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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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Supersonic free-flight test of delta boost-glide figure with analog study of coupled motions
First glide flight of heavy lifting body launched from aircraft wing
Dynamic longitudinal stability of aircraft in constant glide path angle
Wind tunnel tests of recovery parachutes designed for controllable gliding flight
The promise of the grid is that it will enable public access and sharing of immense amounts of computational and data resources among dynamic coalitions of individuals and institutions. However, the current grid solutions make several limiting assumptions that curtail their widespread adoption. To address these limitations, we present GLIDE, a prototype light-weight, data-intensive middleware infrastructure that enables access to the robust data and computational power of the grid on DREAM platforms.
Heat-transfer measurements were made on a simulated glide-rocket shape in free flight at Mach numbers up to 10 and free-stream Reynolds numbers of 2 x 10 based on distance along surface from apex and 3 x 10 based on nominal leading-edge diameter. The model simulated the bottom of a 75 deg delta wing at 8O deg angle of attack. The data indicated that for the test conditions a modified three-dimensional stagnation-point theory will predict to reasonable engineering accuracy the heating on a highly swept wing leading edge, the heating being reduced by sweep by the 3/2 power of the cosine of the sweep angle. The data also indicate that laminar heating rates over the windward surface of a highly swept flat glider wing at moderate angles of attack can be predicted with reasonable engineering accuracy by flat-plate theory using wedge local flow conditions and basing Reynolds numbers on lengths from the wing leading edge parallel to the surface center line.
Thermal sensors for measuring surface temperature and heat flux on glide reentry vehicles
Results of tests at Mach numbers of 3.0 and 7.3 for possible wing flutter of a series of models of a boost-glide-vehicle wing are presented herein. All of the models were tested at conditions which exceeded the proposed nominal design requirements for the full-scale vehicle; namely, dynamic pressure of 1,000 pounds per square foot at the test Mach numbers. None of the models experienced flutter; therefore, large margins of safety from wing flutter are indicated. However, the effects of body freedoms on the flutter characteristics and local types of flutter were not investigated.
Easy glide in electron-beam, zone-refined molybdenum crystals observed by use of direct shear
Pressure distribution on hypersonic glide configuration having 79.5 deg sweepback and 45 deg dihedral at Mach number of 4.95
Reentry control requirements during terminal glide, approach, and landing
Wind tunnel studies of static aerodynamic characteristics of multilobe gliding parachute
Glide slope angle increase effects on pilots manual control accuracy of instrument approaches investigated with simulation equipment, discussing noise reduction
Influence of angle of glide slope on accuracy of performing instrument approaches in simulator tests
Test program for determining visual reference requirements for pilot control of gliding parachutes used in landing spacecraft on land
Hi-glide personnel canopy /Para-Foil, Parawing, Sailwing, Volplane/ technology capability requirements identification from performance parameters tradeoffs
Glide and landing performance of twin-keel parawings, discussing wind tunnel, radio flight and simulator tests
Lift and drag characteristics of HL-10 lifting body during subsonic gliding flight