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A flight study of longitudinal-control-system dynamic characteristics by the use of a variable-control-system airplane
Report presenting flight tests with an airplane equipped to vary the longitudinal-control-system dynamic characteristics over a wide range. Control is obtained through a stabilizer force-command position-feedback longitudinal-control system. Results at a Mach number of 0.80 at 35,000 feet altitude, Mach number of 0.35 at 5,000 feet altitude, and normal-acceleration response are provided.
Date:
March 3, 1958
Creator:
McFadden, Norman M.; Pauli, Frank A. & Heinle, Donovan R.
System:
The UNT Digital Library
Static Longitudinal and Lateral Stability and Control Characteristics of a Model of a Swept-Wing Fighter-Bomber-Type Airplane With a Top Inlet at Mach Numbers From 1.6 to 2.35
"Static longitudinal and lateral stability characteristics of a swept-wing fighter-bomber airplane model with a top inlet have been determined experimentally. In addition, vertical-tail effectiveness, spoiler effectiveness, effects of several store configurations, and effects of mass flow were investigated. Tests were made at Mach numbers of 1.6, 1.8, 2.0, 2.2, and 2.35 and Reynolds numbers, based upon mean aerodynamic chord, of between 2.0x10(exp 6) and 2.5x10(exp 6)" (p. 1).
Date:
March 3, 1958
Creator:
Gnos, A. Vernon & Kurkowski, Richard L.
System:
The UNT Digital Library
Summary of locations, extents, and intensities of turbulent areas encountered during flight investigations of the jet stream from January 7, 1957 to April 28, 1957
"A summary of the locations, extents, and intensities of turbulent areas encountered during a flight investigation of the jet stream is presented. The data were obtained from NACA VGH time-history records" (p. 1).
Date:
March 3, 1958
Creator:
Copp, Martin R.
System:
The UNT Digital Library