The External-Shock Drag of Supersonic Inlets Having Subsonic Entrance Flow Page: 3 of 29
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NACA RM L5OG1ha
The system, however, cannot be directly applied to the determination of
the external-shock drag of inlets operating with subsonic entrance flow
In reference h, a method has been presented which can be used for
determining the external-shock drag of supersonic inlets having either
supersonic or subsonic entrance flow and/or perforations. The only
experimental information needed is a shadow or schlieren photograph of
the shock configuration of the inlet and the free-stream Mach number.
This method has been applied in the present paper for the determination
of the external-shock drag of an inlet having low external compression
and different relative mass flows and of an inlet having high external
compression at a free-stream Mach number of 2.70.
An approximate method for determining the external-shock drag of
bodies having attached or detached frontal shock waves, which was sug-
gested by Dr. A. Ferri of the Langley Aeronautical Laboratory, has also
been applied for the determination of the external-shock drag of the
inlets investigated. The results obtained by this approximate method
have been compared with the results obtained by the more accurate method
given in reference 4.
q dynamic pressure
cp specific heat at constant pressure
y ratio of specific heats
--- relative mass flow, ratio of mass of air that entered the
ML inlet divided by the air which would enter an area equal
to the cowling-entrance area in the free stream
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Nucci, Louis M. The External-Shock Drag of Supersonic Inlets Having Subsonic Entrance Flow, report, December 20, 1950; (digital.library.unt.edu/ark:/67531/metadc64669/m1/3/: accessed January 17, 2019), University of North Texas Libraries, Digital Library, digital.library.unt.edu; crediting UNT Libraries Government Documents Department.