Free-flight transonic model investigation of jet effects on a fighter-type configuration employing a tail boom and three horizontal-tail positions Page: 3 of 157
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2 NACA RM L57J31
INTRODUCTION
Many research and operational fighter airplanes have a tail boom
extending above and back of a jet exit. Others with no boom have sta-
bilizing surfaces in a position to be affected by an exhausting jet.
Because of the insufficient free-flight information available on the jet-
interference effects on fighter-type configurations having a tail boom,
the National Advisory Committee for Aeronautics has initiated a series of
tests to obtain data on power effects and tail position effects on the
stability characteristics of a configuration with a tail boom of rectan-
gular cross section.
References 1 and 2 give some information on jet effects obtained
from free-flight model tests where these effects were incidental to the
tests. References 5 to 6 give results of investigations using free-
flight models that were primarily initiated to obtain information on jet
interference. The jet effects on the longitudinal stability and trim of
two of the models included in this paper were reported in reference 6.
Reference 7 presents wind-tunnel results of an investigation conducted
on a configuration with a tail boom extending back of and above an
exhausting jet. References 8 to 10 present the results of some inves-
tigations on jet effects on a surface located within the shock region
back of an exhausting jet as obtained in the preflight jet at the Langley
Pilotless Aircraft Research Station at Wallops Island, Va., the Langley
9-inch supersonic tunnel, and the Lewis 18- by 18-inch tunnel, respectively.
The primary concern of this paper is to present all the data that
are available on the longitudinal trim, normal force, drag, static and
dynamic stability for this series of models and to present the results
of a limited pressure survey on the boom and horizontal tails. The data
herein were obtained from four models whose only geometric difference
was the position and size of the horizontal tail.
The tests were conducted at the Langley Pilotless Aircraft Research
Station at Wallops Island, Va., by the rocket-boosted free-flight model
technique. A Mach number range of 1.1 to 1.4 and a Reynolds number range
of 9 X 106 to 15 x 106 were covered.
SYMBOLS
Positive displacements, forces, moments, and pressures are shown in
the body axes system (fig. 1) which is used throughout this paper.
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Jackson, Bruce G. Free-flight transonic model investigation of jet effects on a fighter-type configuration employing a tail boom and three horizontal-tail positions, report, February 20, 1958; (https://digital.library.unt.edu/ark:/67531/metadc64464/m1/3/: accessed April 24, 2024), University of North Texas Libraries, UNT Digital Library, https://digital.library.unt.edu; crediting UNT Libraries Government Documents Department.