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Record Details

Record 17 of 911
Transonic analysis of canted winglets
Author and Affiliation:
Rosen, B. S.(Grumman Aerospace Corp., Bethpage, NY, United States)
Abstract: A computational method developed to provide a transonic analysis for upper/lower surface wing-tip mounted winglets is described. Winglets with arbitrary planform, cant and toe angle, and airfoil section can be modeled. The embedded grid approach provides high flow field resolution and the required geometric flexibility. In particular, coupled Cartesian/cylindrical grid systems are used to model the complex geometry presented by canted upper/lower surface winglets. A new rotated difference scheme is introduced in order to maintain the stability of the small-disturbance formulation in the presence of large spanwise velocities. Wing and winglet viscous effects are modeled using a two-dimensional 'strip' boundary layer analysis. Correlations with wind tunnel and flight test data for three transport configurations are included.
Publication Date: Jan 01, 1984
Document ID:
19840035222
(Acquired Nov 28, 1995)
Accession Number: 84A18009
Subject Category: AERODYNAMICS
Report/Patent Number: AIAA PAPER 84-0302
Document Type: Preprint
Publisher Information: United States
Contract/Grant/Task Num: NAS1-14732
Financial Sponsor: NASA; United States
Organization Source: Grumman Aerospace Corp.; Bethpage, NY, United States
Description: 11p; In English
Distribution Limits: Unclassified; Publicly available; Unlimited
Rights: Copyright
NASA Terms: COMPUTATIONAL FLUID DYNAMICS; TRANSONIC FLOW; WINGLETS; C-135 AIRCRAFT; CARTESIAN COORDINATES; COMPUTATIONAL GRIDS; FINITE DIFFERENCE THEORY; PRESSURE DISTRIBUTION; TRANSPORT AIRCRAFT
Imprint And Other Notes: American Institute of Aeronautics and Astronautics, Aerospace Sciences Meeting, 22nd, Reno, NV, Jan. 9-12, 1984. 11 p.
Availability Source: Other Sources
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