NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Back to Results
Computational study of the aerodynamics and control by blowing of asymmetric vortical flows over delta wingsSome of the work is described which was done in a study of the flow field produced by tangential leading edge blowing on a 60 deg. delta wing. The flow is studied computationally by solving the Thin Layer Navier-Stokes equations. Steady state flow fields are calculated for various angles of attack and yaw, with and without the presence of tangential leading edge blowing. The effectiveness of blowing as a rolling moment control mechanism to extend the envelope of controllability is illustrated at pre- and post-stall angles of attack. The numerical grid is generated using algebraic grid generation and various interpolation and blending techniques. The jet emanates from a slot with linearly varying thickness and is introduced into the flow field using the concept of an actuator plane, thereby not requiring resolution of the jet slot geometry. The Baldwin-Lomax algebraic turbulence model is used to provide turbulent closure. The computational results are compared with those of experiments.
Document ID
19920001772
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Craig, Ken
(Stanford Univ. CA, United States)
Date Acquired
September 6, 2013
Publication Date
September 1, 1991
Subject Category
Aerodynamics
Report/Patent Number
NAS 1.26:187979
NASA-CR-187979
JIAA-TR-104
Accession Number
92N10990
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
No Preview Available