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Hypersonics

Project Description & Objectives

  • Studying surface ablation of wakes behind bodies at hypersonic velocities

    • Convert GT High Pressure Shock Tube to a shock tunnel capable of replicating Mach 5-6 conditions​

    • Use thermographic phosphor coating on flight model surface to measure surface temperature

    • Measure chemiluminescent emissions from electronically excited NOx

  • Lead graduate student heading team for fabrication of test article and test stand

Accomplishments & Work Completed

  • Designed axi-symmetric 3D contour nozzle using Method of Characteristics 

    • Used finite differences method to develop 3 dimensional contoured nozzle expanding shock tube flow to Mach 5

  • Manufactured nozzle with high precision given length and size constraints

  • Stand assembly and nozzle test verification currently underway

    • High speed dynamic transducer rake built for flow speed verification in nozzle wake​

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