dc.contributor.author |
P. B. Earnshaw |
en_US |
dc.contributor.author |
J. A. Lawford |
en_US |
dc.date.accessioned |
2014-10-21T15:56:25Z |
|
dc.date.available |
2014-10-21T15:56:25Z |
|
dc.date.issued |
1964 |
en_US |
dc.identifier.other |
ARC/R&M-3424 |
en_US |
dc.identifier.uri |
https://reports.aerade.cranfield.ac.uk/handle/1826.2/4008 |
|
dc.description.abstract |
A series of six delta wings of varying angles of sweepback has been tested. A three-component strain-gauge balance was used to investigate the forces and moments, and normal-force fluctuations for incidences between ± 60°. Positions of vortex breakdown on these wings were noted. Surface flow pattern and boundary-layer transition observations were made. The three most highly swept wings (i.e. having sweepback angles of 65°, 70° and 76°) appeared to have the most favourable characteristics of growth of normal-force fluctuations and had a smooth variation of forces and moments throughout the incidence range between positive and negative stalls. The change from a vortex type of flow to one with complete flow reversal on the upper surface occurred at increased incidence with increase of sweepback angle. At moderate incidence α the main features of the flow pattern correspond to conical flow development, and correlate well with the single parameter α/cot φ, where φ is the sweepback angle of the leading edge. |
en_US |
dc.relation.ispartofseries |
Aeronautical Research Council Reports & Memoranda |
en_US |
dc.title |
Low-speed wind-tunnel experiments on a series of sharp-edged delta wings |
en_US |