Comparison of the minimum drag of two versions of a modified delta-wing fighter as obtained from flight tests of rocket-boosted models and equivalent bodies between Mach numbers of 0.80 and 1.64 Page: 3 of 26
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2 NACA RM L56EOi
revolution which were designed according to the transonic-area-rule con-
cept and provided a simple and inexpensive means of estimating the zero-
lift pressure drag and drag rise of thin, low-aspect-ratio wing-body
combinations. The revised design was then tested by use of large-scale
This paper presents the results from tests of the equivalent bodies
of revolution and the minimum drag data obtained from the flight results
of rocket-boosted models. Comparisons are made between the original and
revised configurations. All tests were conducted at the Langley Pilotless
Aircraft Research Station at Wallops Island, Va.
A cross-sectional area, sq ft
aZ/g longitudinal-accelerometer reading
an/g normal-accelerometer reading
5 mean aerodynamic chord, ft
Cc chord-force coefficient, positive in rearward
direction, g q
CDtot total drag coefficient, Cc cos a + CN sin a
CN normal-force coefficient, positive toward top of model, An W
g acceleration due to gravity, 32.2 ft/sec2
H total pressure, lb/sq ft
2 length, ft
M Mach number
m/mo ratio of total mass flow through ducts to mass flow at free-
stream conditions passing through an area equal to total
inlet capture area*
static pressure, lb/sq ft
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Hasting, Earl C , Jr & Mitcham, Grady L. Comparison of the minimum drag of two versions of a modified delta-wing fighter as obtained from flight tests of rocket-boosted models and equivalent bodies between Mach numbers of 0.80 and 1.64, report, September 24, 1956; (digital.library.unt.edu/ark:/67531/metadc62790/m1/3/: accessed March 24, 2018), University of North Texas Libraries, Digital Library, digital.library.unt.edu; crediting UNT Libraries Government Documents Department.