Computational assessment of the hvab rotor in hover using laminar-turbulent transition modeling

Jared A. Carnes, James G. Coder

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

6 Scopus citations


Hover predictions of the Hover Validation and Acoustic Baseline (HVAB) rotor are made using a computational fluid dynamics approach. Solutions are generated using the NASA OVERFLOW 2.2n solver with both hybrid RANS/LES and laminar-turbulent transition modeling enabled. Solutions are based on a hover tip Mach number of 0.675 for a pre-deformed rotor with prescribed collective pitch, lag, and coning angles. Grid generation and computational methods are described. The rotor flowfield is analyzed and the effect of the transition model is assessed through comparison to predictions made using a fully-turbulent modeling approach.

Original languageEnglish (US)
Title of host publicationAIAA Scitech 2019 Forum
PublisherAmerican Institute of Aeronautics and Astronautics Inc, AIAA
ISBN (Print)9781624105784
StatePublished - 2019
EventAIAA Scitech Forum, 2019 - San Diego, United States
Duration: Jan 7 2019Jan 11 2019

Publication series

NameAIAA Scitech 2019 Forum


ConferenceAIAA Scitech Forum, 2019
Country/TerritoryUnited States
CitySan Diego

All Science Journal Classification (ASJC) codes

  • Aerospace Engineering


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