FOR 1066:  Stall Simulation of Wings and Engine Nacelles

• Subject Area: Thermal Engineering/Process Engineering
• Term: from 2008 to 2015
• Project identifier: Deutsche Forschungsgemeinschaft (DFG) - Project number 62584147

Transport aircrafts are generally designed for a specific range of flight conditions where flight safety is required. Flight performance, operational cost and environmental compatibilities are considered secondary values as compared to flight safety, but they depend significantly on the flight boundaries of the aircraft. Therefore, it is of great importance, to know the behaviour of transport aircraft at their flight boundaries and to extend these boundaries while still ensuring flight safety. While experimental flight testing is very expensive and often risky, advances in the numerical simulation capabilities offer new perspectives for aircraft design and flight testing.
One of the physical mechanisms that limit the flight range of transport aircrafts is wing and the empennage stall at low speeds. Here one needs validated, mathematical models and efficient numerical algorithms for flow simulation that can be used to compute maximum lift of wings and empennages and their dynamic behaviour during stall. The effect of meteorological distortions will be considered in our simulations for the first time. Flow states with flow separation in the engine inlet are important as well, as the resulting inhomogeneous inlet flow can lead to large loads on the fan stage and the first compressor stages.
The Research Unit strives for a scientifically founded simulation methodology that can address flight boundaries. While numerical simulation methods are now well developed for applications close to the aircraft design point and widely used in industrial design, the Research Unit will use interdisciplinary, high fidelity simulations to address complex interactions of different effects at stalling conditions. This great challenge can only met using close cooperation by which scientific knowledge and methods needed for highly accurate simulations of external flow fields and powered engine nacelles at the flight boundaries are obtained. Rolls-Royce Germany and Airbus Germany participate within the Research Unit in specific transfer projects by supplying model hardware, testing time in facilities and resources for numerical simulations used for model validation.

• DFG Programme: Research Units

Projects

• Experimentelle und numerische Untersuchung von gestörter Triebwerks-Einlaufströmung und deren Interaktion mit einem Triebwerks-Fan (Applicant Schiffer, Heinz-Peter )
• Experimentelle Untersuchung des Überziehverhaltens eines 2-Element-Profils mit 2D- und 3D-Störungen der Zuströmung (Applicant Radespiel, Rolf )
• Koordination der Forschungsgruppe 1066 (Applicant Radespiel, Rolf )
• Numerische Modellierung der Strömung in einem Triebwerks-Fan bei inhomogenen Zuströmbedingungen (Applicant Niehuis, Reinhard )
• Numerische Simulation des Überziehens von Triebwerkseinläufen im Niedergeschwindigkeitsbereich mit Reynolds-Spannungsmodellen der Turbulenz (Applicant Radespiel, Rolf )
• Numerische Simulation zur Wechselwirkung der Atmosphäre mit der Tragflügelumströmung (Applicants Bange, Jens ;  Raasch, Siegfried )
• Numerische Studien zum Einfluss turbulenter Zuströmung auf die instationäre Aerodynamik von Tragflügeln und die Entwicklung des Nachlaufs (Applicant Lutz, Thorsten )
• Simulationsmethodik für den überzogenen Flugzustand bei gestörter Zuströmung mit DES (Applicant Knopp, Tobias )
• Simulationsmethodik zur Berechnung von Böenlasten an Flugzeugen (Applicant Heinrich, Ralf )
• Untersuchung der Wirbeldynamik beim Überziehen von Triebwerksgondeln mit zeitauflösenden Messverfahren (Applicant Kähler, Christian Joachim )

• Spokesperson: Professor Dr.-Ing. Rolf Radespiel