Aerospace & Aviation

Nmr study of indene using proton-proton decoupling technique

Convective and radiant heat transfer for flow of a transparent gas in a tube with a gray wall

The optimum-thrust equations for both variable and constant thrust are presented. These thrust programs are used to generate rendezvous trajectories from the Earth to Mars for various flight times and launch dates during the years 1968-71. The manner in which the propulsion requirements vary with flight time and launch date are considered, and a comparison of vehicle performance using the variable- and constant-thrust programs is presented. The optimization of the pro- pulsion system parameters is discussed, and the existence of optimum launch dates is interpreted in terms of certain transversality conditions derivable from the calculus of variations. A brief comparison of the advanced propulsion vehicle and the ballistic vehicle propulsion requirements is made for Earth-Mars rendezvous trajectories. An appendix considering the analytical basis for this work is included.

Effects of temperature & illuminance on chlorella growth uncoupled from cell division

Notch rupture sensitivity

Electrostatic & electromagnetic drag forces on a spherical satellite

Longitudinal stability and control of a tilt-wing vtol aircraft model with rigid and flapping propeller blades

Adhesion between atomically clean metallic surfaces

Crosslinked & non-crosslinked diisocyanate-linked elastomers containing substituted urea groups

Quarterly Status Report: June 15, 1961 - September 15, 1961

Ionization phenomena in hypersonic wind tunnels

Comparison of theory and observation of the echo I satellite

Exploratory study of potassium and sodium superoxide for oxygen control in manned spacecraft

Producing improved bearing components by elimination or control of fiber orientation including magnetic analysis

Subjective noisiness of aircraft sounds