Drag coefficients of microscopic spheres in free-molecule flow
Drag coefficients of microscopic spheres in free molecule flow
FREE FLOW↗
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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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Flight evaluation of splitter-plate effectiveness in reducing base drag at Mach numbers from 0.65 to 0.90
Flight test evaluation of splitter plate in base drag reduction at subsonic speeds
SUBSONIC SPEED↗
Hypersonic viscous drag on cones in rarefied flow
Hypersonic viscous drag on cones in rarefied flow
FLOW MEASUREMENT↗
Injection of a drag-reducing fluid into turbulent pipe flow of a Newtonian fluid
Injection of drag reducing fluid into turbulent pipe flow of Newtonian fluid
NEWTONIAN FLUID↗
Hypersonic aerodynamic characteristics of minimum-wave-drag bodies having variations in cross-sectional shape
Hypersonic aerodynamic performance of minimum wave drag bodies having various cross sections
LIFTING BODY↗
Aerodynamic investigation of some high-drag entry shapes at Mach 15.4
Effects of body shape, nose radius, and shoulder shape of reentry body on aerodynamic drag
DRAG COEFFICIENT↗
Investigation of drag and heat transfer during air motion in divergent and convergent nozzles
Experimental investigation of drag and heat transfer of turbulent airflow in divergent and convergent nozzles
TURBULENT AIR CURRENT↗
Experimentally determined local flow properties and drag coefficients for a family of blunt bodies at Mach numbers from 2.49 to 4.63
Experimentally determined local flow properties and drag coefficients for family of blunt bodies at Mach numbers from 2.49 to 4.63
DRAG COEFFICIENT↗
Bodies of maximum lift-to-drag ratio in hypersonic flow.
Optimum shaped-bodies of maximum lift-to-drag ratio in hypersonic flow for modified Newtonian pressure distribution and constant skin friction
HYPERSONIC FLOW↗
Alfven waves and induction drag on long cylindrical satellites.
Induction drag of long cylindrical satellites and Alfven waves emitted from them, determining potential and current distribution and effect on energy loss
CURRENT DISTRIBUTION↗
Two-dimensional, hypersonic wings of maximum lift-to-drag ratio.
Slender two-dimensional wing lift-drag ratio at hypersonic speed maximized, assuming modified pressure coefficient
PRESSURE COEFFICIENT↗
Three-dimensional, hypersonic wings of maximum lift-to-drag ratio.
Three-dimensional slender wings of maximum lift/ drag ratio in hypersonic flow studied by variational calculus under several lift and volume conditions
THREE-DIMENSIONAL FLOW↗
Fluid drag on a sphere rolling in a tube.
Incompressible fluid drag force on sphere rolling at constant speed in closed-end tube
CIRCULAR TUBE↗
Maximum lift-to-drag ratio of a slender, flat-top, hypersonic body.
Lift-drag ratio attainable by slender flat-top body at supersonic speeds, considering Newtonian pressure distribution and constant skin friction
NEWTONIAN FLUID↗
Ion drag and current partitioning at the cathode of a plasma accelerator.
Tangential drag measurements at electrodes of arc in plasma accelerator, ion current partitioning at cathode and electrode damage
PLASMA ACCELERATOR↗
Drag measurements of cones in the rarefied flow regime.
Drag measurements of cones in rarefied flow regime extended to higher and lower cone semivertex angles
CONE↗
Distribution of wave drag and lift in the vicinity of wing tips at supersonic speeds
The point-source-distribution method of calculating the aerodynamic coefficients of thin wings at supersonic speeds was extended to include the effect of the region between the wing boundary and the foremost Mach wave from the wing leading edge. The effect of this region on the surface velocity potential has been determined by an equivalent function, which is evaluated over a portion of the wing surface. In this manner, the effect of angles of attack and yaw as well as the asymmetry of top and bottom wing surfaces may be calculated. As examples of the method, the pressure distribution on a thin plate wing of rectangular plan form as well as the lift and the drag coefficients as a function of Mach number, angle of attack, and aspect ratio are calculated. The equations for the surface velocity potential of several other plan forms are also included. (author)
AIRFOILS, FLAT-PLATE↗
Flight Investigation of Boundary-layer and Profile-drag Characteristics of Smooth Wing Sections of a P-47D Airplane
In Mach range of 0.25 - 0.69, boundary-layer measurements were made on upper wing surface at 25% semi-span, pressure-distribution measurements made on upper surface at 63% semi-span, and wake surveys made at 63% semi-span. The minimum profile-drag coefficient of 0.0062 was indicated for smooth section at 63% semi-span. Critical mach number was exceeded by 0.04, but no compressibility shocks appeared. In slipstream, boundary layer transition occurred as far back as 20% chord on upper surface at low lift coefficients.
PRESSURE DISTRIBUTION - WINGS - REPUBLIC P-47D↗