Flight Investigation of the Supersonic Area Rule for a Straight Wing-Body Configuration at Mach Numbers Between 0.8 and 1.5 Page: 3 of 37
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2 NACA RM L55C09
for several wing-body configurations have shown that a substantial
reduction in the drag rise near Mach number 1.0 may be obtained by
modifying or designing an airplane to have a cross-sectional area dis-
tribution that is conducive to low drag. A convenient type of m6difi-
cation is a fuselage indentation for Mach number 1.0, which effectively
cancels the exposed wing cross-sectional areas normal to the axis of
symmetry. However, recent investigations (refs. 2 and 11, for example)
have shown that the beneficial effects obtained from such indentations
decrease with increasing Mach number and eventually produce an unfavor-
able effect on the drag. This effect is particularly acute on straight
wing-body combinations where the indentations result in considerable
necking down of the fuselage causing high body slopes at the wing-body
The concept of the transonic area rule has been extended to super-
sonic speeds (refs. 12 to 15) in an attempt to provide area distribu-
tions for low wave drag at supersonic speeds as well as transonic speeds.
This paper presents an investigation of the supersonic area rule for a
straight wing-body configuration which was optimized with symmetrical
body indentations (according to ref. 15) for design Mach numbers of 1.10
and 1.41. The wing had an aspect ratio of 3.04, taper ratio of 0.5394,
00 of sweep along the 75-percent chord line, and an NACA 65A004.5 airfoil
section in the free-stream direction. The unmodified fuselage was para-
bolic having a frontal area equal to 0.0606 that of the total wing plan-
The models were flight tested at the Langley Pilotless Aircraft
Research Station at Wallops Island, Va. The tests of the indented con.
figurations covered a continuous range of Mach number from 0.8 to 1.5
with corresponding Reynolds number from 5 X 106 to 12 x 106, based on
wing mean aerodynamic chord. The experimental results are compared with
the theoretical wave drags of the configurations tested through most of
the Mach number range.
A cross-sectional area
a tangential acceleration
CD total drag coefficient, based on Sw
5 mean aerodynamic chord of wing
g acceleration due to gravity
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Hoffman, Sherwood; Wolff, Austin L. & Faget, Maxime A. Flight Investigation of the Supersonic Area Rule for a Straight Wing-Body Configuration at Mach Numbers Between 0.8 and 1.5, report, April 29, 1955; (digital.library.unt.edu/ark:/67531/metadc61224/m1/3/: accessed February 18, 2019), University of North Texas Libraries, Digital Library, digital.library.unt.edu; crediting UNT Libraries Government Documents Department.