Layer

  22. Swept-Shock Boundary Layer Interaction • Separated Boundary Layer • Centerline Vortex • Interaction Flows

  23. Conclusions of CFD • Overall shock structure well aligned with prediction • Viscous correction adequate for shock location • Influence of Swept-Shock Boundary Layer Interaction could have implications on performance

  24. Experimental Test Program • NASA Langley Aerothermodynamics Branch 20” Mach 6 Tunnel • Originally Planned for May, Slipped to August • Test Goals: • Establish inlet starting parameters • Back-pressure study • Evaluate on and off design performance • Angle of Attack/Yaw • Re & Minf

  25. Model Fabrication • Instrumentation location based on CFD predictions • Diagnostics include: • Pressure • Temperature • Surface Oil Flow Visualization

  26. Conclusions & Future Work EngineeringDesign Tools Experimental Ground Testing High-Fidelity CFD • Functional Analytical Design • CFD to check & improve method • EFD to verify computations & improve method • CFD on off-design cases • Comparison of CFD & EFD data

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