NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Back to Results
Stability and Control CFD Investigations of a Generic 53 Degree Swept UCAV ConfigurationNATO STO Task Group AVT-201 on "Extended Assessment of Reliable Stability & Control Prediction Methods for NATO Air Vehicles" is studying various computational approaches to predict stability and control parameters for aircraft undergoing non-linear flight conditions. This paper contributes an assessment through correlations with wind tunnel data for the state of aerodynamic predictive capability of time-accurate RANS methodology on the group's focus configuration, a 53deg swept and twisted lambda wing UCAV, undergoing a variety of roll, pitch, and yaw motions. The vehicle aerodynamics is dominated by the complex non-linear physics of round leading-edge vortex flow separation. Correlations with experimental data are made for static longitudinal/lateral sweeps, and at varying frequencies of prescribed roll/pitch/yaw sinusoidal motion for the vehicle operating with and without control surfaces. The data and the derived understanding should prove useful to the AVT-201 team and other researchers who are developing techniques for augmenting flight simulation models from low-speed CFD predictions of aircraft traversing non-linear regions of a flight envelope.
Document ID
20140011406
Document Type
Conference Paper
Authors
Frink, Neal T. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 8, 2014
Publication Date
June 16, 2014
Subject Category
Fluid Mechanics and Thermodynamics
Aircraft Stability and Control
Report/Patent Number
NF1676L-17572
AIAA Paper-2014-2133
Meeting Information
AIAA Aviation and Aeronautics Forum and Exposition (AVIATION 2014)(Atlanta, GA)
Funding Number(s)
WBS: WBS 284848.02.05.07.01
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

Available Downloads

NameType 20140011406.pdf STI