Optical Measurements of Rocket Nozzle Thrust and Noise

The high-temperature, high-speed exhaust from the propulsion systems of commercial systems, such as the SpaceX Falcon vehicles, impinges on the launch pad surface (see Space X, Merlin Engine in figure). This results in very high unsteady pressure loads and extremely high fluctuating thermal loads in the vicinity of the impingement region which leads to structural vibrations that can compromise efficiency and operational safety. The aeroacoustic loads due to rocket plume impingement and vehicle leading edge and boat-tail interactions will be experimentally examined in the research team's jet, rocket and aerodynamic facilities. The team will develop, test and refine promising Active, Passive and Hybrid flow control methods. Based on the results the team will identify the most promising method(s) in light of: flow unsteadiness reduction efficacy and full-scale implementation practicality.

Language

  • English

Project

Subject/Index Terms

Filing Info

  • Accession Number: 01678246
  • Record Type: Research project
  • Source Agency: Federal Aviation Administration Center of Excellence for Commercial Space Transportation
  • Files: RiP, USDOT
  • Created Date: Aug 22 2018 1:03PM