A Summary of the Effects of Reynolds Number on Drag Divergence for Airfoils Tested in the Langley 0.3-Meter Transonic Cryogenic Tunnel NASA Langley Research Center

Format:

Conference/Event

Author/Creator:

Jenkins, Renaldo V., author.

Conference Name:

SAE Aerospace Technology Conference and Exposition (1986-10-13 : Long Beach, California, United States)

Language:

English

Physical Description:

1 online resource

Place of Publication:

Warrendale, PA SAE International 1986

Summary:

The direct first order effect of Reynolds number on the determination of drag-divergence conditions is summarized for six airfoils which were tested in the Langley 0.3-Meter Transonic Cryogenic Tunnel. A second order effect, derived through the effect of Reynolds number on the sidewall boundary layer, is included. In addition, a comparison of how the drag-divergence condition is affected on going from one class of airfoil to another is presented. The drag-divergence condition is affected first order by Reynolds number for each of the six airfoils and of course all data are affected second order, since the presence of the boundary layer necessitates a sidewall correction

Notes:

Vendor supplied data

Publisher Number:

861767

Access Restriction:

Restricted for use by site license