Accession Number : ADA259044


Title :   An Experimental Investigation of a Finite Circulation Control Wing


Descriptive Note : Master's thesis


Corporate Author : AIR FORCE INST OF TECH WRIGHT-PATTERSONAFB OH SCHOOL OF ENGINEERING


Personal Author(s) : Tallarovic, John M


Full Text : https://apps.dtic.mil/dtic/tr/fulltext/u2/a259044.pdf


Report Date : Dec 1992


Pagination or Media Count : 76


Abstract : This wind tunnel investigation examined the lift, drag, and pitching moment of a 20% thick, 8.5% camber, partial elliptical cross-section, single blowing slot, rectangular, circulation control wing. The aspect ratios tested were 3.71 and 3.99. Variables included three differently shaped trailing edge Coanda surfaces and steady blowing and pulsed blowing. The test Reynolds number, based on the chord was 500,000. The-angle of attack was varied from minus 6 degrees to the inception of stall. The maximum lift coefficient measured was 3. 17 with an equivalent drag coefficient of 1.85. Results also show a limit to increasing lift by increasing the blowing. Additionally, a 90 degree Coanda surface had equal lift performance and better drag performance than a 180 degree Coanda surface.... Circulation control, V/STOL Aircraft wind tunnel testing, Wing, Pulsed blowing.


Descriptors :   *FLIGHT CONTROL SYSTEMS , *WINGS , TEST AND EVALUATION , CONTROL , RATIOS , AIRCRAFT , EDGES , MOMENTS , ANGLE OF ATTACK , VARIABLES , SURFACES , COEFFICIENTS , CROSS SECTIONS , SLOTS , NUMBERS , DRAG , LIFT , CIRCULATION , WIND TUNNELS , REYNOLDS NUMBER , ASPECT RATIO , TRAILING EDGES , SHORT TAKEOFF AIRCRAFT , CAMBER


Subject Categories : Flight Control and Instrumentation


Distribution Statement : APPROVED FOR PUBLIC RELEASE