Force and moment test on a low boom configuration in Glenn's 8 × 6 wind tunnel

Thomas R. Wayman, George R. Hicks, Jason M Merret

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

Abstract

Experimental aerodynamic data are presented for a wind tunnel model of a low-boom aircraft concept conducted in the NASA Glenn Research Center 8- by 6-foot Supersonic Wind Tunnel. This aircraft concept, originally designed for experimental investigations of off-body acoustics, was modified to characterize aerodynamic performance and stability parameters across a wide range of Mach numbers. Data has been obtained at chord Reynolds numbers of 1.2 to 3.9×106 and Mach numbers from 0.6 to 1.56 for the configuration. Force and moment, surface pressure, and surface visualization data were obtained but the focus of this paper will be to describe the force and moment data only.

Original languageEnglish (US)
Title of host publication29th AIAA Applied Aerodynamics Conference 2011
StatePublished - Dec 1 2011
Externally publishedYes
Event29th AIAA Applied Aerodynamics Conference 2011 - Honolulu, HI, United States
Duration: Jun 27 2011Jun 30 2011

Other

Other29th AIAA Applied Aerodynamics Conference 2011
CountryUnited States
CityHonolulu, HI
Period6/27/116/30/11

ASJC Scopus subject areas

  • Aerospace Engineering
  • Mechanical Engineering

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    Wayman, T. R., Hicks, G. R., & Merret, J. M. (2011). Force and moment test on a low boom configuration in Glenn's 8 × 6 wind tunnel. In 29th AIAA Applied Aerodynamics Conference 2011