Transonic shock-induced dynamics of a flexible wing with a thick circular-arc airfoil

Bennett, Robert M.; Dansberry, Brian E.; Farmer, M. G.; Eckstrom, Clinton V.; Seidel, David A.

doi:10.2514/6.1991-1107

Cited by 2 publications

(1 citation statement)

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“…4 possesses a pitch inertia of 65,000 lbm-in. 2 , which corresponds to design point 1 in Table 1. The inertia model and actuator angular positions were measured using an angular displacement transducer.…”

Section: Ott Shakedown Test Resultsmentioning

confidence: 99%

Oscillating Turntable for the Measurement of Unsteady Aerodynamic Phenomena

Piatak

Cleckner

2003

Journal of Aircraft

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A new forced oscillation system has been installed and tested at NASA Langley Research Center's Transonic Dynamics Tunnel. The system is known as the Oscillating Turntable (OTT) and has been designed for the purpose of oscillating, large semispan models in pitch at frequencies up to 40 Hz to acquire high-quality unsteady pressure and loads data. Precisely controlled motions of a wind-tunnel model on the OTT can yield unsteady aerodynamic phenomena associated with utter, limit-cycle oscillations, shock dynamics, and nonlinear aerodynamic effects on many vehicle con gurations. This paper will discuss the general design and components of the OTT and will present data from performance testing and from research tests on two rigid semispan wind-tunnel models. The research tests were designed to challenge the OTT over a wide range of operating conditions while acquiring unsteady pressure data on a small rectangular supercritical wing and a large supersonic transport wing. These results will be presented to illustrate the performance capabilities, consistency of oscillations, and usefulness of the OTT as a research tool. NomenclatureC p =deg = pressure coef cient normalized by oscillation amplitude .C p / Im =deg = imaginary component of pressure coef cient normalized by oscillation amplitude .C p / mean = mean pressure coef cient .C p / Re =deg = real component of pressure coef cient normalized by oscillation amplitude f = frequency, Hz k = reduced frequency M = Mach number Q = dynamic pressure, psf Re = Reynolds number x=c = nondimensional chordwise location N ® = mean angle of attack, deg j®j = angular amplitude, deg 1 P = hydraulic pressure amplitude, psi

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Section: Ott Shakedown Test Resultsmentioning

confidence: 99%