The experimental demonstration of a fluidic, multiaxis thrust vectoring (MATV) scheme is presented for a structurally fixed, afterburning nozzle referred to as the conformal fluidic nozzle (CFN). This concept for jet flow control features symmetric injection around the nozzle throat to provide throttling for jet area control, and asymmetric injection to subsonically skew the sonic plane for jet vectoring. The conceptual development of the CFN was presented in a companion paper (Miller et al. [1]). In that study, critical design variables were shown to be the flap length and expansion area ratio of the nozzle, and the location, angle, and distribution of injected flow. Measures of merit were vectoring capability, gross thrust coefficient, and discharge coefficient. A demonstration of MATV was conducted on a 20 percent scale CFN test article across a range of nozzle pressure ratios (NPR), injector flow rates, and flow distributions. Both yaw and pitch vector angles of greater than 8 deg were obtained at NPR of 5.5. Yaw vector angles greater than 10 deg were achieved at lower NPR. Values of thrust coefficient for the CFN generally exceeded published measurements of shock-based vectoring methods. In terms of vectoring effectiveness (ratio of vector angle to percent injected flow), fluidic throat skewing was found to be comparable to shock-based vectoring methods.

Issue Section:
Gas Turbines: Aircraft Engine
Keywords:
nozzles, aircraft, aerodynamics, flow control, fluidic devices
Topics:
Flow (Dynamics), Nozzles, Thrust, Yaw, Design
1.
Miller, D. N., Yagle, P. J., and Hamstra, J. W., 1999, “Fluidic Throat Skewing for Thrust Vectoring in Fixed Geometry Nozzles,” AIAA 99-0365.
2.
Miller, D. N., and Catt, J. A., 1995, “Conceptual Development of Fixed-Geometry Nozzles Using Fluidic Injection for Throat-Area Control,” AIAA 95-2603.
3.
Miller, D. N., Catt, J. A., and Walker, S. H., 1997, “Extending Flow Control of Fixed Nozzles Through Systematic Design: Introducing Assisted Reinjection,” ASME FEDSM97-3680.
4.
Gridley, M. C., and Walker, S. H., 1996, “Inlet and Nozzle Tech. for 21st Century Aircraft,” ASME 96-GT-244.
5.
Chiarelli, C., Johnsen, R. K., and Shieh, C. F., 1993, “Fluidic Scale Model Multi-Plane Thrust Vector Control Test Results,” AIAA 93-2433.
6.
Strykowski, P., and Krothapalli, A., 1994, “Thrust Vector Control of Rectangular Jets Using Counter Flow,” AFOSR Contractors Meeting Abstract.
7.
Gunter, F., and Fahrenholz, F., 1961, “Final Report on a Study of Rocket Thrust Control by Gas Injection,” MIT Naval Supersonic Lab, Technical Report 430.
8.
Walker, S., 1997, “Lessons Learned in the Development of a National Program,” AIAA 97-3348.
9.
Wing, D. J., 1994, “Static Investigation of Two Fluidic Thrust-Vectoring Concepts on a Two-Dimensional C-D Nozzle,” NASA TM 4574.
10.
Catt, J. A., Miller, D. N., and Giuliano, V. J., 1995, “A Static Investigation of Fixed-Geometry Nozzles Using Fluidic Injection for Throat-Area Control,” AIAA 95-2604.
11.
Yokota, J. W., et al., 1988, “A Diagonally Inverted LU Implicit Multigrid Scheme,” AIAA 88-3565-CP.
12.
Smith, B. R., 1990, “The k-kl Turbulence Model and Wall Layer Model for Compressible Flows,” AIAA 90-1483.
13.
Wing, D. J., Mills, C. T. L., and Mason, M. L., 1997, “Static Investigation of a Multiaxis Thrust-Vectoring Nozzle With Variable Internal Contouring Ability,” NASA TP 3628.
Copyright © 2001
 by ASME
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