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Boundary layer transition measured by DIT on the PSP rotor in forward flightA well-defined reference set of data for CFD and comprehensive code validation for a scaled helicopter
main rotor with boundary layer transition in forward flight is presented (Fig. 1). The boundary layer
transition was measured using differential infrared thermography (DIT) on the top (suction) side of the
three-bladed NASA/Army “PSP rotor”, in the NASA Langley 14- by 22-Foot Subsonic Tunnel at an
advance ratio of 0.3 (115kt).
Document ID
20205009333
Acquisition Source
Ames Research Center
Document Type
Conference Paper
Authors
Anthony Gardner (German Aerospace Center Cologne, Germany)
Armin Weiss (German Aerospace Center Cologne, Germany)
James T Heineck (Ames Research Center Mountain View, California, United States)
Austin D Overmeyer (U.S. Army Hampton, Virgina, United States)
Hannah R Spooner (Ames Research Center Mountain View, California, United States)
Rohit Kumar Jain (U.S. Army Moffett Field, California, United States)
Claude Christian Wolf (German Aerospace Center Cologne, Germany)
Markus Raffel (German Aerospace Center Cologne, Germany)
Date Acquired
October 28, 2020
Subject Category
Aerodynamics
Meeting Information
Meeting: Vertical Flight Society Annual Forum
Location: West Palm Beach, FL
Country: US
Start Date: May 11, 2021
End Date: May 13, 2021
Sponsors: VFS - The Vertical Flight Society
Funding Number(s)
WBS: 664817.02.01.04.03.02
Distribution Limits
Public
Copyright
Public Use Permitted.
Keywords
Boundary layer transistion
Rotorcraft blades
Thermography
DIT

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