A description of hypersonic laminar heat transfer at the stagnation point of a blunt body - case 110
Stagnation point convective heat transfer for blunt body moving at hypersonic speed
STAGNATION POINT↗
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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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One-dimensional approach to the maximum lift- to-drag ratio of a slender, flat-top, hypersonic wing
One-dimensional approach to maximum lift-drag ratio of slender, flat-top, affine wing at hypersonic speeds
FLAT SURFACE↗
Experimental performance of a conical pressure probe at Mach numbers of 3.0, 4.5, and 6.0
Wind tunnel investigation of performance of conical pressure probe at hypersonic speeds
PRESSURE PROBE↗
EQUATIONS FOR THE NEWTONIAN STATIC AND DYNAMIC AERODYNAMIC COEFFICIENTS FOR A BODY OF REVOLUTION WITH AN OFFSET CENTER-OFGRAVITY LOCATION
Equations for predicting aerodynamic stability of bodies of revolution with offset centers of gravity at supersonic and hypersonic speeds
AERODYNAMIC STABILITY↗
Aerodynamic force and moment characteristics of spheres and cones at mach 7.0 in methane-air combustion products
Aerodynamic force and moment characteristics of spheres and cones at hypersonic speeds in methane-air combustion products
HYPERSONIC SPEED↗
Effects of leading-edge bluntness on pressure and heat-transfer measurements over a flat plate at a mach number of 20
Effects of leading edge bluntness on pressure and heat transfer at hypersonic speed
HEAT TRANSFER↗
Effect of thickness and sweep angle on the longitudinal aerodynamic characteristics of slab delta planforms at a Mach number of 20
Effect of thickness and sweep angle on longitudinal aerodynamic characteristics of slab delta planforms at hypersonic speed
DELTA WING↗
Free-flight investigations of subliming ablators and transpiration cooling at hypersonic velocities
Free flight tests of subliming ablators and transpiration cooling as thermal protection at hypersonic speeds
EVAPORATION COOLING↗
Use of fusible temperature indicators for obtaining quantitative aerodynamic heat-transfer data
Fusible thin film coatings used in determining aerodynamic heat transfer coefficients at hypersonic speeds
THIN FILM↗
MEASUREMENTS OF THERMAL RADIATION OF AIR FROM THE STAGNATION REGION OF BLUNT BODIES TRAVELING AT VELOCITIES UP TO 31,000 FEET PER SECOND
Thermal radiation of air from stagnation region of blunt bodies at hypersonic speed
HYPERSONIC SPEED↗
STATIC LONGITUDINAL AERODYNAMIC CHARACTERISTICS OF SEVERAL WING AND BLUNT-BODY SHAPES APPLICABLE FOR USE AS REENTRY CONFIGURATIONS AT A MACH NUMBER OF 6.8 AND ANGLES OF ATTACK UP TO 90 DEG
Static longitudinal aerodynamics of wing and blunt body shapes for use as reentry configurations at hypersonic speed and angles of attack up to 90-deg
HYPERSONIC SPEED↗
70 Years of Aeropropulsion Research at NASA Glenn Research Center
This paper presents a brief overview of air-breathing propulsion research conducted at the NASA Glenn Research Center (GRC) over the past 70 years. It includes a historical perspective of the center and its various stages of propulsion research in response to the countrys different periods of crises and growth opportunities. GRCs research and technology development covered a broad spectrum, from a short-term focus on improving the energy efficiency of aircraft engines to advancing the frontier technologies of high-speed aviation in the supersonic and hypersonic speed regimes. This paper highlights major research programs, showing their impact on industry and aircraft propulsion, and briefly discusses current research programs and future aeropropulsion technology trends in related areas
turbojet↗
Experimental flow field and heat-transfer investigation of several tension shell configurations at a Mach number of 8
Flow field, pressure distributions, and heat transfer distribution of several tension shell configurations at hypersonic speeds
HEAT TRANSFER↗
Analysis of the project fire re-entry package flow field final technical report
Theoretical prediction of state of gas in flow field surrounding Apollo type vehicle in reentry at hypersonic speeds
GAS FLOW↗
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↗
Theoretical and experimental studies of equilibrium and nonequilibrium radiation to bodies entering postulated martian and venusian atmospheres at high speeds.
Spectral and total radiation studies of bodies traveling at hypersonic speed in simulated Martian and Venusian atmospheres
SHOCK HEATING↗
Heat-transfer and pressure distributions on a flat-face rounded-corner body of revolution with and without a flap at a Mach number of 8
Heat transfer and pressure distributions on flat face rounded-corner body of revolution with and without flap control at hypersonic speeds and angles of attack from 0 deg to 45 deg
FLAT SURFACE↗
Aerodynamic flight research using the Pegasus air-launched space booster
Completed and planned flight research using the Pegasus as a research vehicle and booster for other hypersonic research vehicles is reviewed. Highlights from flights 1 and 2 are discussed and compared with some analytical results. In particular, attention is given to total vehicle aerodynamics (performance and trim), local aerodynamics (pressure and heat flux distributions), and response of the thermal protection system. Future programs will include a metallic wing test section for laminar flow studies and the use of the Pegasus to boost a research vehicle to hypersonic speeds. The proposed concepts for a dedicated hypersonic research vehicle project are also discussed.
Meyer, Robert R., Jr.↗