Unsteady Wing-Pylon-Nacelle Interference in Transonic Flow Export

@inproceedings{DietzUnsteady, abstract = {The interference effects between an unswept supercritical airfoil model and an annular wing representing an engine nacelle were investigated. The investigation aims to better understand and predict the impact of the interference effects on the aeroelastic stability of large, modern transport aircraft at transonic speeds. The main objective was to identify potential aerodynamic instabilities in the interference region due to unsteady shock-wave/boundary-layer interactions. The applied model allows to roll and yaw the nacelle relative to the model wing, and to pitch the entire model. The aerodynamic response to these movements affects the aeroelastic stability of an aircraft and was also investigated here. The overlap between the wing and the nacelle, and the height of the pylon were designed by numerical simulations such that locally supersonic velocities and flow separation in the interference region might occur. Two linear hydraulic jacks inside the model were used to perform prescribed yaw and roll movements of the nacelle including the pylon. The experiments were conducted up to Mach numbers of 0.84 in an adaptive solid-wall wind tunnel using a hydraulic driven pitch-oscillation setup. Boundary-layer transition was tripped on the wing as well as on the nacelle. The unsteady tests reveal a strong dependency of the aerodynamic response to the structural movement on the topology of the time-averaged flow field. During the static tests, an aerodynamic instability was detected for certain Mach-number/model-incidence combinations. In addition to the initial objectives, a simple countermeasure was applied in the interference region and its effectiveness was demonstrated.}, address = {Department Structural Dynamics and Coupled Systems}, author = {Dietz, G. and Mai, H. and Schr\"{o}der, A. and Klein, C. and Moreaux, N. and Leconte, R.}, citeulike-article-id = {1739802}, citeulike-linkout-0 = {http://www.scopus.com/record/display.url?view=extended&origin=resultslist&eid=2-s2.0-34547532136}, citeulike-linkout-1 = {http://www.scopus.com/scopus/record/display.url?view=extended&origin=resultslist&eid=2-s2.0-34547532136}, journal = {Collect Tech Pap AIAA ASME ASCE AHS Struct Struct Dyn Mater}, keywords = {aeroelasticity, buffet, dlr, nacelle, pylon, transonic, wing, wiona}, pages = {3923--3937}, posted-at = {2007-10-08 08:12:08}, priority = {0}, series = {48th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference}, title = {Unsteady Wing-Pylon-Nacelle Interference in Transonic Flow}, url = {http://www.scopus.com/scopus/record/display.url?view=extended&origin=resultslist&eid=2-s2.0-34547532136}, volume = {4} }

TY - CONF ID - DietzUnsteady L3 - citeulike-article-id:1739802 N2 - The interference effects between an unswept supercritical airfoil model and an annular wing representing an engine nacelle were investigated. The investigation aims to better understand and predict the impact of the interference effects on the aeroelastic stability of large, modern transport aircraft at transonic speeds. The main objective was to identify potential aerodynamic instabilities in the interference region due to unsteady shock-wave/boundary-layer interactions. The applied model allows to roll and yaw the nacelle relative to the model wing, and to pitch the entire model. The aerodynamic response to these movements affects the aeroelastic stability of an aircraft and was also investigated here. The overlap between the wing and the nacelle, and the height of the pylon were designed by numerical simulations such that locally supersonic velocities and flow separation in the interference region might occur. Two linear hydraulic jacks inside the model were used to perform prescribed yaw and roll movements of the nacelle including the pylon. The experiments were conducted up to Mach numbers of 0.84 in an adaptive solid-wall wind tunnel using a hydraulic driven pitch-oscillation setup. Boundary-layer transition was tripped on the wing as well as on the nacelle. The unsteady tests reveal a strong dependency of the aerodynamic response to the structural movement on the topology of the time-averaged flow field. During the static tests, an aerodynamic instability was detected for certain Mach-number/model-incidence combinations. In addition to the initial objectives, a simple countermeasure was applied in the interference region and its effectiveness was demonstrated. JF - Collect Tech Pap AIAA ASME ASCE AHS Struct Struct Dyn Mater SE - 48th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference AD - Department Structural Dynamics and Coupled Systems EP - 3937 TI - Unsteady Wing-Pylon-Nacelle Interference in Transonic Flow VL - 4 SP - 3923 KW - aeroelasticity KW - buffet KW - dlr KW - nacelle KW - pylon KW - transonic KW - wing KW - wiona AU - Dietz, G AU - Mai, H AU - Schröder, A AU - Klein, C AU - Moreaux, N AU - Leconte, R UR - http://www.scopus.com/record/display.url?view=extended&origin=resultslist&eid=2-s2.0-34547532136 ER -