Flow Visualization Study Of A Vortex Wing Interaction
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A Water Tunnel Flow Visualization Study of the Vortex Flow Structures on the F/a-18 Aircraft
| Author | : National Aeronautics and Space Administration (NASA) |
| Publisher | : Createspace Independent Publishing Platform |
| Total Pages | : 124 |
| Release | : 2018-07-17 |
| Genre | : |
| ISBN | : 9781722915285 |
The vortex flow structures occurring on the F/A-18 aircraft at high angles of attack were studied. A water tunnel was used to gather flow visualization data on the forebody vortex and the wing leading edge extension vortex. The longitudinal location of breakdown of the leading edge vortex was found to be consistently dependent on the angle of attack. Other parameters such as Reynolds number, model scale, and model fidelity had little influence on the overall behavior of the flow structures studied. The lateral location of the forebody vortex system was greatly influenced by changes in the angle of sideslip. Strong interactions can occur between the leading edge extension vortex and the forebody vortex. Close attention was paid to vortex induced flows on various airframe components of the F/A-18. Reynolds number and angle of attack greatly affected the swirling intensity, and therefore the strength of the studied vortices. Water tunnel results on the F/A-18 correlated well with those obtained in similar studies at both full and sub scale levels. The water tunnel can provide, under certain conditions, good simulations of realistic flows in full scale configurations. Sandlin, Doral R. and Ramirez, Edgar J. Unspecified Center FLOW DISTRIBUTION; FLOW VISUALIZATION; HYDRAULIC TEST TUNNELS; LEADING EDGES; VORTICES; WING PROFILES; AIRFRAMES; ANGLE OF ATTACK; FOREBODIES; REYNOLDS NUMBER; SCALE MODELS; SIDESLIP; SWIRLING...
A Visualisation Study of the Vortex Flow Around Double-delta Wings
| Author | : D. H. Thompson |
| Publisher | : |
| Total Pages | : 46 |
| Release | : 1985 |
| Genre | : Airplanes |
| ISBN | : 9780642112620 |
A family of double-delta wings with leading-edge sweep combinations of 80/80,80/7080/6080/50 and 80/40 deg. was tested in a small towing tank. The hydrogen bubble technique was used to visualize the vortex patterns above the wings over a range of Reynolds numbers (based on centerline chord) from 7000 to 100,000. The effects of variations in incidence and leading-edge kink angle were examined. Reynolds number and leading-edge cross-section shape were found to have significant effects on the vortex structure. Attempts to visualize details of the upper surface secondary vortex flows met with only partial success. Keywords Flow visualization, Vortices, Delta wings, Angle of incidence. (Australia).
Flow Visualization Study of Vortex Manipulation on Fighter Configurations at High Angles of Attack
| Author | : Gerald N. Malcolm |
| Publisher | : |
| Total Pages | : 19 |
| Release | : 1987 |
| Genre | : |
| ISBN | : |
Experiments were performed in a flow visualization water tunnel on a generic fighter model to explore vortex manipulation as an effective means of aircraft control by altering the natural state of the forebody and LEX vortices in the medium-to-high-angle of attack range with either small surface modifiers or blowing jets. Specifically, the forebody vortex system was examined with the clean forebody, with forebody strakes, and with forebody surface blowing. LEX vortices were examined with a clean LEX, with small geometric modifications near the apex, and with surface blowing, both in upstream and downstream directions at various locations on the LEX surface. The interactive effects of forebody and LEX/wing vortices and their response to the various methods of control were also examined. Generally, it was concluded that the forebody vortices can be effectively controlled by either blowing or using strakes, but the effectiveness is very dependent on proper radial placement of the blowing port or strake. Geometric modifications and blowing at the LEX apex were not particularly effective in altering the trajectory of the LEX vortices or the burst points. Blowing aft of the mid-chord of the LEX was much more effective and could force the burst points to move forward significantly. Interactions between the forebody and LEX vortex systems were pronounced.
Interaction, Bursting and Dynamic Control of Vortices of a Cropped Double-delta Wing at High Angle of Attack
| Author | : Abdullah M. Alkhozam |
| Publisher | : |
| Total Pages | : 217 |
| Release | : 1994 |
| Genre | : |
| ISBN | : |
A flow visualization study of the vortical flow over a cropped double-delta wing model with sharp leading edges and its three derivatives with small geometric modifications (fillets) at the strake wing junction was conducted in the Naval Postgraduate School water tunnel using the dye-injection technique. The fillets increased the wing area of the baseline model by 1%. The main focus of this study was to evaluate the effect of fillets on vortex core trajectories, interactions and breakdown on the leeward surface at high angle of attack (AOA) with zero sideslip angle. Comparison of test results for different fillet shapes indicates delay in both vortex interaction and breakdown at high AOA, particularly for the diamond fillet shapes. The vortex breakdown data implies lift augmentation for both static and dynamic case, with the static data correlating well with recently published numerical data. High angle-of-attack aerodynamics, Effect of fillets on vortex core trajectories, Interaction and breakdown, Flow visualization by dye-injection technique, Static and dynamic water tunnel studies on double-delta wings.
Interaction, Bursting and Control of Vortices of A Cropped Double-Delta Wing at High Angle of Attac
| Author | : |
| Publisher | : |
| Total Pages | : 224 |
| Release | : 1994 |
| Genre | : |
| ISBN | : |
A flow visualization study of the vortical flow over a cropped double-delta wing model with sharp leading edges and its three derivatives with small geometric modifications (fillets) at the strake wing junction was conducted in the Naval Postgraduate School water tunnel using the dye-injection technique. The fillets increased the wing area of the baseline model by 1%. The main focus of this study was to evaluate the effect of fillets on vortex core trajectories, interactions and breakdown on the leeward surface at high angle of attack (AOA) with zero sideslip angle. Comparison of test results for different fillet shapes indicates delay in both vortex interaction and breakdown at high AOA, particularly for the diamond fillet shapes. The vortex breakdown data implies lift augmentation for both static and dynamic case, with the static data correlating well with recently published numerical data. High angle-of-attack aerodynamics, Effect of fillets on vortex core trajectories, Interaction and breakdown, Flow visualization by dye-injection technique, Static and dynamic water tunnel studies on double-delta wings.
