SACCON UCAV FORCED OSCILLATION TESTS AT DNW-NWB AND NASA LANGLEY 14ft × 22ft TUNNEL

Abstract

The role of Computational Fluid Dynamics (CFD) methods in the design process of both air and sea vehicles continues to grow. However, the ability of CFD to accurately predict the static and dynamic stability characteristics of these vehicles has yet to be validated. An Applied Vehicle Technology Task Group (AVT-161) was established by the NATO Research and Technology Organization (RTO) to assess the state-of-the-art in CFD methods for the prediction of static and dynamic stability and control characteristics of military vehicles in the air and sea domains. Two highly swept wing configurations were selected for the air vehicle experimental and numerical investigations. The primary configuration was a generic UCAV geometry called SACCON – “Stability And Control CONfiguration”. The SACCON model mounted in the Low-Speed Wind Tunnel Braunschweig (DNW-NWB) is shown in Figure 3-1. The other focus air vehicle of AVT-161 was the X-31. This paper presents the results of a series of forced oscillation tests of the SACCON model conducted in both the DNW-NWB low-speed wind tunnel and the NASA Langley 14′ × 22′ Subsonic Tunnel. A complementary set of static data were also collected during these tests and reported in reference.