Longitudinal Stability Investigation of a Vertical-Take-Off-and-Landing Airplane Configuration With Simulated Jet Intake and Exhaust at Mach Numbers of 1.61 and 2.01 Page: 4 of 83
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NACA RM L57KD 05V rLI L 3
c wing chord, 8.18 in.
Pt, jet total pressure
tjp ratio of jet total pressure to stream static pressure
M stream Mach number
p stream static pressure
PB base static pressure
q stream dynamic pressure
S semispan wing area, 36.0 sq in.
SH semispan horizontal-tail area
a model angle of attack
8c canard incidence
A prefix indicating increment in coefficient (horizontal tail
on minus horizontal tail off or vertical tail on minus
vertical tail off)
it horizontal-tail incidence
This investigation was conducted in the Langley 4- by 4-foot super-
sonic pressure tunnel, which is a rectangular, closed-throat, single-
return type of wind tunnel with provisions for the control of the
pressure, temperature, and humidity of the enclosed air. Flexible nozzle
walls were adjusted to give the desired test section Mach numbers of 1.61
and 2.01. During the tests, the dewpoint was kept below -200 F at atmos-
pheric pressure so that the effects of water condensation in the super-
sonic nozzle were negligible.
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Lord, Douglas R. Longitudinal Stability Investigation of a Vertical-Take-Off-and-Landing Airplane Configuration With Simulated Jet Intake and Exhaust at Mach Numbers of 1.61 and 2.01, report, January 30, 1958; (digital.library.unt.edu/ark:/67531/metadc64021/m1/4/: accessed February 18, 2019), University of North Texas Libraries, Digital Library, digital.library.unt.edu; crediting UNT Libraries Government Documents Department.