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Experimental investigation of a 0.15 scale model of a conformal variable-ramp inlet for the F-16 airplaneA 0.15 scale model of a proposed conformal variable-ramp inlet for the Multirole Fighter was tested from Mach 0.8 to 2.2 at a wide range of angles of attack and sideslip. Inlet ramp angle was varied to optimize ramp angle as a function of engine airflow, Mach number, angle of attack, and angle of sideslip. Several inlet configuration options were investigated to study their effects on inlet operation and to establish the final flight configuration. These variations were cowl sidewall cutback, cowl lip bluntness, boundary layer bleed, and first-ramp leading edge shape. Diagnostic and engine face instrumentation were used to evaluate inlet operation at various inlet stations and at the inlet/engine interface. Pressure recovery and stability of the inlet were satisfactory for the proposed application. On the basis of an engine stability audit of the worst-case instantaneous distortion patterns, no inlet/engine compatibility problems are expected for normal operations.
Document ID
19800015771
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Hawkins, J. E. (General Dynamics/Fort Worth TX, United States)
Date Acquired
September 4, 2013
Publication Date
March 1, 1980
Subject Category
Aerodynamics
Report/Patent Number
NASA-CR-159640
ERR-FW-2014
Accession Number
80N24263
Funding Number(s)
PROJECT: RTOP 505-32-12
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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