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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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Axisymmetric external compression double cone inlet - mach 3 to 0.8 - pressure recovery, mass flow ratio, cowl pressure and additive drag
Axisymmetric double cone external compression inlet in transonic range - drag components at detached shock conditions
Calculated radio attenuation due to plasma sheath on hypersonic blunt-nosed cone
Measurement of aerodynamic heating on sharp cones entering earth atmosphere
Exploratory tests were made to determine the reduction of heat transfer resulting from ejection of gases at the stagnation point on a hemisphere-cone at a nominal Mach number of about 9 and at stagnation enthalpies up to 1600 BTU per pound. Helium, nitrogen, and argon gases were used as coolants. The ratio of mass flow of coolant to the mass flow of air swept out by the model projected area was less than 0.20 in all cases. The experimental heat-transfer data were normalized by the calculated stagnation-point values based on test conditions in the tunnel and are presented as a function of the surface distance from the stagnation point. The variation of shock standoff distances with mass flow and volumetric flow of the gaseous ejectants is presented along with photographs of the luminous flow field of the model during tests.
Laminar convective heat transfer and boundary layer equations for cones at escape velocity
Integral relations method applied to supersonic nonequilibrium flow past wedges and cones
Close-tolerance elliptical cones are fabricated by cutting-tool guide assembly used with conventional tracer cartridge on turret lathe accurately produced in two machine operations.
Wind tunnel pressure measurements in flow field behind simple cone-cylinder body of rotation at Mach number 2.30 and 4.65
Pressure measurement at instrument rack of sounding rocket payload after nose cone ejection
Pressure distribution and flow fields of blunted cones at hypersonic Mach numbers
Asymptotic acceptance cone variation of cosmic ray neutron monitors in geomagnetic field distorted by solar wind, noting particle trajectories
Radiative decay effect on shock layer radiation toward circular cones under finite angle of attack
Small perturbation technique solves the problem of an oscillating cone in supersonic flow. The logic of the program is straightforward, as reflected in the actual instructions for solving the problem.
Longitudinal aerodynamic characteristics of blunted cone reentry vehicle configurations at high Mach numbers, including Reynolds number effect
Design, fabrication, test, and field handling of S-band Cassegrain monopulse cone assembly for DSIF 30-foot diameter antenna
Charts of additive drag coefficient and mass flow ratio for inlets utilizing right circular cones at zero angle of attack
Effect of body nose blunting, control planform area, and leading edge bluntness on aerodynamic control of semivertex cone at hypersonic speed