Reductions in temperature-recovery factor associated with pulsating flows generated by spike-nosed cylinders at a Mach number of 3.50
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Hermach, C A↗
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Results for “NOSE”
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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Free-flight Aerodynamic-heating Data to a Mach Number of 15.5 on a Blunted Conical Nose with a Total Angle of 29 Degrees
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Bland, William M , Jr↗
Free-flight Pressure Measurements over a Flare-stabilized Rocket Model with a Modified Von Karman Nose for Mach Numbers up to 4.3
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Bland, William M , Jr↗
Feasibility of Nose-cone Cooling by the Upstream Ejection of Solid Coolants at the Stagnation Point
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Kinard, William H↗
Theoretical analysis of the interference effects of several supersonic-tunnel walls capable of absorbing the shock caused by the nose of a model
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Matthews, Clarence W↗
Heat transfer and pressure measurement on a 5-inch hemispherical concave nose at a Mach number of 2.0
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Markley, J Thomas↗
A Flight-test Study of Total-pressure Distortion in a Thick-lipped Nose Inlet
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Wingrove, Rodney C↗
Heat-transfer measurements on a concave hemispherical nose shape with unsteady-flow effects at Mach numbers of 1.98 and 4.95
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Cooper, Morton↗
Investigation of shock-boundary-layer interaction on the spike of a conical-spike nose inlet
Measurements were made of the height of the shock-induced boundary-layer thickening and separation over a Mach number range of 1.6 to 2.0. The behavior of the interaction depended on longitudinal spike position as well as on cone surface Mach number. The cone position affected the interaction by changing the rate of subsonic diffusion and thereby changing the pressure aft of the terminal shock. When the pressure rise due to the interaction exceeded about 1.9, the boundary layer was separated.
Wise, George A↗
Wind-tunnel Investigation of the Effects of Lip Geometry on Drag and Pressure Recovery of a Normal-shock Nose Inlet on a Body of Revolution at Mach Numbers of 1.41 and 1.81
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Robins, A Warner↗
Performance of Separation Nose Inlets at Mach Number 5.5
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Haefeli, Rudolph C↗
The effect of nose radius and shape on the aerodynamic characteristics of a fuselage and a wing-fuselage combination at angles of attack
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Gapcynski, John P↗
Pressure Recovery and Mass-flow Performance of Four Annular Nose Inlets Operating in Mach Number Region of 3.1 and Reynolds Number Range of Approximately 0.45 x 10(exp 6) to 2.20 x 10(exp 6)
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Hunczak, Henry R↗
The development of satisfactory flying qualities on the Douglas dive bomber, model SBD-1 through flight testing successive modifications in control-surface area, hinge-line location, and aerodynamic-balance nose shape
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STALLING - DOUGLAS SBD-1↗
Flight Investigation of the Performance and Cooling Characteristics of a Long-Nose High-Inlet-Velocity Cowling on the XP-42 Airplane
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INSTRUMENTS- GALVANOMETERS↗
Wind-tunnel investigation of control-surface characteristics VII : a medium aerodynamic balance of two nose shapes used with a 30-percent-chord flap on an NACA 0015 airfoil
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CONTROL SURFACES - CHARACTERISTICS↗
Wind Tunnel Tests of Ailerons at Various Speeds IV : Ailerons of 0.20 Airfoil Chord and True Contour with 0.35 Aileron-chord Extreme Blunt-nose Balance on the NACA 23012 Airfoil
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AILERONS - WIND TUNNEL TESTS↗
Effect of leakage past aileron nose on aerodynamic characteristics of plain and internally balanced ailerons on NACA 66(215)-216, a = 1.0 airfoil
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PRESSURE DISTRIBUTION - AILERONS↗