03.4 - Applied Aerodynamics
WIND TUNNEL EXPERIMENTS WITH LOCAL ACTIVE FLOW CONTROL FOR AIRCRAFT TOWARDS FUTURE FLIGHT TESTING
V. Ciobaca¹, B. Stefes², A. de Bruin³, M. Bauer, NAVASTO GmbH, Germany; P. Schlösser, Airbus Defence and Space GmbH, Germany; A. de Blécourt³, N. Bier¹, J. Zhai, DNW-KKK, Germany; M. Meyer², J. Wild¹; ¹Deutsches Zentrum für Luft und Raumfahrt, DLR, Germany ;²Airbus Operations GmbH, Germany ;³NLR-Netherlands Aerospace Center, Netherlands
A high Reynolds number wind tunnel test with a single aisle transport aircraft model at low speed cryogenic conditions is addressing the challenges to apply local active flow control technologies to delay the wing stall at high-lift conditions and enables the close-coupling of UHBR engines. The study considers flow control technologies to be matured towards a future flight test.