An apparatus for experimental research into unsteady transonic flows is described. The apparatus, as installed in the NASA-Ames 11 by 11 Foot Transonic Wind Tunnel, can impart full two-degree-of-freedom motions at reduced frequencies to 0.3, oscillatory amplitudes to tn-2 degs, mean angles to 12 degs, Mach numbers to 1.4 and Reynolds numbers to 12x10. The test wing is fully instrumented for dynamic waveform measurements and the data can be acquired, processed, and displayed in real-time with a new computational data acquisition system. Following a description of the apparatus, sample data from a recently completed test program is presented.
A new two-dimensional oscillating wing apparatus for unsteady aerodynamics research
1978-01-01
Aufsatz (Konferenz)
Keine Angabe
Englisch
High attitude delta wing unsteady aerodynamics
AIAA | 1974
|Unsteady Aerodynamics of an Oscillating Fastback Model
SAE Technical Papers | 2013
|Aerodynamics of Wing with Oscillating Wingtip Flapper
AIAA | 2016
|Unsteady aerodynamics of a diamond wing configuration
Online Contents | 2018
|