Aerodynamic Characteristics at Supersonic Speeds of a Series of Wing-Body Combinations Having Cambered Wings With an Aspect Ratio of 3.5 and a Taper Ratio of 0.2: Effect at M = 2.01 of Nacelle Shape and Position on the Aerodynamic Characteristics in Pitch of Two Wing-Body Combinations with 47 Degree Sweptback Wings Page: 3 of 29

                                
NACA RM LS2F03

INTRODUCTION
A research program has been in progress at the Langley Aeronautical
Laboratory to determine at subsonic, transonic, and supersonic speeds
the effects of thickness ratio and sweep on the aerodynamic characteris-
tics of a series of wing-body combinations. The cambered wings have an
aspect ratio of 3.5 and a taper ratio of 0.2. The effects of sweep at
subsonic and transonic speeds are presented in references 1 and 2. The
effects of sweep, thickness ratio, and nacelle position on the longi-
tudinal and lateral stability characteristics at a Mach number of 1.60
are presented in references 3, 4, and 5. The effects of both sweep and
thickness ratio on the longitudinal and lateral stability characteristics
at a Mach number of 2.01 are presented in references 6 and 7.
This paper presents the results of tests at M = 2.01    of a majority
of the nacelle configurations previously tested at M = 1.60    (ref. 5).
The nacelle shape and location were varied on a 6-percent-thick wing
having the quarter-chord line swept back 47o. Simulated submerged
nacelles were also tested on this configuration and on a simular configu-
ration with a wing having a thickened root section. The root-section
thickness ratio varied linearly from 12 percent at the body center line
to 6 percent at the 40-percent-semispan station. Lift, drag, and
pitching-moment results are presented for a Mach number of 2.01 and a
Reynolds number of 2.2 x 106 based on the wing mean aerodynamic chord.
The data of this paper are presented with a minimum of analysis to
expedite publication.
SYMBOLS
mean aerodynamic chord of wing, 0.646 ft
CD        drag coefficient, D/qS
ACD      nacelle drag increment, drag-coefficient rise due to
addition of nacelles to basic wing configuration
CL        lift coefficient, L/qS
Cm        pitching-moment coefficient about the quarter chord of
the mean aerodynamic chord, m/qSE
D         drag
L         lift

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