Simulation of 3D co-flow jet airfoil with embedded micro-compressor actuator

Yan Ren, GeCheng Zha

Research output: Chapter in Book/Report/Conference proceedingConference contribution

2 Citations (Scopus)

Abstract

This paper presents simulations of 3D co-flow jet (CFJ) active flow control airfoil with an embedded micro-compressor actuator. The injection and suction ducts geometries, slot locations and micro-compressor interface boundary conditions are determined based on the design of 2D CFJ airfoil and micro-compressor actuator. The simulations are performed at Mach number 0.15 to simulate the cruise condition of a general aviation aircraft. The airfoil used in this work is CFJ-NACA-6421. The simulations employ 3D RANS solver with Spalart-Allmaras (S-A) turbulence model, 3th order WENO scheme for the inviscid fluxes, and 2nd order central differencing for the viscous terms. The aerodynamic performance, energy expenditure, and 3D flow field are compared between the CFJ airfoils with different jet momentum coefficient (Cµ) and maximum swirl angle at the injection duct inlet (βmax). An CFJ airfoil with ideal ducts and a baseline airfoil are also studied as reference for comparison. The parametric study results show that the lift coefficient (CL) and power coefficient (Pc) linearly increase with the rise of Cµ, while the drag coefficient (CD) and productivity efficiency ((CL 2/CD)c) linearly decreases with the rise of Cµ. A large βmax leads to a more favorable mass flow rate distribution at the injection slot, which suppresses the flow separation at the injection slot edges and improves the aerodynamic performance. However, a too large βmax leads to flow separation inside the injection duct and increase the pumping energy loss. The results of this work will guide the future high efficiency CFJ airfoil design optimization and the design for wind tunnel testing with embedded micro-compressors.

Original languageEnglish (US)
Title of host publicationAIAA Aerospace Sciences Meeting
PublisherAmerican Institute of Aeronautics and Astronautics Inc, AIAA
Edition210059
ISBN (Print)9781624105241
DOIs
StatePublished - Jan 1 2018
EventAIAA Aerospace Sciences Meeting, 2018 - Kissimmee, United States
Duration: Jan 8 2018Jan 12 2018

Other

OtherAIAA Aerospace Sciences Meeting, 2018
CountryUnited States
CityKissimmee
Period1/8/181/12/18

Fingerprint

Airfoils
Compressors
Actuators
Ducts
Flow separation
Aerodynamics
Drag coefficient
Turbulence models
Flow control
Aviation
Mach number
Wind tunnels
Energy dissipation
Flow fields
Momentum
Productivity
Aircraft
Flow rate
Boundary conditions
Fluxes

ASJC Scopus subject areas

  • Aerospace Engineering

Cite this

Ren, Y., & Zha, G. (2018). Simulation of 3D co-flow jet airfoil with embedded micro-compressor actuator. In AIAA Aerospace Sciences Meeting (210059 ed.). American Institute of Aeronautics and Astronautics Inc, AIAA. https://doi.org/10.2514/6.2018-0330

Simulation of 3D co-flow jet airfoil with embedded micro-compressor actuator. / Ren, Yan; Zha, GeCheng.

AIAA Aerospace Sciences Meeting. 210059. ed. American Institute of Aeronautics and Astronautics Inc, AIAA, 2018.

Research output: Chapter in Book/Report/Conference proceedingConference contribution

Ren, Y & Zha, G 2018, Simulation of 3D co-flow jet airfoil with embedded micro-compressor actuator. in AIAA Aerospace Sciences Meeting. 210059 edn, American Institute of Aeronautics and Astronautics Inc, AIAA, AIAA Aerospace Sciences Meeting, 2018, Kissimmee, United States, 1/8/18. https://doi.org/10.2514/6.2018-0330
Ren Y, Zha G. Simulation of 3D co-flow jet airfoil with embedded micro-compressor actuator. In AIAA Aerospace Sciences Meeting. 210059 ed. American Institute of Aeronautics and Astronautics Inc, AIAA. 2018 https://doi.org/10.2514/6.2018-0330
Ren, Yan ; Zha, GeCheng. / Simulation of 3D co-flow jet airfoil with embedded micro-compressor actuator. AIAA Aerospace Sciences Meeting. 210059. ed. American Institute of Aeronautics and Astronautics Inc, AIAA, 2018.
@inproceedings{9942461efd8e4c17a16a740d3effcd6b,
title = "Simulation of 3D co-flow jet airfoil with embedded micro-compressor actuator",
abstract = "This paper presents simulations of 3D co-flow jet (CFJ) active flow control airfoil with an embedded micro-compressor actuator. The injection and suction ducts geometries, slot locations and micro-compressor interface boundary conditions are determined based on the design of 2D CFJ airfoil and micro-compressor actuator. The simulations are performed at Mach number 0.15 to simulate the cruise condition of a general aviation aircraft. The airfoil used in this work is CFJ-NACA-6421. The simulations employ 3D RANS solver with Spalart-Allmaras (S-A) turbulence model, 3th order WENO scheme for the inviscid fluxes, and 2nd order central differencing for the viscous terms. The aerodynamic performance, energy expenditure, and 3D flow field are compared between the CFJ airfoils with different jet momentum coefficient (Cµ) and maximum swirl angle at the injection duct inlet (βmax). An CFJ airfoil with ideal ducts and a baseline airfoil are also studied as reference for comparison. The parametric study results show that the lift coefficient (CL) and power coefficient (Pc) linearly increase with the rise of Cµ, while the drag coefficient (CD) and productivity efficiency ((CL 2/CD)c) linearly decreases with the rise of Cµ. A large βmax leads to a more favorable mass flow rate distribution at the injection slot, which suppresses the flow separation at the injection slot edges and improves the aerodynamic performance. However, a too large βmax leads to flow separation inside the injection duct and increase the pumping energy loss. The results of this work will guide the future high efficiency CFJ airfoil design optimization and the design for wind tunnel testing with embedded micro-compressors.",
author = "Yan Ren and GeCheng Zha",
year = "2018",
month = "1",
day = "1",
doi = "10.2514/6.2018-0330",
language = "English (US)",
isbn = "9781624105241",
booktitle = "AIAA Aerospace Sciences Meeting",
publisher = "American Institute of Aeronautics and Astronautics Inc, AIAA",
edition = "210059",

