Computed and Experimental Flutter/LCO Onset for the Boeing Truss-Braced Wing Wind-Tunnel Model

NF1676L-17719 · NASA (NTRS) · 2014

Public domain · NASA (NTRS)Technical Reports

Overview

This paper presents high fidelity Navier-Stokes simulations of the Boeing Subsonic Ultra Green Aircraft Research truss-braced wing wind-tunnel model and compares the results to linear MSC. Nastran flutter analysis and preliminary data from a recent wind-tunnel test of that model at the NASA Langley…

Publisher: NASA (NTRS)
Document: NF1676L-17719
Year: 2014
Pages: 24

Document

+ + + + + = = ) ( ) ( ) ( ) = ( ) = = = + = = + D = 0.100 0.000 2 2 2 2 2 2 2 2 2 2 2 2 2 2 2 2 2 2 2 2 2 2 2 222 3 6 7 2 6 7 9 6 6 6 6 6 6 6 6 6 6 6 6 7 7 7 7 7 7 7 7 7 7 7 7 7 7 7 7 7 7 777 9 2 2 2 3 9 3 5 9 9 9 9 9 9 9 9 9 9 9 9 9 9 9 9 9 999 3 3 3 5 4 5 5 8 4 5 5 8 4 8 5 6 7 5 6 7 7 8 4 6 5 8 6 7 7 7 7 5 5 6 9 5 5 5 5 5 5 555 6 8 1 6 8 6 8 9 4 9 9 9 1 5 5 5 5 5 8 6 8 4 8 DAMP ING (G) 8 -0.100 -0.200 0. 50. 100. 150. 200.

VELOCITY (KEAS ) 30.0 9 9 9 9 9 9 9 9 9 9 9 9 9 9 9 9 9 9 9 9 999 8 8 8 8 8 8 8 9 9 9 9 9 9 9 8 8 8 8 8 8 8 8 8 8 8 8 8 8 8 8 8 8 8 8 888 7 7 7 7 7 7 7 7 7 7 7 7 7 7 7 7 7 7 7 7 777 7 7 7 7 7 7 7 6 6 6 6 6 6 6 6 6 6 6 6 6 6 6 6 6 6 6 6 666 6 6 6 6 6 6 6 20.0 5 5 5 5 5 5 5 5 5 5 5 5 5 5 5 5 5 5 5 5 5 5 5 5 5 5 555 4 4 4 4 4 4 4 4 3 3 3 3 3 3 3 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 444 FREQUENCY (HZ) 10.0 3 3 3 3 3 3 3 3 3 3 3 3 3 3 3 3 3 333 3 3 1 1 1 1 1 1 1 2 2 2 2 2 2 2 2 2 2 2 2 2 2 2 2 2 2 2 2 222 2 2 2 2 2 2 2 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 111 1 1 0.0 0. 50. 100. 150. 200.

VELOCITY (KEAS ) h = 1000 h = 700 Flutter/Strong LCO Weak LCO h = 500 Stable Dynamic pressure, psf h = 300 h = 200 0.5 0.6 0.7 0.8 0.9 1 Mach Number = h = 1000 h = 700 Flutter/Strong LCO Weak LCO Stable h = 500 Torsion Dynamic pressure, psf h = 300 h = 200 0.5 0.6 0.7 0.8 0.9 1 Mach Number = +