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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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Approximate relative-total-pressure losses of an infinite cascade of supersonic blades with finite leading-edge thickness
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Wind-tunnel investigation of a number of total-pressure tubes at high angles of attack : subsonic speeds
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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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Total-pressure recovery characteristics of a model of the McDonnell XF3H-1 inlets and forebody in a free jet at a Mach number of 1.55
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Total-pressure Recovery of a Circular Underslung Inlet with Three Different Nose Shapes at a Mach Number of 1.42
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Total Pressure and Schlieren Studies of the Wakes of Various Canard Control Surfaces Mounted on a Missile Body at a Mach Number of 1.93
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Transonic Free-flight Investigation of the Total Drag and of the Component Drags (cowl Pressure, Additive, Base, Friction, and Internal) Encountered by a 16-inch-diameter Ram-jet Engine for Mach Numbers from 0.80 to 1.43
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Wind-tunnel investigation of a shielded total-pressure tube at transonic speeds
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Preliminary Investigation of the Total-pressure-recovery Characteristics of a Symmetric and Asymmetric Nose Inlet over a Wide Range of Angle of Attack at Supersonic Mach Numbers
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Wind-tunnel investigation of a shielded total-pressure tube at a Mach number of 1.61
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Effect of circumferential total-pressure gradients typical of single-inlet duct installations on performance of an axial-flow turbojet engine
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Experimental Investigation of Methods of Improving Diffuser-exit Total-pressure Profiles for Side-inlet Model at Mach Number 3.05
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A Free-flight Investigation of the Effects of a Sonic Jet on the Total-drag and Base-pressure Coefficients of a Boattail Body of Revolution from Mach Number 0.83 to 1.70
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Theoretical analysis of total-pressure loss and airflow distribution for tubular turbojet combustors with constant annulus and liner cross-sectional areas
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Investigation of the Effect of Velocity Diagram on Inlet Total-pressure Distortions Through Single-stage Subsonic Axial-flow Compressors
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Free-flight Skin-temperature and Surface-pressure Measurements on a Highly Polished Nose Having a 100 Degree Total-angle Cone and a 10 Degree Half-angle Conical Flare Section up to a Mach Number of 4.08
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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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