SEARCH · Search NASA
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.
Quote a phrase for an exact phrase match. Source license links do not imply unrestricted reuse.
Space shuttle abort stage separation wind tunnel tests of orbiter and booster vehicles - orbiter proximity data, Mach number 3
Space shuttle abort stage separation wind tunnel tests of orbiter and booster vehicles - booster proximity data, Mach number 2
Space shuttle abort stage separation wind tunnel tests of orbiter and booster vehicles - orbiter proximity data, Mach number 2
Stored arc heated air true temperature, flight and altitude simulation facility in Mach number 8 to 10 region for air breathing propulsion research
Wind tunnel tests of a proposed HL-10 lifting body vehicle were conducted to determine the subsonic and transonic aerodynamic characteristics. The conditions under which the tests were conducted are described. The tests indicate that the configuration has slightly positive damping in pitch except at higher angles of attack at Mach numbers of 0.8, 0.9, and 1.0. At supersonic speeds, the configuration has positive damping in pitch for all test conditions. At subsonic and transonic speed, the configuration has positive damping and positive stability in yaw for all test conditions.
The subsonic aerodynamic characteristics of a series of irregular planform wings were studied in wind tunnel tests conducted at M = 0.3 over a range of Reynolds numbers from 1.6 million to 26 million/m. The five basic wing planforms varied from a trapezoidal to a delta shape. Leading edge extensions, added to the basic shape, varied in approximately 5 deg increments from the wing leading edge sweep-back angle to a maximum 80 deg. Most of the tests were conducted using an NACA 0008 airfoil section with grit boundary layer trips. Tests were also conducted using an NACA 0012 airfoil section and an 8% thick wedge. In addition, the effect of free transition (no grit) was investigated. A body was used on all models.
Performance of four 16-inch-diameter ram-jet units was determined at free-stream Mach numbers of 0.49 to 1.78 over range of gas total-temperature ratios of 1.0 to 6.1. Time histories of each flight and data on thrust, drag, diffuser efficiency, and combustion are presented. A maximum thrust coefficient of 0.88 and a maximum net acceleration of 5.13 g's were observed for the four units.
Heat-transfer data were evaluated from temperature time histories measured on a cooled cylindrical model with a cone-shaped nose and with turbulent flow at Mach numbers 3.00, 3.44, 4.08, 4.56, and 5.04. The experimental data were compared with calculated values using a modified Reynold's analogy between skin-friction and heat-transfer. Theoretical skin- friction coefficients were calculated using the method of Van Driest the method of Sommer and Short. The heat-transfer data obtained from the model were found to correlate when the 'T' method of Sommer and Short was used. The increase in turbulent heat-transfer rate with a reduction in wall to freestream temperature ratio was of the same order of magnitude as has been found for the turbulent skin-friction coefficient.
Explore the source record for details and available documents.
Explore the source record for details and available documents.
Explore the source record for details and available documents.
Off-design aerodynamic characteristics of swept arrow wings with twist and camber at supersonic velocities
Axisymmetric double cone compression inlet
Lifting surface for reentry vehicles - flutter of sails having delta wing planforms
Axisymmetric double cone external compression inlet in transonic range - drag components at detached shock conditions
Description of hemisphere cylinder models to measure heat flux in low density wind tunnels
Heat transfer measurements on blunt spherical segment nose and cylindrical body and flight test of rocket-propelled model
Explore the source record for details and available documents.