Super-lift coefficient of active flow control airfoil

What is the limit?

Yunchao Yang, GeCheng Zha

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

9 Citations (Scopus)

Abstract

This paper studies the enhancement of maximum lift coefficient and cruise efficiency using Co-Flow Jet (CFJ) active flow control airfoils. For potential flows, the maximum lift coefficient limit is derived as CLmax = 2π(1+t/c) for any airfoil with thickness of t=c. The present study indicates that the CFJ active flow control airfoil is able to achieve the maximum lift coefficient that far exceeds the theoretical limit. It is named super-lift coefficient. The research is based on validated CFD simulation, which employs 2D RANS solver with Spalart-Allmaras(S-A) turbulence model, 5th order WENO scheme for the inviscid fluxes, and 4th order central differencing for the viscous terms. The momentum coefficient Cµ studied is from 0.02 to 0.60 and the angle of attack (AoA) is from 0° to 74°.

Original languageEnglish (US)
Title of host publicationAIAA SciTech Forum - 55th AIAA Aerospace Sciences Meeting
PublisherAmerican Institute of Aeronautics and Astronautics Inc.
ISBN (Electronic)9781624104473
DOIs
StatePublished - 2017
Event55th AIAA Aerospace Sciences Meeting - Grapevine, United States
Duration: Jan 9 2017Jan 13 2017

Other

Other55th AIAA Aerospace Sciences Meeting
CountryUnited States
CityGrapevine
Period1/9/171/13/17

Fingerprint

Airfoils
Flow control
Potential flow
Angle of attack
Turbulence models
Momentum
Computational fluid dynamics
Fluxes

ASJC Scopus subject areas

  • Aerospace Engineering

Cite this

Yang, Y., & Zha, G. (2017). Super-lift coefficient of active flow control airfoil: What is the limit? In AIAA SciTech Forum - 55th AIAA Aerospace Sciences Meeting [AIAA 2017-1693] American Institute of Aeronautics and Astronautics Inc.. https://doi.org/10.2514/6.2017-1693

Super-lift coefficient of active flow control airfoil : What is the limit? / Yang, Yunchao; Zha, GeCheng.

AIAA SciTech Forum - 55th AIAA Aerospace Sciences Meeting. American Institute of Aeronautics and Astronautics Inc., 2017. AIAA 2017-1693.

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

Yang, Y & Zha, G 2017, Super-lift coefficient of active flow control airfoil: What is the limit? in AIAA SciTech Forum - 55th AIAA Aerospace Sciences Meeting., AIAA 2017-1693, American Institute of Aeronautics and Astronautics Inc., 55th AIAA Aerospace Sciences Meeting, Grapevine, United States, 1/9/17. https://doi.org/10.2514/6.2017-1693
Yang Y, Zha G. Super-lift coefficient of active flow control airfoil: What is the limit? In AIAA SciTech Forum - 55th AIAA Aerospace Sciences Meeting. American Institute of Aeronautics and Astronautics Inc. 2017. AIAA 2017-1693 https://doi.org/10.2514/6.2017-1693
Yang, Yunchao ; Zha, GeCheng. / Super-lift coefficient of active flow control airfoil : What is the limit?. AIAA SciTech Forum - 55th AIAA Aerospace Sciences Meeting. American Institute of Aeronautics and Astronautics Inc., 2017.
@inproceedings{386ecf1656b848f29fb11b242c749019,
title = "Super-lift coefficient of active flow control airfoil: What is the limit?",
abstract = "This paper studies the enhancement of maximum lift coefficient and cruise efficiency using Co-Flow Jet (CFJ) active flow control airfoils. For potential flows, the maximum lift coefficient limit is derived as CLmax = 2π(1+t/c) for any airfoil with thickness of t=c. The present study indicates that the CFJ active flow control airfoil is able to achieve the maximum lift coefficient that far exceeds the theoretical limit. It is named super-lift coefficient. The research is based on validated CFD simulation, which employs 2D RANS solver with Spalart-Allmaras(S-A) turbulence model, 5th order WENO scheme for the inviscid fluxes, and 4th order central differencing for the viscous terms. The momentum coefficient Cµ studied is from 0.02 to 0.60 and the angle of attack (AoA) is from 0° to 74°.",
author = "Yunchao Yang and GeCheng Zha",
year = "2017",
doi = "10.2514/6.2017-1693",
language = "English (US)",
booktitle = "AIAA SciTech Forum - 55th AIAA Aerospace Sciences Meeting",
publisher = "American Institute of Aeronautics and Astronautics Inc.",

}

TY - GEN

T1 - Super-lift coefficient of active flow control airfoil

T2 - What is the limit?

AU - Yang, Yunchao

AU - Zha, GeCheng

PY - 2017

Y1 - 2017

N2 - This paper studies the enhancement of maximum lift coefficient and cruise efficiency using Co-Flow Jet (CFJ) active flow control airfoils. For potential flows, the maximum lift coefficient limit is derived as CLmax = 2π(1+t/c) for any airfoil with thickness of t=c. The present study indicates that the CFJ active flow control airfoil is able to achieve the maximum lift coefficient that far exceeds the theoretical limit. It is named super-lift coefficient. The research is based on validated CFD simulation, which employs 2D RANS solver with Spalart-Allmaras(S-A) turbulence model, 5th order WENO scheme for the inviscid fluxes, and 4th order central differencing for the viscous terms. The momentum coefficient Cµ studied is from 0.02 to 0.60 and the angle of attack (AoA) is from 0° to 74°.

AB - This paper studies the enhancement of maximum lift coefficient and cruise efficiency using Co-Flow Jet (CFJ) active flow control airfoils. For potential flows, the maximum lift coefficient limit is derived as CLmax = 2π(1+t/c) for any airfoil with thickness of t=c. The present study indicates that the CFJ active flow control airfoil is able to achieve the maximum lift coefficient that far exceeds the theoretical limit. It is named super-lift coefficient. The research is based on validated CFD simulation, which employs 2D RANS solver with Spalart-Allmaras(S-A) turbulence model, 5th order WENO scheme for the inviscid fluxes, and 4th order central differencing for the viscous terms. The momentum coefficient Cµ studied is from 0.02 to 0.60 and the angle of attack (AoA) is from 0° to 74°.

UR - http://www.scopus.com/inward/record.url?scp=85017195323&partnerID=8YFLogxK

UR - http://www.scopus.com/inward/citedby.url?scp=85017195323&partnerID=8YFLogxK

U2 - 10.2514/6.2017-1693

DO - 10.2514/6.2017-1693

M3 - Conference contribution

BT - AIAA SciTech Forum - 55th AIAA Aerospace Sciences Meeting

PB - American Institute of Aeronautics and Astronautics Inc.

ER -