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.
Experimental Data from the Benchmark SuperCritical Wing Wind Tunnel Test on an Oscillating Turntable
2013
25 pages
Report
Keine Angabe
Englisch
Aerodynamics , Supercritical wings , Wind tunnel tests , Oscillations , Pitching moments , Flow distribution , Aeroelasticity , Airfoils , Trailing edges , Unsteady flow , Computational fluid dynamics , Transonic flow , Pressure distribution , Angle of attack , Testing time , Frequency domain analysis , Histograms
Experimental Data from the Benchmark Supercritical Wing Wind Tunnel Test on an Oscillating Turntable
British Library Conference Proceedings | 2013
|Transonic Wind Tunnel Test of Wing Oscillating in Pitch
AIAA | 2018
|Transonic Wind Tunnel Test of Wing Oscillating in Pitch (AIAA 2018-3004)
British Library Conference Proceedings | 2018
|