Tests of Aerodynamically Heated Multiweb Wing Structures in a Free Jet at Mach Number 2: Two Aluminum-Alloy Models of 20-Inch Chord With 0.064- and 0.081-Inch-Thick Skin Page: 3 of 40
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NACA RM L55F13
The second model MW-2, of 20-inch chord and span, was essentially a
half-scale version of model MW-1 and was tested to compare its behavior
with that of its prototype and to obtain additional information through
increased instrumentation. This model also experienced a dynamic fail-
ure near the end of its test. The third model MW-3 was similar in size
to model MW-2 but was provided with a thicker skin in order to withstand
greater stresses, due to both loading and heating; this model failed
statically at an angle of attack of 50 after surviving four tests at
smaller angles of attack. The present paper discusses in detail the test
results of models MW-2 and MW-3.
c specific heat, Btu/(lb)(F)
h heat-transfer coefficient, Btu/(sq ft) (sec) (F)
H stagnation pressure, lb/sq in. abs
t time from start of air flow, sec
tO time of initial conditions in temperature calculations, sec
T model temperature, OF
TAW adiabatic wall temperature, OF
TO initial model temperature, OF
TS stagnation temperature, OF
w specific weight, lb/cu ft
a angle of attack, deg
7 skin thickness, ft
The models designated MW-2 and MW-3 were identical in construction
except for skin thickness; they comprised somewhat idealized semispan
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Griffith, George E.; Miltonberger, Georgene H. & Rosecrans, Richard. Tests of Aerodynamically Heated Multiweb Wing Structures in a Free Jet at Mach Number 2: Two Aluminum-Alloy Models of 20-Inch Chord With 0.064- and 0.081-Inch-Thick Skin, report, August 9, 1955; (https://digital.library.unt.edu/ark:/67531/metadc61471/m1/3/: accessed April 25, 2019), University of North Texas Libraries, Digital Library, https://digital.library.unt.edu; crediting UNT Libraries Government Documents Department.