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Active Flow Control on Vertical Tail Models.

Marlyn Y Andino1, John C Lin1, Seele Roman2

  • 1NASA Langley Research Center, Hampton, Virginia 23681.

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Summary
This summary is machine-generated.

Active flow control experiments demonstrated significant side force increases on a vertical tail model using fluidic oscillators. A 1% momentum coefficient achieved 30-50% side force enhancement, crucial for scaling to full-size aircraft.

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Area of Science:

  • Aerospace Engineering
  • Fluid Dynamics
  • Active Flow Control

Background:

  • Flow separation on aircraft control surfaces can degrade performance.
  • Active flow control (AFC) offers a method to mitigate separation.
  • Fluidic oscillators are a promising AFC technology.

Purpose of the Study:

  • To investigate the effectiveness of fluidic oscillators for active flow control on a vertical tail model.
  • To determine the relationship between momentum coefficient and side force enhancement.
  • To establish scaling parameters for AFC systems from subscale to full-scale applications.

Main Methods:

  • Subscale wind tunnel experiments on a generic vertical tail model at low speeds.
  • Implementation of fluidic oscillators at the trailing edge of the vertical stabilizer.
  • Systematic variation of momentum coefficient (C_micro) to measure side force changes.

Main Results:

  • Achieved side force increases exceeding 50% with a 2% momentum coefficient.
  • Demonstrated a 30-50% side force increase with a 1% momentum coefficient.
  • Identified C_micro as a critical parameter for scaling AFC systems.

Conclusions:

  • Fluidic oscillator AFC effectively delays or prevents flow separation on vertical tails.
  • The momentum coefficient is key for successful scaling of fluidic oscillator AFC systems.
  • Results support the use of fluidic oscillators for full-scale flight testing and aircraft applications.