Towards full-scale fuselage drag reduction computations using fluidic oscillators

Nicholson K. Koukpaizan; Ari Glezer; Marilyn J. Smith

Towards full-scale fuselage drag reduction computations using fluidic oscillators

Nicholson K. Koukpaizan, Ari Glezer, Marilyn J. Smith

Advanced Computing for Life Sciences and

Research output: Contribution to conference › Paper › peer-review

Abstract

Computations were performed to assess the effect of fluidically-oscillating jets on a ROBIN-mod7 helicopter fuselage. The simulations utilize previously experimentally validated methodologies that rely on a new boundary condition formulation at the actuator throats, based on phase-averaged flow variables, which obviates the need to resolve the internal cavities simultaneously with the outer flow. Predictions of the base flow past the helicopter fuselage were validated against experimental and computational data available in the literature. The fluidic oscillator characteristics were then evaluated at different scales and pressure ratios, and invariant quantities were identified. In the flow control evaluation, flow separation was significantly reduced and, in some cases, suppressed. However, drag reduction was not obtained, indicating the sensitivity of the actuation location and operating conditions to the vehicle design and flight orientation.

Original language	English
State	Published - 2020
Event	Vertical Flight Society's 76th Annual Forum and Technology Display - Virtual, Online Duration: Oct 5 2020 → Oct 8 2020

Conference

Conference	Vertical Flight Society's 76th Annual Forum and Technology Display
City	Virtual, Online
Period	10/5/20 → 10/8/20

Funding

This research was partially funded through the U.S. Army/Navy/NASA Vertical Lift Research Center of Excellence at Georgia Tech via Task 5 under the direction of Mahendra Bhagwat of ADD-A, Agreement No. W911W6-17-2-0002. Computational time was, in part, provided through the Department of Defense (DoD) high Performance Computing Modernization Program (HPCMP) from the DoD HPC Center AFRL DSRC. Roger Strawn was the S/AAA for this HPC time, and his support is gratefully acknowledged. The U.S. Government is authorized to reproduce and distribute reprints for Government purposes notwithstanding any copyright notation thereon. The views and conclusions contained in this document are those of the authors and should not be interpreted as representing the official policies, either expressed or implied, of the US Army Aviation Development Directorate, CCDC AvMC or the U.S. Government.

Funders	Funder number
DoD HPC Center AFRL DSRC
U.S. Department of Defense

Cite this

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title = "Towards full-scale fuselage drag reduction computations using fluidic oscillators",

abstract = "Computations were performed to assess the effect of fluidically-oscillating jets on a ROBIN-mod7 helicopter fuselage. The simulations utilize previously experimentally validated methodologies that rely on a new boundary condition formulation at the actuator throats, based on phase-averaged flow variables, which obviates the need to resolve the internal cavities simultaneously with the outer flow. Predictions of the base flow past the helicopter fuselage were validated against experimental and computational data available in the literature. The fluidic oscillator characteristics were then evaluated at different scales and pressure ratios, and invariant quantities were identified. In the flow control evaluation, flow separation was significantly reduced and, in some cases, suppressed. However, drag reduction was not obtained, indicating the sensitivity of the actuation location and operating conditions to the vehicle design and flight orientation.",

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AU - Koukpaizan, Nicholson K.

AU - Glezer, Ari

AU - Smith, Marilyn J.

PY - 2020

Y1 - 2020

N2 - Computations were performed to assess the effect of fluidically-oscillating jets on a ROBIN-mod7 helicopter fuselage. The simulations utilize previously experimentally validated methodologies that rely on a new boundary condition formulation at the actuator throats, based on phase-averaged flow variables, which obviates the need to resolve the internal cavities simultaneously with the outer flow. Predictions of the base flow past the helicopter fuselage were validated against experimental and computational data available in the literature. The fluidic oscillator characteristics were then evaluated at different scales and pressure ratios, and invariant quantities were identified. In the flow control evaluation, flow separation was significantly reduced and, in some cases, suppressed. However, drag reduction was not obtained, indicating the sensitivity of the actuation location and operating conditions to the vehicle design and flight orientation.

AB - Computations were performed to assess the effect of fluidically-oscillating jets on a ROBIN-mod7 helicopter fuselage. The simulations utilize previously experimentally validated methodologies that rely on a new boundary condition formulation at the actuator throats, based on phase-averaged flow variables, which obviates the need to resolve the internal cavities simultaneously with the outer flow. Predictions of the base flow past the helicopter fuselage were validated against experimental and computational data available in the literature. The fluidic oscillator characteristics were then evaluated at different scales and pressure ratios, and invariant quantities were identified. In the flow control evaluation, flow separation was significantly reduced and, in some cases, suppressed. However, drag reduction was not obtained, indicating the sensitivity of the actuation location and operating conditions to the vehicle design and flight orientation.

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M3 - Paper

AN - SCOPUS:85096909423

T2 - Vertical Flight Society's 76th Annual Forum and Technology Display

Y2 - 5 October 2020 through 8 October 2020

ER -

Towards full-scale fuselage drag reduction computations using fluidic oscillators

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