The external-shock drag of supersonic inlets having subsonic entrance flow Page: 3 of 29
This report is part of the collection entitled: National Advisory Committee for Aeronautics Collection and was provided to Digital Library by the UNT Libraries Government Documents Department.
The following text was automatically extracted from the image on this page using optical character recognition software:
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
Here’s what’s next.
This report can be searched. Note: Results may vary based on the legibility of text within the document.
Tools / Downloads
Get a copy of this page or view the extracted text.
Citing and Sharing
Basic information for referencing this web page. We also provide extended guidance on usage rights, references, copying or embedding.
Reference the current page of this Report.
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 November 20, 2018), University of North Texas Libraries, Digital Library, digital.library.unt.edu; crediting UNT Libraries Government Documents Department.