Accession Number : ADA294884

Title :   Flight Test to Determine Feasibility of a Proposed Airborne Wake Vortex Detection Concept.

Descriptive Note : Technical memo. Jul 89-Feb 90,

Corporate Author : NATIONAL AERONAUTICS AND SPACE ADMINISTRATION HAMPTON VA LANGLEY RESEARCH CEN TER

Personal Author(s) : Branstetter, James R. ; Hastings, E. C., Jr. ; Patterson, James C., Jr

PDF Url : ADA294884

Report Date : APR 1991

Pagination or Media Count : 41

Abstract : An investigation was conducted jointly by the FAA and NASA to determine the radial extent of the circulatory flow field around the lift-induced vortex system of an aircraft in flight. This flow field, if found to be of sufficient strength and span to activate instrumentation onboard a following aircraft, may provide the basis for designing a feasible airborne wake detection and avoidance system. A small probe aircraft was flown behind a larger wake generator aircraft to measure the lateral separation distance at which the vortex could be detected using conventional instrumentation. This report discusses the results and mechanics of the flight test and proposes recommendations for future tests. (AN)

Descriptors :   *VORTICES, *FLOW FIELDS, *WAKE, AERIAL RECONNAISSANCE, FLIGHT TESTING, PROBES, COMPARISON, TURBULENCE, ANGLE OF ATTACK, FEASIBILITY STUDIES, INFLIGHT, DATA ACQUISITION, FLAPS(CONTROL SURFACES), SIDESLIP, RANGE(DISTANCE), ALTITUDE, FLOW SEPARATION, WING BODY CONFIGURATIONS, AERODYNAMIC LIFT, GYROSCOPES, AILERONS, AERIAL RUDDERS, WING TIPS, WAKE DETECTION.

Subject Categories : Aerodynamics
      Fluid Mechanics

Distribution Statement : APPROVED FOR PUBLIC RELEASE