Accession Number : AD0283754

Title :   FLEXIBLE WING MANNED TEST VEHICLE

Corporate Author : RYAN AERONAUTICAL CO SAN DIEGO CA

PDF Url : AD0283754

Report Date : Aug 1962

Pagination or Media Count : 166

Abstract : Studies were conducted to provide information on the aerodynamic characteristics, handling qualities, and stability and control of the flexible wing concept. Standard stability and control flight tests were conducted, where applicable, on a full sized manned Flexible Wing test vehicle incorporating the principle of center of gravity (cg) movement for longitudinal and lateral control. Control forces and vehicle response to control input were investigated. As anticipated, high longitudinal and lateral control forces were encountered. Longitudinal control forces of approximately 100 lb were considered acceptable to the pilot. Lateral control forces of approximately 70 lb were considered undesirable. Longitudinal response to control input was satisfactory and positive in sense, i.e. a forward shift in cg resulted in a nose down movement of the vehicle. Lateral response was masked by the high lateral forces, but was also positive in sense. Tests indicated the need for a rudder to facilitate cross-wind operations of a manned vehicle, and to augment the lateral control system for roll control. Static longitudinal and lateral/directional stability tests were conducted throughout the greater portion of the speed range. A deterioration of longitudinal stability and a right wing down roll tendency at speeds above 40 kt were noted. (Author)

Descriptors :   *AERODYNAMIC CHARACTERISTICS, *FLIGHT TESTING, AIRFRAMES, CONTROL, DELTA WINGS, MATHEMATICAL ANALYSIS, ROLL, STABILITY, STRESSES

Subject Categories : Military Aircraft Operations

Distribution Statement : APPROVED FOR PUBLIC RELEASE