Mach 4 testing of scramjet inlet models

Tekashi Kanda, Tomoyuki Komuro, Goro Masuya, Kenji Kudo, Atsuo Murakami, Kouichiro Tani, Yoshio Wakamatsu, Nobuo Chinzei

Research output: Contribution to journalArticlepeer-review

15 Citations (Scopus)


Six scramjet inlet models were tested in a Mach 4 wind tunnel. Wall and pitot pressure were measured and schlieren photographs were taken. Parameters of these models are side-plate sweep angle, contraction ratio, and cowl geometry. The shock pattern inside one of the models, as shown by schlieren photographs, coincides with the calculations. Both mass-capture ratio and total pressure recovery are 50-70%. There seems to be a better sweep angle and a better cowl length for maximum total pressure recovery.

Original languageEnglish
Pages (from-to)275-280
Number of pages6
JournalJournal of Propulsion and Power
Issue number2
Publication statusPublished - 1991 Jan 1

ASJC Scopus subject areas

  • Aerospace Engineering
  • Fuel Technology
  • Mechanical Engineering
  • Space and Planetary Science


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