1,474 research outputs found
Flight Measurements with the Douglas D-558-II (buaero No. 37974) Research Airplane : Static Lateral and Directional Stability Characteristics as Measured in Sideslips at Mach Numbers up to 0.87
A flight investigation of the handling characteristics of a fighter airplane controlled through automatic-pilot control systems
Flight Measurements of the Longitudinal Stability, Stalling, and Lift Characteristics of an Airplane Having a 35 Degrees Sweptback Wing Without Slots and with 40-percent-span Slots and a Comparison with Wind-tunnel Data
Flight Measurements of the Stability, Control, and Stalling Characteristics of an Airplane Having a 35 Degree Sweptback Wing Without Slots and with 80-percent-span Slots and a Comparison with Wind-tunnel Data
Preliminary flight measurements of the static longitudinal stability and stalling characteristics of the Douglas D-558-II research airplane (BuAero No. 37974)
Flight Measurements of the Lateral and Directional Stability and Control Characteristics of an Airplane Having a 35 Degree Sweptback Wing 40-percent-span Slots and a Comparison with Wind-tunnel Data
Empirical Studies of Evolving Systems
This paper describes the results of the working group investigating the issues of empirical studies for
evolving systems. The groups found that there were many issues that were central to successful evolution and this
concluded that this is a very important area within software engineering. Finally nine main areas were selected for consideration. For each of these areas the central issues were identified as well as success factors. In some cases success stories were also described and the critical factors accounting for the success analysed. In some cases it was later found that a number of areas were so tightly coupled that it was important to discuss them together
Flight Investigation of a Normal-Acceleration Automatic Longitudinal Control System in a Fighter Airplane
A flight investigation was made to obtain experimental information on the handling qualities of a normal-acceleration type of automatic longitudinal control system. The control system was installed in a subsonic fighter-type airplane. In hands-off (stick-free) flight the normal-acceleration control system attempted to regulate the normal acceleration to a constant value which is dependent on the automatic-control-system trim setting. In maneuvering flight a given pilot's stick deflection produced a proportional change in normal acceleration, the change in acceleration being independent of flight condition. A small side-located controller stick was used by the pilot to introduce signals into the automatic control system. In the flight program emphasis was placed on the acceleration-limiting capabilities of the control system. The handling qualities were investigated in maneuvers such as slow and rapid pull-ups and turns and also in flight operations such as cruising, stalls, landings, aerobatics, and air-to-air tracking. Good acceleration limiting was obtained with the normal-acceleration control system by limiting the magnitude of the input signal that the pilot could introduce into the control system. The same values of control-system gain settings could be used from an acceleration-limiting stand-point at both 10,000 and 30,000 feet for the complete speed range of the airplane. The response characteristics of the airplane-control system combination were also satisfactory at both high and low altitude with these same values of control-system gain setting. In the pilot's opinion, the normal-acceleration control system provided good stability and control characteristics in flight operations such as cruising, stalls, landings, aerobatics, and air-to-air tracking
Flight Measurements with the Douglas D-558-II (buaero No. 37974) Research Airplane : Static Longitudinal Stability and Control Characteristics at Mach Numbers up to 0.87
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