Project 059(A) Jet Noise Modeling to Support Low Noise Supersonic Aircraft Technology Development

Details

• Alternative Title:
  Jet Noise Modeling to Support Low Noise Supersonic Aircraft Technology Development
• Creators:
  Mavris, Dimitri N. ; Tai, Jimmy C. ; Kenny, James D. ; Ahuja, Jai ; Chartier, Noah ; Tai, Andrew
• Corporate Creators:
  Georgia Institute of Technology. School of Aerospace Engineering
• Corporate Contributors:
  United States. Department of Transportation. Federal Aviation Administration. Center of Excellence for Alternative Jet Fuels and Environment
• Subject/TRT Terms:
  Aircraft Noise Jet Engines Noise Control Supersonic Aircraft Technological Innovations
• Resource Type:
  Tech Report
• Geographical Coverage:
  United States
• Corporate Publisher:
  United States. Department of Transportation. Federal Aviation Administration. Center of Excellence for Alternative Jet Fuels and Environment
• Abstract:
  This project sought to understand the degree to which a 2D supersonic inlet with variable geometry could mitigate thrust losses associated with the addition of jet noise reduction technologies, without overcoming the noise benefits from those technologies, during landing and takeoff (LTO) conditions. The work developed a supersonic inlet modeling capability to predict inlet impacts to performance and aerodynamics and then utilized a supersonic transport aircraft with mixed flow turbofan engine models using a multidisciplinary analysis code for supersonic aircraft, which couples the NPSS engine modeling code with several NASA codes for mission analysis (FLOPS), compressor map generation (CMPGEN), and noise prediction (ANOPP). The study modeled the fixed aircraft and engine with an added nozzle-based noise reduction technology in the form of chevrons, and fixed supersonic inlet model, and then performed follow on studies to understand how varying the inlet geometry with a variable geometry cowl lip and/or blow-in doors could improve mass flowrate availability at LTO conditions and it’s effects on a selection of chevrons attached to the engine CD plug nozzle. Results showed that these inlet design features can mitigate thrust losses for LTO, while maintaining sufficient thrust to complete the mission. However, selection of inlet feature for mass flowrate increase and effects at different observed directivity angles vary.
• Format:
  PDF
• Funding:
  13-C-AJFE-GIT–063
• Collection(s):
  Federal Aviation Administration
• Main Document Checksum:
  urn:sha-512:3baea458ee520d1e9ae8e3b79b819cda86107d2b4223018eb824fd7acaba093628bbc51b867555744ff7f24e320aba3a0d59413c21ced03686205821aa3428af
• Download URL:
  https://rosap.ntl.bts.gov/view/dot/89826/dot_89826_DS1.pdf
• File Type:
  [PDF - 2.11 MB ]