The performance of a rectangular ramjet inlet has been investigated experimentally. The main objective of the study has been to analyze the inlet flow before and during buzzing. Experiments have therefore been carried out with an inlet without and with boundary-layer bleed at an angle of attack of 0 deg and at Mach numbers ranging from 2.5 to 3.5 in the Trisonic Wind Tunnel Cologne. The inlet flow was analyzed with schlieren images and unsteady pressure recordings, where different pressure fluctuations are detected. The results show that the inlet flow is highly unsteady even at supercritical condition and that the subsequently added boundary-layer bleed permits better pressure recovery and a delay in inlet buzzing.
Pressure Fluctuations (Buzzing) and Inlet Performance of an Airbreathing Missile
Journal of Propulsion and Power ; 29 , 4 ; 839-848
01.07.2013
Aufsatz (Zeitschrift)
Elektronische Ressource
Englisch
Pressure Fluctuations (Buzzing) and Inlet Performance of an Airbreathing Missile
Online Contents | 2013
|Hypersonic Airbreathing Missile
NTRS | 1978
|Hypersonic Airbreathing Missile
NTIS | 1978
|