Mass flow requirements for LFC wing design

Srokowski, A. J.; Orszag, Steven A.

doi:10.2514/6.1977-1222

Cited by 79 publications

(13 citation statements)

References 4 publications

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“…The prediction of transition in three-dimensional boundary layers [1][2][3] is a aubject of both fundamental and practical importance in fluid mechanics. Practical interest in the subject w centers on the design of laminar flow control (LFC) wings that promise significant improvement in airplane fuel efficiency.…”

Section: Introductionmentioning

confidence: 99%

Instability and transition in rotating disk flow

Malik¹,

1981

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Section: Introductionmentioning

confidence: 99%

Instability and transition in rotating disk flow

Malik¹,

1981

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“…These crossflow vortices are very important and dominate disturbance growth in the leading-edge region (Srokowski and Orszag, 1977). On the other hand, the mid-chord region is dominated by the classical Tollmien-Schlichting instability (T-S waves).…”

Section: Motivationmentioning

confidence: 99%

“…For parallel, three-dimensional, incompressible stability calculations, a computer code SALLY has been developed by Srokowski and Orszag (1977) that uses the e n -method for correlating the transition location. They calculate the maximum temporal amplification rate for a given dimensional frequency at each boundary-layer station from the parallel, incompressible stability equations (the so-called envelope method).…”

Section: Review Of Stability Theorymentioning

confidence: 99%

An Analysis of Wave Interactions in Swept-Wing Flows

Reed

1985

Laminar-Turbulent Transition

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>Crossflow instabilities dominate disturbance growth in the leading-edge region of swept wings. It is well known that streamwise vortices in a boundary layer strongly influence the behavior of other disturbances. Amplification of crossflow vortices near the leading edge produces a residual spanwise nonuniformity in the mid-chord regions where Tollmien-Schlichting (T-S) waves are strongly amplified. Should the T-S wave undergo double-exponential growth because of this effect, the usual transition prediction. methods would fail.Thus it is important to study interactions of this sort and to develop more realistic criteria for transition prediction.We modeled analytically the crossflow/Tollmlen-Schlichting wave interaction as a secondary instability. The effects of compressibilty of the threedimensional flow over a swept wing will be considered in a future analysis.

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“…If , then is calculated and the target pressures in the three regions are modified. With (12) the new target pressures in the center and leading-edge regions are, respectively, (13) (14) where denotes the old target pressures, denotes the new target pressures, is a relaxation factor (typically 0.50) and…”

Section: The Pressures In the Recovery Regionmentioning

confidence: 99%

“…The NLF(1)-0414F was designed iteratively using the NYU code 11,12,13 to calculate the pressures of each intermediate airfoil and the SALLY code 14 to perform the stability analysis. Modifications were then made by hand to the airfoil geometry to give the airfoil the desired characteristics.…”

Section: Airfoil For a General Aviation Applicationmentioning

confidence: 99%

A method for the constrained design of natural laminar flow airfoils

Bradford¹,

John²,

Richard

et al. 1996

14th Applied Aerodynamics Conference

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A fully automated iterative design method has been developed by which an airfoil with a substantial amount of natural laminar flow can be designed, while maintaining other aerodynamic and geometric constraints. Drag reductions have been realized using the design method over a range of Mach numbers, Reynolds numbers and airfoil thicknesses. The thrusts of the method are its ability to calculate a target NFactor distribution that forces the flow to undergo transition at the desired location; the target-pressure-NFactor relationship that is used to reduce the N-Factors in order to prolong transition; and its ability to design airfoils to meet lift, pitching moment, thickness and leading-edge radius constraints while also being able to meet the natural laminar flow constraint. The method uses several existing CFD codes and can design a new airfoil in only a few days using a Silicon Graphics IRIS workstation.

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Mass flow requirements for LFC wing design

Cited by 79 publications

References 4 publications

Instability and transition in rotating disk flow

Instability and transition in rotating disk flow

An Analysis of Wave Interactions in Swept-Wing Flows

A method for the constrained design of natural laminar flow airfoils

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