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FOR 1066: Simulation of Wing and Nacelle Stall

Logo des Forschungsprojektes FOR 1066

Spokesman: Prof. Dr. –Ing. Rolf Radespiel

For detailed information you are welcome to visit the FOR 1066 website.

Mission of the FOR 1066

The FOR 1066 is a group of scientist funded by the German Research Foundation (DFG), which conducted its research activities between 2008 and 2015. Its objectives have been technical challenges concerning the development and flight test of commercial aircraft and aircraft engines. With regard to this, the FOR 1066 covers different research areas as for example flight performance, functional costs and environmental impact including its various consequences. Moreover, flight safety in civil aviation represents an important element of the group’s research activities. For safe transportation of goods as well as of people as a basic principle is to be guaranteed. Thus it is of great importance to accurately investigate the performance of commercial aircraft at flight boundaries in order to eventually augment these boundaries while at the same time maintaining flight safety.

But what is the reason for those flight boundaries in first place? The main reason is the stall of aerofoils and elevator units during slow flight. In order to compute the maximum lift of aerofoils and tail unit as well as the dynamic performance during slow flight, valid mathematic models and efficient numeric algorithms for flow simulation are required. Therefore the main aim of the group is to solve flight physical problems by the application of a well-founded scientific simulation methodology which in the end is to be validated by results of new experiments. Research papers of five DFG projects from the time between 2006 and 2008 which have been funded as PAK 136 by the DFG, serve as the theoretical basis for the group’s research approaches.

Research Programs A and B

The FOR 1066 consists of two partial projects (A and B), which deal with various sub-projects.

Sub-project A

Brief Description of Activities: The focus of attention of sub-project A is on the generation of a well-founded computing method for numeric prediction of the occurrence and extension of massive flow separation predominantly at aerofoils. Moreover the project concentrates on the method’s application for the examination of atmospheric disturbances in incoming air flow (especially while approaching for landing). Moreover an object of investigation is the interaction of aerofoils with turbulent atmospheric air flows. With regard to this, simulation of surround-flow of aerofoils in realistic metrological circumstances plays a central role. Ultimately the research goal is to generate a well-founded experimental database which is able to represent the dynamics of flow separation at a two element profile during transient disturbances concerning the incoming air flow. Thus, the project aims at generically presenting conditions during dynamic stall of high-lift profiles of commercial aircraft.

A1: Simulation methodology for stall during disturbed incoming air flow with DES

A2: Numerical simulation regarding the interaction of the atmosphere with surround-flow of aerofoils

A3: Experimental investigation of stall behavior of a two element profile with disturbances of incoming air flow

Sub-project B

Brief Description of Activities: The aim of the sub-project is the implementation of a high-precision and efficient simulation technology for interlinked computing of surround air flow of an aircraft as well as of inside air flow of engines. Hereby the junction of the respectively optimized processes TAU and TRACE, plays a major role. Another concern is to answer the question if and by what means a physically well-founded computing method for the transient separation at engine inlets in interaction with first compression levels can be demonstrated. This question shall be settled with the help of advancements in optical metrology for spatially resolved measurements of both pressure and speed. Finally, the generation and validation of numeric computing methods for disturbed incoming air flow and its interaction with the fan stage is another important research field of the project. In collaboration with the UniBW (Bundeswehr University Munich) the computation of the interaction with the fan stage shall be validated. Furthermore, the characteristic curves of the compressor stages shall be measured.

B2/B3: Numerical simulation of flow inside an engine fan during inhomogeneous flow situations

B4: Investigation of vortex-dynamics during stall of engine nacelles using time-resolving measurement methods

B5: Model tests for experimental examination of disturbed jet engine inflow and its interaction with an engine fan


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