Wing-Body Combinations With Wings of Very Low Aspect Ratio at Supersonic Speeds Page: 4 of 63
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NACA RM A56Gi6
fn fineness ratio of body nose, _
I body length
1.e. leading edge
in body nose length (see fig. l(a))
free-stream Mach number
QW free-stream dynamic pressure
R Reynolds number based on body length
r local body radius
x,y,z Cartesian coordinates as shown in figure l(e)
3E controid of plan-form area measured from tip of body nose
Xp center of pressure measured from tip of body nose
O angle of attack measured between body axis and free-stream
direction (see fig. l(e))
ewing semiapex angle
cp angle of bank about x axis (see fig. 1(e))
APPARATUS AND TESTS
The experimental investigation was conducted in the Ames 1- by 3-foot
supersonic wind tunnels no. 1 and no. 2. Tunnel no. 1 is a closed-circuit,
continuous-operation type and is equipped with a flexible-plate nozzle that
provides a variation of Mach number from 1.4 to 4.0. The Reynolds number
is changed by varying the total pressure within the approximate limits of
1/5 of an atmosphere to 4 atmospheres. Tunnel no. 2 is a nonreturn,
intermittent-operation type and is also equipped with a flexible-plate
nozzle that provides a variation of Mach number from about 1.4 to 3.8.
Air for this tunnel is obtained from the Ames 12-foot wind tunnel at a
pressure of about 6 atmospheres and is expanded through the nozzle to the
atmosphere. Changes in Reynolds number are obtained by varying the total
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Jorgensen, Leland H. & Katzen, Elliott D. Wing-Body Combinations With Wings of Very Low Aspect Ratio at Supersonic Speeds, report, October 26, 1956; (https://digital.library.unt.edu/ark:/67531/metadc62824/m1/4/: accessed April 19, 2019), University of North Texas Libraries, Digital Library, https://digital.library.unt.edu; crediting UNT Libraries Government Documents Department.