Active Flow Control on Vertical Tail Models

Andino, Marlyn Y [Point of Contact] ; Lin, John C ; Roman, Seele ; Graff, Emilio C ; Gharib, Mory ; Whalen, Edward A ; Wygnanski, Israel J

关键词: ACTIVE CONTROL;    BOEING 757 AIRCRAFT;    BOUNDARY LAYER SEPARATION;    FLOW DISTRIBUTION;    FLUIDICS;    FULL SCALE TESTS;    OSCILLATORS;    SEPARATED FLOW;    STABILIZERS (FLUID DYNAMICS);    SWEPT WINGS;    TAIL ASSEMBLIES;    TRAILING EDGES;    WIND TUNNEL TESTS;   

RP-ID  :  NF1676L-29550

学科分类：力学，机械学

美国|英语

来源: NASA Technical Reports Server

【 摘 要 】

Active flow control (AFC) subscale experiments were conducted at the Lucas Wind Tunnel of the California Institute of Technology. Tests were performed on a generic vertical tail model at low speeds. Fluidic oscillators were used at the trailing edge of the main element (vertical stabilizer) to redirect the flow over the rudder and delay or prevent flow separation. Side force increases in excess of 50% were achieved with a 2% momentum coefficient (C(sub μ)) input. The results indicated that a collective C(sub μ) of about 1% could increase the side force by 30–50%. This result is achieved by reducing the spanwise flow on the swept back wings that contributes to early flow separation near their tips. These experiments provided the technical backdrop to test the full-scale Boeing 757 vertical tail model equipped with a fluidic oscillator system at the National Full-scale Aerodynamics Complex 40-by 80-foot Wind Tunnel, NASA Ames Research Center. The C(sub μ) is shown to be an important parameter for scaling a fluidic oscillator AFC system from subscale to full-scale wind tunnel tests. The results of these tests provided the required rationale to use a fluidic oscillator AFC configuration for a follow-on flight test on the Boeing 757 ecoDemonstrator.