An experimental investigation has been conducted at the NASA Langley 16-Foot Transonic Tunnel Static Test Facility to determine the concept feasibility of using Fluidics to achieve multi-plane thrust vector control in a two-dimensional convergent-divergent (2D-CD) fixed aperture nozzle. Pitch thrust vector control is achieved by injection of flow through a slot in the divergent flap into the primary nozzle flow stream. Yaw vector control results fiom secondary air delivered ++' t angent i al l y to vertical Coanda flaps. These flaps are offset laterally and aligned parallel to the primary nczzle side walls. AU tests were conducted at static (no external flow) conditions. Flow visualization was conducted using a paint flow technique and Focus Schlieren. Significant levels of pitch deflection angles (19O) were achieved at low pressure ratios and practical levels (14O) resulted at typical intermediate power settings. The ability of the Coanda surface blowing concept to produce yaw deflection was limited to NF' R < 4. Svmbolg Primary nozzle exit area$ Primary nozzle throat area, in2 Primary nozzle exit plane base area, in Aspect ratio, widthheight at nozzle throat Primary nozzle discharge coefficient, wp/wp, Total gross thrust coefficient, 2 Axial gross thrust coefficient, = FgX,/(Fq + Finj, + Fp, ) Lateral thrust coefficient, = Fgy/(Fs, + Finj, + Fp,) Vertical thrust coefficient, = Fgz/( Fq + Finj, + Fp, ) 1 Downloaded by MONASH UNIVERSITY on October 11, 2015 | http://arc.aiaa.org |

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