An attempt is made for fluidic control of the vortical flow and its related vortex breakdown phenomenon over a delta wing with a particular geometry. The model has a sweep angle of Lambda = 60 deg and a rounded leading edge. The control system is based on four rectangular slots along the portside leading edge, and it provides continuous or pulsed jets normal to the leading-edge surface and parallel to the leeward side plane. The mass flow rate and the frequency of injection can be varied independently. The results are compared to a reference case defined by a microflap fixed along the leading edge and set perpendicular to it. Qualitative measurements are obtained with surface flow visualizations and boundary-layer transition detections with acenaphten. Quantitative data consist in mean and instantaneous surface pressure distributions measurements under the primary vortex axis and in mean three-dimensional velocity held measurements. The control effect is analyzed by means or laser sheet visualizations to detect the vortex breakdown position and by normal force and rolling moment measurements with a five-component balance.
Control of vortical flow over a rounded leading-edge delta wing
Beeinflussung der Wirbelströmung über einem Deltaflügel mit abgerundeter Vorderkante
AIAA Journal ; 43 , 7 ; 1409-1418
2005
10 Seiten, 22 Bilder, 34 Quellen
Article (Journal)
English
Abrundung (Fase) , Drehmoment , Druckmessung , Druckverteilung , Fächerstrahl , Geschwindigkeitsverteilung , Grenzschichtablösung , Grenzschichtströmung , Klappe , Laser-Doppler-Anemometrie , Naphthen , Ölfilm , Pfeilflügel , pulsierende Strömung , Schlitz , Strahlausfluss , Sublimation , Tragflügelumströmung , Turbulenz , Visualisierung , Windkanalprüfung , Wirbel (Strömung) , Wirbelströmung , Zusammenbruch , stetige Strömung , Strömungsregelung
Vortical flow prediction of a diamond wing with rounded leading edges
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