Dynamic wind-tunnel testing using captive flight method

Koji Fukami, Shin-Ichiro Higashino, Akira Sakurai

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

Abstract

This paper presents the concept of dynamic wind tunnel testing using captive flight method, in which the airplane is supported by three elastic lines mainly in the vertical direction, and given oscillatory motions by an external actuator. This experimental method is designed for the aerodynamic parameter estimation. All of the captive flight modes are second-order systems. Longitudinal and lateral dynamic tests are carried out sweeping driving frequency, and every mode except surging motion, of which damping is weak, was excited. This experiment method has the advantages of the experimental simplicity, quite small aerodynamic interference, stable flight and the capability of excitation of motion necessary for the estimation.

Original languageEnglish
Title of host publicationCollection of Technical Papers - AIAA Atmospheric Flight Mechanics Conference
Pages1035-1039
Number of pages5
Publication statusPublished - Dec 1 2004
EventCollection of Technical Papers - AIAA Atmospheric Flight Mechanics Conference - Providence, RI, United States
Duration: Aug 16 2004Aug 19 2004

Publication series

NameCollection of Technical Papers - AIAA Atmospheric Flight Mechanics Conference
Volume2

Other

OtherCollection of Technical Papers - AIAA Atmospheric Flight Mechanics Conference
CountryUnited States
CityProvidence, RI
Period8/16/048/19/04

All Science Journal Classification (ASJC) codes

  • Engineering(all)

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