CFD hover predictions including boundary-layer transition

Bernardo A.O. Vieira, Michael P. Kinzel, Mark David Maughmer

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

6 Citations (Scopus)

Abstract

Computational fluid dynamics predictions of a helicopter in hover remain a challenge due to the tight interaction between the complex wake system and the rotor. This work focuses on model-scale hover predictions using a Reynolds averaged Navier-Stokes model supplemented with an approximate e n envelope method transition model. These simulations are performed to evaluate the ability of the model to predict natural laminar-turbulent transition and its impact on rotor performance. The predicted transition locations and rotor figure of merit are compared with experimental measurements obtained from a joint U.S. Army/NASA hover test campaign conducted at NASA Langley Research Center. Figure of merit predictions obtained with and without the transition model align well with experiments with natural and forced transition, respectively. The predicted transition locations are also in good agreement with experiments for most of the thrust conditions. This study suggests that the present modeling approach is reasonably accurate for predicting transition on rotor blades, but also identifies areas for potential improvements.

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 - Jan 1 2017
Event55th AIAA Aerospace Sciences Meeting - Grapevine, United States
Duration: Jan 9 2017Jan 13 2017

Publication series

NameAIAA SciTech Forum - 55th AIAA Aerospace Sciences Meeting

Other

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

Fingerprint

Computational fluid dynamics
Boundary layers
Rotors
NASA
Helicopters
Turbomachine blades
Experiments

All Science Journal Classification (ASJC) codes

  • Aerospace Engineering

Cite this

Vieira, B. A. O., Kinzel, M. P., & Maughmer, M. D. (2017). CFD hover predictions including boundary-layer transition. In AIAA SciTech Forum - 55th AIAA Aerospace Sciences Meeting [AIAA 2017-1665] (AIAA SciTech Forum - 55th AIAA Aerospace Sciences Meeting). American Institute of Aeronautics and Astronautics Inc.. https://doi.org/10.2514/6.2017-1665
Vieira, Bernardo A.O. ; Kinzel, Michael P. ; Maughmer, Mark David. / CFD hover predictions including boundary-layer transition. AIAA SciTech Forum - 55th AIAA Aerospace Sciences Meeting. American Institute of Aeronautics and Astronautics Inc., 2017. (AIAA SciTech Forum - 55th AIAA Aerospace Sciences Meeting).
@inproceedings{9bf8f9fe06cd4ff8b9efa50e65a8b5fc,
title = "CFD hover predictions including boundary-layer transition",
abstract = "Computational fluid dynamics predictions of a helicopter in hover remain a challenge due to the tight interaction between the complex wake system and the rotor. This work focuses on model-scale hover predictions using a Reynolds averaged Navier-Stokes model supplemented with an approximate e n envelope method transition model. These simulations are performed to evaluate the ability of the model to predict natural laminar-turbulent transition and its impact on rotor performance. The predicted transition locations and rotor figure of merit are compared with experimental measurements obtained from a joint U.S. Army/NASA hover test campaign conducted at NASA Langley Research Center. Figure of merit predictions obtained with and without the transition model align well with experiments with natural and forced transition, respectively. The predicted transition locations are also in good agreement with experiments for most of the thrust conditions. This study suggests that the present modeling approach is reasonably accurate for predicting transition on rotor blades, but also identifies areas for potential improvements.",
author = "Vieira, {Bernardo A.O.} and Kinzel, {Michael P.} and Maughmer, {Mark David}",
year = "2017",
month = "1",
day = "1",
doi = "10.2514/6.2017-1665",
language = "English (US)",
series = "AIAA SciTech Forum - 55th AIAA Aerospace Sciences Meeting",
publisher = "American Institute of Aeronautics and Astronautics Inc.",
booktitle = "AIAA SciTech Forum - 55th AIAA Aerospace Sciences Meeting",

}

Vieira, BAO, Kinzel, MP & Maughmer, MD 2017, CFD hover predictions including boundary-layer transition. in AIAA SciTech Forum - 55th AIAA Aerospace Sciences Meeting., AIAA 2017-1665, AIAA SciTech Forum - 55th AIAA Aerospace Sciences Meeting, American Institute of Aeronautics and Astronautics Inc., 55th AIAA Aerospace Sciences Meeting, Grapevine, United States, 1/9/17. https://doi.org/10.2514/6.2017-1665

CFD hover predictions including boundary-layer transition. / Vieira, Bernardo A.O.; Kinzel, Michael P.; Maughmer, Mark David.

AIAA SciTech Forum - 55th AIAA Aerospace Sciences Meeting. American Institute of Aeronautics and Astronautics Inc., 2017. AIAA 2017-1665 (AIAA SciTech Forum - 55th AIAA Aerospace Sciences Meeting).

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

TY - GEN

T1 - CFD hover predictions including boundary-layer transition

AU - Vieira, Bernardo A.O.

AU - Kinzel, Michael P.

AU - Maughmer, Mark David

PY - 2017/1/1

Y1 - 2017/1/1

N2 - Computational fluid dynamics predictions of a helicopter in hover remain a challenge due to the tight interaction between the complex wake system and the rotor. This work focuses on model-scale hover predictions using a Reynolds averaged Navier-Stokes model supplemented with an approximate e n envelope method transition model. These simulations are performed to evaluate the ability of the model to predict natural laminar-turbulent transition and its impact on rotor performance. The predicted transition locations and rotor figure of merit are compared with experimental measurements obtained from a joint U.S. Army/NASA hover test campaign conducted at NASA Langley Research Center. Figure of merit predictions obtained with and without the transition model align well with experiments with natural and forced transition, respectively. The predicted transition locations are also in good agreement with experiments for most of the thrust conditions. This study suggests that the present modeling approach is reasonably accurate for predicting transition on rotor blades, but also identifies areas for potential improvements.

AB - Computational fluid dynamics predictions of a helicopter in hover remain a challenge due to the tight interaction between the complex wake system and the rotor. This work focuses on model-scale hover predictions using a Reynolds averaged Navier-Stokes model supplemented with an approximate e n envelope method transition model. These simulations are performed to evaluate the ability of the model to predict natural laminar-turbulent transition and its impact on rotor performance. The predicted transition locations and rotor figure of merit are compared with experimental measurements obtained from a joint U.S. Army/NASA hover test campaign conducted at NASA Langley Research Center. Figure of merit predictions obtained with and without the transition model align well with experiments with natural and forced transition, respectively. The predicted transition locations are also in good agreement with experiments for most of the thrust conditions. This study suggests that the present modeling approach is reasonably accurate for predicting transition on rotor blades, but also identifies areas for potential improvements.

UR - http://www.scopus.com/inward/record.url?scp=85017224991&partnerID=8YFLogxK

UR - http://www.scopus.com/inward/citedby.url?scp=85017224991&partnerID=8YFLogxK

U2 - 10.2514/6.2017-1665

DO - 10.2514/6.2017-1665

M3 - Conference contribution

T3 - AIAA SciTech Forum - 55th AIAA Aerospace Sciences Meeting

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

PB - American Institute of Aeronautics and Astronautics Inc.

ER -

Vieira BAO, Kinzel MP, Maughmer MD. CFD hover predictions including boundary-layer transition. In AIAA SciTech Forum - 55th AIAA Aerospace Sciences Meeting. American Institute of Aeronautics and Astronautics Inc. 2017. AIAA 2017-1665. (AIAA SciTech Forum - 55th AIAA Aerospace Sciences Meeting). https://doi.org/10.2514/6.2017-1665