Development and Use of a Dynamic-Testing Capability for the DSTO Water Tunnel
Abstract
This report gives details of the development and use of a water-tunnel dynamic-testing system, whereby models of aircraft are tested as they undergo a dynamic manoeuvre, with the roll, pitch and yaw angles changing in a specified way. Traditionally, most testing of aircraft in tunnels has been done with the aircraft stationary and set at a known orientation, but the acquired static data has limited applicability to manoeuvring aircraft. Dynamic data are needed to study unsteady aerodynamic effects associated with aircraft motion, to obtain data for use in flight-dynamic models of aircraft behaviour, and when validating CFD predictions of aircraft behaviour. Using the new testing system, flow-induced loads on an aircraft model can be measured and corresponding images of the flow over the aircraft can be captured for known instantaneous orientations of the aircraft, so that the loads can be correlated with the flow patterns. During a dynamic manoeuvre, including a coning manoeuvre, loads and images can also be acquired while simulating engine-intake flows. Loads were measured on a delta wing in the water tunnel when the wing was stationary and when it was in motion. The measured loads showed good agreement with wind- and water-tunnel data reported in the literature, showing that the new testing system gives credible results.
Document Details
- Document Type
- Technical Report
- Publication Date
- Mar 01, 2006
- Accession Number
- ADA458341
Entities
People
- Lincoln P. Erm
Organizations
- Defence Science and Technology Group