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: 2 of 83
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NASA Technical LibraI
NACA RM L7KO 3 1176 01437 2610
NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS
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
By Douglas R. Lord
An investigation has been made at Mach numbers of 1.61 and 2.01
and a Reynolds number of 2.5 x 106, based on the wing chord, of a semi-
span model of a possible vertical-take-off-and-landing jet bomber con-
figuration. The purpose of the investigation was to determine the
effects of jet interference, horizontal-tail location, and canard con-
trols on the longitudinal stability characteristics of the model. Tests
were made for an angle-of-attack range from 00 to 120 and for a range of
ratios of jet total pressure to stream static pressure from the jet-off
condition to a maximum of 21.2.
In general, the jet-interference effects on longitudinal stability
were of small magnitude except for a decrease in stability as the jet
was first turned on for the high-tail configurations at a Mach number
of 2.01. The horizontal tail located at the midpoint of the vertical,
tail caused severe pitch-up characteristics whereas the low horizontal-
tail configuration exhibited generally favorable stability characteristics.
A coordinated program of research is under way at the Langley
Laboratory on a possible vertical-take-off-and-landing jet bomber con-
figuration which employs the tilt-wing concept for achieving its vertical-
flight capabilities. The proposed aircraft would be capable of cruising
at supersonic Mach numbers and therefore the side-by-side positioning of
the six jet engines gives a plan-form area large enough that the required
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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/m1/2/: accessed November 18, 2018), University of North Texas Libraries, Digital Library, digital.library.unt.edu; crediting UNT Libraries Government Documents Department.