In-flight flow visualization of F-106B leading-edge vortex using thevapor-screen technique

Lamar, John E.; Bruce, Robert A.; Pride, J. D.; Smith, R. H.; Brown, P. W.

doi:10.2514/6.1986-9785

Cited by 1 publication

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“…The first of the two programs was to examine the flow field above the wing to look for evidence of vortical flows in a range of test conditions, including variations in Reynolds numbers (44,45) . The vapour-screen technique was wind-tunnel proven and chosen to be the best method of obtaining the needed data, but there were many unanswered questions regarding whether it could be used in flight, as this was a first for NASA -later, I learned of a prior Soviet effort (46) .…”

Section: Flight Vortex-flow Analysismentioning

confidence: 99%

A career in vortices and edge forces

Lamar¹

2012

Aeronaut. j. (1968)

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This lecture recognises the background and distinguished work of Frederick William Lanchester, and notes that my background has a few similarities with his. These include a shared interest in wings, lift and vortices. My career at the NASA Langley Research Center spans the time-frame from America's Super Sonic Transport through 2009. An early emphasis involved wind-tunnel testing of research aircraft models and the development of computer codes for subsonic aerodynamics of wing planforms. These attached-flow codes were applied to various configurations, including those with variable-sweep, dihedral, and more than one planform in both the analysisand design-modes. These codes were used to provide a connection between leading-edge-forces and the associated additional lift on delta-wings with shed-vortex systems through the leadingedge suction analogy of Edward C. Polhamus. Subsequently, I extended the suction analogy to configurations with side-edges to predict the vortical-flow aerodynamics on complex configurations, including wing-strake combinations. These analysis codes could also be used in a design-by-analysis mode for configurations with leading-edge shed vortices. Later, I was involved in vortical-flow flight research with the F-106B and the F-16XL aircraft at cruise and maneuver conditions. Associated CFD predictions, generated by me and other members of the RTO/AVT-113 task group, have increased our understanding of the flight flow-physics measured on the F-16XL aircraft. (a) Planview drawing (b) Front view drawing with wings at Λ = 16°( c) Model with wings at Λ = 16°(d) Model with wings at Λ = 76°N ASA Langley 7 ft by 10 ft HST Figure 2. SCAT 16 drawings and photographs from Ref. 5; model has a fuselage length of 91 inches (231·14cm) and a wing-span of 84·85 inches (215·52cm) at Λ = 16°.

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Section: Flight Vortex-flow Analysismentioning

confidence: 99%