Accession Number : ADA256311


Title :   Flowfield Study of a Close-Coupled Canard Configuration


Descriptive Note : Master's thesis


Corporate Author : NAVAL POSTGRADUATE SCHOOL MONTEREY CA


Personal Author(s) : O'Leary, John F


Full Text : https://apps.dtic.mil/dtic/tr/fulltext/u2/a256311.pdf


Report Date : Jun 1992


Pagination or Media Count : 96


Abstract : A nulling five-hole pressure probe was used to complete a flowfield survey behind a close-coupled canard and wing model set at 22 degrees angle of attack. The canard and wing were both low-aspect-ratio, highly-swept, delta planforms with rounded leading edges. The model was set at the condition of maximum lift enhancement of the canard/wing configuration over a corresponding wing-alone configuration, based on previous force measurements. For comparison, the pressure measurements were made with the canard on and with the canard off. From the pressure measurements, flowfield velocity-vector, velocity-streamline and total-pressure-coefficient contours were plotted. These plots showed the dramatic effect of the canard vortex on the wing flowfield. The location and interaction of the canard and wing leading-edge vortices were analyzed. Large- scale reattachment of previously reversed flow over the wing was noted, as well as the re-establishment and strengthening of the wing leading-edge vortex. Close-coupled canard, Vortex interaction, Post-stall, High angle of attack, Agility.


Descriptors :   *FIGHTER AIRCRAFT , *FLOW FIELDS , *DELTA WINGS , *CANARD CONFIGURATIONS , VELOCITY , PROBES , MANEUVERABILITY , MODELS , INTERACTIONS , CONFIGURATIONS , LEADING EDGES , PLANFORM , CONTOURS , HIGH ANGLES , ASPECT RATIO , LIFT , WINGS , FLOW , PRESSURE , SURVEYS , COMPARISON , AUGMENTATION , THESES , VORTICES , ANGLE OF ATTACK


Subject Categories : Attack and Fighter Aircraft
      Fluid Mechanics


Distribution Statement : APPROVED FOR PUBLIC RELEASE