The Use of Area Suction for the Purpose of Delaying Separation of Air Flow at the Leading Edge of a 63 Degree Swept-back Wing
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Cook, Woodrow L↗
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Search indexed NASA NTRS and DOE OSTI research on propulsion, heat transfer, battery materials and energy systems. Follow report and document links to the original sources.
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Experimental investigation of air-flow uniformity and pressure level on wire cloth for transpiration-cooling applications
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Donoughe, Patrick L↗
Effect of Liner Air-entry Holes, Fuel State, and Combustor Size on Performance of an Annular Turbojet Combustor at Low Pressures and High Air-flow Rates
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Norgren, Carl T↗
Measurements of heat-transfer and friction coefficients for air flowing in a tube of length-diameter ratio of 15 at high surface temperatures
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Weiland, Walter F↗
Air-flow Characteristics of Brazed and Rolled Wire Filter Cloth for Transpiration-cooled Afterburners
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Koffel, William K↗
Effect of Unequal Air-flow Distribution from Twin Inlet Ducts on Performance of an Axial-flow Turbojet Engine
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Walker, Curtis, L↗
A wind-tunnel investigation of the first-order vibratory stresses on a full-scale supersonic-type propeller operating in an asymmetric air flow
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O'NEAL ROBERT L↗
Experimental Heat-transfer and Friction Coefficients for Air Flowing Through Stacks of Parallel Flat Plates
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Sams, Eldon W↗
The Use of a Leading-edge Area-suction Flap to Delay Separation of Air Flow from the Leading Edge of a 35 Degree Sweptback Wing
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Holzhauser, Curt A↗
Effects of Secondary-air Flow on Annular Base Force of a Supersonic Airplane
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Vargo, Donald J↗
Effects of Inlet-air-flow Distortion on Steady-state Altitude Performance of an Axial-flow Turbojet Engine
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Conrad, E William↗
An Experimental Investigation of the Air-flow Stability of a Scoop-type Normal-shock Inlet
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Mossman, Emmet A↗
Investigation at supersonic and subsonic Mach numbers of auxiliary inlets supplying secondary air flow to ejector exhaust nozzles
The results indicated increases in auxiliary-inlet pressure recovery with increases in scoop height relative to the boundary-layer thickness. The pressure recovery increased at about the same rate as theoretically predicted for an inlet in a boundary layer having a one-seventh power profile, but was only about 0.68 to 0.75 of the theoretically obtainable values. Under some operating conditions, flow from the primary jet was exhausted through the auxiliary inlet. This phenomenon could be predicted from the ejector pumping characteristics.
Hearth, Donald P↗
Investigation of the air-flow regulation characteristics of a translating-spike inlet with two oblique shocks from Mach 1.6 to 2.0
The pressure recovery of an axially symmetric translating-spike inlet was essentially the same as for a single cone with the same total angle. In order to match a turbojet engine over the Mach range of 1.6 to 2.0, the spike translation must be larger than it is for a single cone.
Nettles, J C↗
Low-speed Measurement of Tail Contribution to Rolling Stability Derivatives and Air-flow Angularity at the Tail for an X-tail Model in Steady Roll Including Some Effects of Wing-tip Stores
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Riley, Donald R↗
Investigation of fixed-geometry supersonic inlets with bypass ducts for matching turbojet-engine air-flow requirements over a range of transonic and supersonic speeds
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Leiss, Abraham↗
Effect of uneven air-flow distribution to the twin inlets of an axial-flow turbojet engine
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Wallner, Lewis E↗
Air-flow surveys in the vicinity of representative NACA 1-series cowlings
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Boswinkle, Robert W , Jr↗