The Comparative Analysis of Two Typical Fluidic Thrust Vectoring Exhaust Nozzles on Aerodynamic Characteristics

Authors: Xin H. Zou, Qiang Wang

Abstract:

The comparisons of two typical fluidic thrust vectoring exhaust nozzles including two-dimensional(2-D) nozzle and axisymmetric nozzle on aerodynamic characteristics was presented by numerical simulation. The results show: the thrust vector angles increased with the increasing secondary flow but decreased with the nozzle pressure ratio (NPR) increasing. With the same secondary flow and NPR, the thrust vector angles of 2-D nozzle were higher than the axisymmetric nozzle-s. So with the lower NPR and more secondary weight flow, the much higher thrust vector angle was caused by 2-D fluidic nozzle. And with the higher NPR and less secondary weight flow, there was not much difference in angular dimension between two nozzles.

Keywords: Aerodynamic characteristics, fluidic nozzle, vector angle, thrust coefficient comparison.

Digital Object Identifier (DOI): doi.org/10.5281/zenodo.1078052

References:

[1] Wing D J. Static investigation of two fluidic. Thrust-vectoring concepts on a 2DCD nozzle
[R]. N A S A-TM-4574, December, 1994
[2] Wing David J, Giuliano V J. Fluidic Thrust Vectoring of an Axisymmetric Exhaust Nozzle at Static Conditions. ASMEFEDSM97-3228, 1997.
[3] Jeffrey D. Flamm. Experimental Study of a Nozzle Using Fluidic Counterflow for Thrust Vectoring. AIAA98-3255, 1998
[4] Deere K A. Summary of Fluidic Thrust Vectoring Research Conducted at NASA Langley Research Center. AIAA2003´╝ì3800´╝î2003
[5] Deere K A. Computational Investigation of the Aerodynamic Effects on Fluidic Thrust Vectoring. AIAA2000-3598´╝î2000.
[6] Deere K A, Waithe Kenrick A. Experimental and Computational Investigation of Multiple Injection Ports in a Convergent-Divergent Nozzle for Fluidic Thrust Vectoring. AIAA 2003-3802, 2003.