Low-speed experimental investigation of a thin, faired, double-wedge airfoil section with nose and trailing-edge flaps
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AIRFOILS, WEDGE - DOUBLE - CHARACTERISTICS & MOMEN↗
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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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Low-speed Investigation of a Thin, Faired, Double-wedge Airfoil Section with Nose Flaps of Various Chords
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WING FLAPS↗
Low-speed Investigation of the Stalling of a Thin, Faired, Double-wedge Airfoil with Nose Flap
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AIRFOILS, WEDGE - DOUBLE - CHAR & MOMENTS↗
Experimental Study of an Angle-of-attack Vane Mounted Ahead of the Nose of an Airplane for Use as a Sensing Device for an Acceleration Alleviator
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LOADS, GUST - ALLEVIATION↗
On the attached curved shock in front of a sharp-nosed axially symmetrical body placed in a uniform stream
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Shen, S F↗
Prediction of losses induced by angle of attack in cascades of sharp-nosed blades for incompressible and subsonic compressible flow
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Kramer, James J↗
An Experimental Investigation at Low Speeds of the Effects of Lip Shape on the Drag and Pressure Recovery of a Nose Inlet in a Body of Revolution
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Blackaby, James R↗
Flight Determination of the Drag and Pressure Recovery of an NACA 1-40-250 Nose Inlet at Mach Numbers from 0.9 to 1.8
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Sears, R I↗
Low-speed Investigation of the Effects of Angle of Attack on the Pressure Recovery of a Circular Nose Inlet with Several Lip Shapes
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Blackaby, James R↗
Theoretical and Experimental Investigation of Aerodynamic-heating and Isothermal Heat-transfer Parameters on a Hemispherical Nose with Laminar Boundary Layer at Supersonic Mach Numbers
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Stine, Howard A↗
Flight Investigation at Mach Numbers from 0.8 to 1.5 to Determine the Effects of Nose Bluntness on the Total Drag of Two Fin-stabilized Bodies of Revolution
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Hart, Roger G↗
An Investigation of Several NACA 1-series Nose Inlets with and Without Protruding Central Bodies at High-subsonic Mach Numbers and at a Mach Number of 1.2
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Pendley, Robert E↗
Characteristics of Four Nose Inlets as Measured at Mach Numbers Between 1.4 and 2.0
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Brajnikoff, George B↗
Effects of vertical fins near the nose of the fuselage on the directional and damping-in-yaw stability derivatives of an airplane model under steady-state and oscillatory conditions
A wind-tunnel investigation has been made at low speed to determine the effects of vertical fins placed ahead of the vertical tail on the directional stability and damping-in-yaw characteristics of a swept-wing model under steady-state oscillatory conditions. Various sizes of fins were used above and below the fuselage center line. The vertical-tail size also was varied.
STABILITY, DIRECTIONAL - STATIC↗
Study of Pressure Distributions on Simple Sharp-nosed Models at Mach Numbers from 16 to 18 in Helium Flow
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Erickson, Wayne D↗
Boundary-layer Transition at Mach 3.12 as Affected by Cooling and Nose Blunting
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Diaconis, N S↗
The useful heat capacity of several materials for ballistic nose-cone construction
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Stalder, Jackson R↗
Wind-tunnel Investigation of Effects of Spoiler Location, Spoiler Size, and Fuselage Nose Shape on Directional Characteristics of a Model of a Tandem-rotor Helicopter Fuselage
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Williams, James L↗