Please use this identifier to cite or link to this item: https://hdl.handle.net/10356/146359
Title: Improving inlet performance of turbo-ramjet engine by using surface correction
Authors: Nandhini Raju
Keywords: Engineering::Aeronautical engineering::Aerodynamics
Issue Date: 2016
Publisher: Nanyang Technological University
Abstract: In this study axisymmetric supersonic intake model was tested at Mach number of 4. The intake geometry of SR-71 supersonic aircraft was used here for testing a scale model. Static and total pressure measurements in the duct were used to observe shock effect on internal flow. To improve pressure recovery of intake, surface correction of cone was attempted. By using taper plug different blockage area of exit were obtained to locate normal shock in throat for minimum loss of pressure. Redesign of model, pressure instrumentation, principle of intake operation and data analysis are covered in detail in the thesis. Results of pressure values showed good agreement with simple 1 - D compressible flow calculations.
URI: https://hdl.handle.net/10356/146359
Fulltext Permission: restricted
Fulltext Availability: With Fulltext
Appears in Collections:MAE Theses

Files in This Item:
File Description SizeFormat 
NandhiniRaju's Master thesis2016.pdf
  Restricted Access
2.08 MBAdobe PDFView/Open

Page view(s)

58
Updated on Apr 23, 2021

Google ScholarTM

Check

Items in DR-NTU are protected by copyright, with all rights reserved, unless otherwise indicated.