Variable nozzles for aerodynamic testing of scramjet engines

Eijiro Kitamura, Tohru Mitani, Noboru Sakuranaka, Syuichi Watanabe, Goro Masuya

Research output: Chapter in Book/Report/Conference proceedingConference contribution

4 Citations (Scopus)

Abstract

A variable Mach number nozzle for aerodynamic engine tests was designed and calibrated. In this nozzle, only one hydraulic actuator made freestream Mach number change between 2 and 4 during a run of the wind tunnel. The optimization of the nozzle contours was conducted by the 2-D computational simulation. The CFD results predicted that the deviation of Mach number from the averaged value was less than 1% and flow angle was less than 1 degree in the test region. The results of the calibration tests of the nozzle showed that the deviations of Mach number distributions in the test core (60 mm×60 mm) of the exit cross section (100 mm×100 mm) were less than 1.5 % from Mach 2 to 3.5 and 3.5 % at Mach 4. The aerodynamic tests of scramjet engine models with sidewall compression type inlets were carried out with this nozzle. Air capture ratio and internal drag were measured. When the freestream Mach number decreased, the soft unstart in the inlet was observed around Mach 3. It resulted in increase of the internal drags.

Original languageEnglish
Title of host publicationICIASF'05 Record - 21st International Congress on Instrumentation in Aerospace Simulation Facilities, 2005
Pages348-354
Number of pages7
Volume2005
Publication statusPublished - 2005 Dec 1
Event21st International Congress on Instrumentation in Aerospace Simulation Facilities, 2005, ICIASF'05 - Sendai
Duration: 2005 Aug 292005 Sep 1

Other

Other21st International Congress on Instrumentation in Aerospace Simulation Facilities, 2005, ICIASF'05
CitySendai
Period05/8/2905/9/1

ASJC Scopus subject areas

  • Instrumentation
  • Aerospace Engineering
  • Condensed Matter Physics

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