Project Title:

Computation of Tip Flow Field in Advanced Aircraft Propellers

01.01-0511A
Computation of Tip Flow Field in Advanced Aircraft Propellers
Scientific Research Associates Inc.
PO Box 498
Glastonbury
CT
06033
Levy
Ralph
NAS3-24881
Amount:   
LeRC
NAS3-24532

Abstract:

   The Phase I effort has established the feasibility of computing the tipflow field in advanced aircraft propellers using a forward-marching computation procedure.
 The innovative effort has demonstrated the capability of the forward-marching procedure
to compute generation and roll-up the tip vortex in high subsonic Mach numbers and
in high Reynolds number turbulent flows.  Additional tasks, beyond the scope of the
Phase I Statement of Work, have demonstrated capability in handling complex geometry
of advanced propeller blades.

The proposed Phase II effort would extend capabilities demonstrated by the Phase
I innovations.  The objective of the Phase II study would be to provide a computer
code of verified accuracy capable of predicting the tip flow field in advanced propeller
blades.  Such a computer code would be a valuable tool in the design of advanced
propeller blades and the analysis of propeller performance.  In particular, such
a code would be valuable in computing the effects of details of propeller tip geometry
on tip vortex generation and suppression.  Specific tasks have been identified in
the Phase II proposal to accomplish the above-mentioned objectives.