Icing tunnel tests of a glycol-exuding porous leading edge ice protection system on a general aviation airfoil

Kohlman, D. L.; Schweikhard, W. G.; Evanich, P.

doi:10.2514/6.1981-405

Cited by 3 publications

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“…A glycol-exuding porous leading-edge ice protection system has been experimentally investigated by the NASA Lewis Research Center and British aircraft industries. 6 This system can be operated in a deicing mode as well as an anti-icing mode. Another deicing system includes pneumatic deicers ("rubber shoes" that cover the leading edge and are periodically inflated and deflated).…”

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Modeling of surface blowing as an anti-icing technique for aircraft surfaces

Tabrizi

Keshock

1988

Journal of Aircraft

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An analysis of a proposed possible anti-icing technique applicable to aircraft surfaces has been studied and is described herein. Air injection at the leading edge of an ice-accreting surface is used to reduce and/or eliminate ice collection by preventing the supercooled water droplets in the atmosphere from impinging on the surface. In this envisioned technique, a discrete stream of fluid (air) is injected into the mainstream through slots located oh the cylinder surface. The modified flow around the surface produces modified droplet trajectories, deflecting the droplets away from the surface. Exact mathematical expressions for the velocities are obtained from potential flow theory. Droplet trajectories are obtained for a variety of surface blowing conditions. It was found that for a given cylinder diameter, freestream velocity, droplet size, and injection, there is an optimum slot location for which the injection has its maximum effect, i.e., minimum water collection and subsequent ice accretion. The effect of injection rate as well as the number of slots on the collection efficiency are also investigated.Re 0 r s* t u a ,u d Nomenclature = acceleration = droplet drag coefficient = cylinder diameter = droplet diameter = collection efficiency = force vector = drag force vector = gravity force vector = Froude number = gravitational constant and vector = inertia parameter = liquid water content = mass, = droplet mass = accreted ice mass = nondimensional slot (source) flow rate = slot flow rate or source/sink strength = cylinder radius = droplet relative Reynolds number, d(\U a~Ud \)/v = flow Reynolds number, dU^/v = flow Reynolds number, RU W /v -radial coordinate = droplet radius = droplet position vector = droplet position vector (nondimensional) = droplet acceleration vector (nondimensional) = time and duration of icing = local air and droplet velocity vector, respectively = freestream velocity = air and droplet velocity in the x direction, respectively = air and droplet velocity in the y direction, respectivelyPresented as Paper 87-0026 at

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confidence: 99%