Experimental data from the Benchmark SuperCritical Wing wind tunnel test on an oscillating turntable

TLDR

The BSCW was selected as a test case because of its geometric simplicity and the complex flow physics it exhibits, including an unsteady strong shock, shock‑induced separation, and trailing‑edge separation. This paper quantifies those aerodynamic characteristics at the AePW test condition and at a proposed benchmarking test condition. The study uses the BSCW wind‑tunnel model as a semi‑blind test case for the 2012 AIAA Aeroelastic Prediction Workshop, examining unforced system data and forced pitching oscillations across the entire available data set.

Abstract

The Benchmark SuperCritical Wing (BSCW) wind tunnel model served as a semi-blind testcase for the 2012 AIAA Aeroelastic Prediction Workshop (AePW). The BSCW was chosen as a testcase due to its geometric simplicity and flow physics complexity. The data sets examined include unforced system information and forced pitching oscillations. The aerodynamic challenges presented by this AePW testcase include a strong shock that was observed to be unsteady for even the unforced system cases, shock-induced separation and trailing edge separation. The current paper quantifies these characteristics at the AePW test condition and at a suggested benchmarking test condition. General characteristics of the model's behavior are examined for the entire available data set.