Aerodynamic Performance and Static Stability and Control of Flat-Top Hypersonic Gliders at Mach Numbers From 0.6 to 18 Page: 2 of 57
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NACA RM A58G17
NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS C
AERODYNAMIC PERFORMANCE AND STATIC STABILITY AND CONTRbL
OF FLAT-TOP HYPERSONIC GLIDERS AT MACH NUMBERS
FROM 0.6 TO 18
By Clarence A. Syvertson, Hermilo R. Gloria,
and Michael F. Sarabia
A study is made of aerodynamic performance an static stability
control at hypersonic speeds. In a first part of the study, the effect
of interference lift is investigated by tests of asymmetric models hav-
ing conical fuselages and arrow plan-form wings. The fuselage of the
asymmetric model is located entirely beneath the wing and has a semi-
circular cross section. The fuselage of the symmetric model was cen-
trally located and has a circular cross section. Results are obtained
for Mach numbers from 3 to 12 in part by application of the hypersonic
similarity rule. These results show a maximum effect of interference
on lift-drag ratio occurring at a Mach number of 5, the Mach number at
which the asymmetric model was designed to exploit favorable lift inter-
ference. At this Mach number, the asymmetric model is indicated to have
a lift-drag ratio 11 percent higher than the symmetric model and 15 per-
cent higher than the asymmetric model when inverted. These differences
decrease to a few percent at a Mach number of 12. In the course of this
part of the study, the accuracy of the hypersonic similarity rule applied
to wing-body combinations is demonstrated with experimental results.
These results indicate that the rule may prove useful for determining
the aerodynamic characteristics of slender configurations at Mach num-
bers higher than those for which test equipment is readily available.
In a second part of the study, the aerodynamic performance and
static stability and control characteristics of a hypersonic glider are
investigated in somewhat greater detail. Results for Mach numbers from 3
to 18 for performance and O.6 to 12 for stability and control are obtained
by standard test techniques, by application of the hypersonic similarity
rule, and/or by use of helium as a test medium. Lift-drag ratios of
about 5 for Mach numbers up to 18 are shown to be obtainable. The glider
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Syvertson, Clarence A.; Gloria, Hermilo R. & Sarabia, Michael F. Aerodynamic Performance and Static Stability and Control of Flat-Top Hypersonic Gliders at Mach Numbers From 0.6 to 18, report, September 17, 1958; (digital.library.unt.edu/ark:/67531/metadc64409/m1/2/: accessed January 24, 2019), University of North Texas Libraries, Digital Library, digital.library.unt.edu; crediting UNT Libraries Government Documents Department.