}

TY - GEN

T1 - Simulation of 3D co-flow jet airfoil with embedded micro-compressor actuator

AU - Ren, Yan

AU - Zha, GeCheng

PY - 2018/1/1

Y1 - 2018/1/1

N2 - This paper presents simulations of 3D co-flow jet (CFJ) active flow control airfoil with an embedded micro-compressor actuator. The injection and suction ducts geometries, slot locations and micro-compressor interface boundary conditions are determined based on the design of 2D CFJ airfoil and micro-compressor actuator. The simulations are performed at Mach number 0.15 to simulate the cruise condition of a general aviation aircraft. The airfoil used in this work is CFJ-NACA-6421. The simulations employ 3D RANS solver with Spalart-Allmaras (S-A) turbulence model, 3th order WENO scheme for the inviscid fluxes, and 2nd order central differencing for the viscous terms. The aerodynamic performance, energy expenditure, and 3D flow field are compared between the CFJ airfoils with different jet momentum coefficient (Cµ) and maximum swirl angle at the injection duct inlet (βmax). An CFJ airfoil with ideal ducts and a baseline airfoil are also studied as reference for comparison. The parametric study results show that the lift coefficient (CL) and power coefficient (Pc) linearly increase with the rise of Cµ, while the drag coefficient (CD) and productivity efficiency ((CL 2/CD)c) linearly decreases with the rise of Cµ. A large βmax leads to a more favorable mass flow rate distribution at the injection slot, which suppresses the flow separation at the injection slot edges and improves the aerodynamic performance. However, a too large βmax leads to flow separation inside the injection duct and increase the pumping energy loss. The results of this work will guide the future high efficiency CFJ airfoil design optimization and the design for wind tunnel testing with embedded micro-compressors.

AB - This paper presents simulations of 3D co-flow jet (CFJ) active flow control airfoil with an embedded micro-compressor actuator. The injection and suction ducts geometries, slot locations and micro-compressor interface boundary conditions are determined based on the design of 2D CFJ airfoil and micro-compressor actuator. The simulations are performed at Mach number 0.15 to simulate the cruise condition of a general aviation aircraft. The airfoil used in this work is CFJ-NACA-6421. The simulations employ 3D RANS solver with Spalart-Allmaras (S-A) turbulence model, 3th order WENO scheme for the inviscid fluxes, and 2nd order central differencing for the viscous terms. The aerodynamic performance, energy expenditure, and 3D flow field are compared between the CFJ airfoils with different jet momentum coefficient (Cµ) and maximum swirl angle at the injection duct inlet (βmax). An CFJ airfoil with ideal ducts and a baseline airfoil are also studied as reference for comparison. The parametric study results show that the lift coefficient (CL) and power coefficient (Pc) linearly increase with the rise of Cµ, while the drag coefficient (CD) and productivity efficiency ((CL 2/CD)c) linearly decreases with the rise of Cµ. A large βmax leads to a more favorable mass flow rate distribution at the injection slot, which suppresses the flow separation at the injection slot edges and improves the aerodynamic performance. However, a too large βmax leads to flow separation inside the injection duct and increase the pumping energy loss. The results of this work will guide the future high efficiency CFJ airfoil design optimization and the design for wind tunnel testing with embedded micro-compressors.

UR - http://www.scopus.com/inward/record.url?scp=85044368686&partnerID=8YFLogxK

UR - http://www.scopus.com/inward/citedby.url?scp=85044368686&partnerID=8YFLogxK

U2 - 10.2514/6.2018-0330

DO - 10.2514/6.2018-0330

M3 - Conference contribution

SN - 9781624105241

BT - AIAA Aerospace Sciences Meeting

PB - American Institute of Aeronautics and Astronautics Inc, AIAA

ER -