Accession Number:

AD0891439

Title:

Supersonic Inlet Investigation. Volume 2. Air Induction System Dynamic Simulation Model

Descriptive Note:

Final rept. 1 May 1969-1 May 1971

Corporate Author:

NORTHROP CORP HAWTHORNE CA AIRCRAFT DIV

Personal Author(s):

Report Date:

1971-09-01

Pagination or Media Count:

185.0

Abstract:

A one-dimensional mathematical dynamic simulation model for predicting the transient behavior of air induction systems for advanced tactical aircraft operating in the supersonic portion of the flight spectrum is discussed. As a part of the simulation model, control system logic is included to provide control system design criteria necessary to maintain air induction system response to selected input disturbances within prescribed limits. The model is applicable to both external and mixed compression inlets operating at supersonic conditions. The lumped parameter concept is used in simulating the dynamic response of the subsonic duct downstream of the terminal shock, with the duct divided into three lumps.

Subject Categories:

  • Jet and Gas Turbine Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE