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Experimental and Analytical Methods for the Determination of Connected-Pipe Ramjet and Ducted Rocket Intenal Performance

Many NATO nations are now conducting research and de-
velopment of ramjets for supersonic, extended range mis-
siles and projectiles. In the context of this report the
ramjet is taken to be a generic class of propulsion devices
which comprise the liquid fuel ramjet, the solid fuel ramjet
and the ducted rocket (sometimes referred to as the ram—
rocket). Accurate data are needed for trade-off studies (es—
pecially in the medium—range area where solid propellant
motors can effectively compete) in which thrust-time char-
acteristics are input into mission analysis codes. It is also
necessary to standardize the techniques as much as possi-
ble so that performance data reported by one NATO na-
tion (or facility) can be effectively and fairly compared to
performance data reported by other organizations. Each
facility may employ different types of air heaters, chemical
equilibrium codes, instrumentation, calibration techniques
and testing methods. Identical motors tested in different
facilities can result in different reported thrust levels and
combustion efficiencies. These differences become even
more critical with the introduction of metallized fuels and
with increased flight Mach number.

In recognition of these needs, the AGARD Propulsion and
Energetics Panel established Working Group 22 to gen-
erate a working document which delineates the recom-
mended methods for the determination of connected-pipe
ramjet and ducted rocket performance. To accomplish this
goal the Working Group collected, reviewed and evaluated
the methods and techniques used in the NATO commu—
nity.

The scope of this document restricts itself to experi-
mental and analytical methods for the determination of
connected-pipe, subsonic combustion ramjet (with solid
and liquid fuels) and ducted rocket internal performance.