Report presenting an investigation to obtain the effects of a 20-percent-semispan all-movable wing-tip control on the longitudinal stability characteristics of a twisted and cambered 60 degree sweptback-wing-indented-body configuration. Testing occurred over a range of angles of attack and Mach numbers. Results regarding the effects on drag coefficient and lift-drag ratio are also provided.

Report presenting zero-lift experimental flutter data in a range of Mach numbers on a 1.5-percent-thick, untapered, unswept, solid steel wing with hexagonal airfoil sections and wing length-to-chord ratios of 1.61 and 1.73. The wing was tested as a cantilever with and without a half-body-of-revolution fuselage. Results regarding the calculated flutter speeds and frequencies, effect of fuselage, variation of wing flutter characteristics with Mach number, results of analytic solutions, and variation of wing flutter characteristics with mass ratio are provided.

Report presenting flutter data over a range of Mach numbers in free-flight testing of several wing-body combinations as part of a general zero-lift drag investigation. The wings all had the same streamwise airfoil sections and the plan-form variations consisted of delta wings, diamond wings, and an arrow wing. Time histories of model speed, Mach number, and air density are provided for each model as well as flutter frequency, amplitude, and reduced-frequency parameter plotted as functions of model speed.

From summary: "This report was prepared for the Advisory Committee on Reactor Safeguards for their review and consideration of the potential hazards concerning the Battelle Memorial Institute Research Reactor."

We have produced and chemically identified for the first time a few atoms of the element with atomic number 101. Very intense helium ion bombardments of tiny targets of 99{sup 253} have produced a few spontaneously fissionable atoms which elute in the eka-thulium position on a cation resin column.

Various figures depicting views and components of a device for coating the "Model 100" 8-faced metallic rotating mirror with an equal amount of material on each mirror face.

Report presenting an investigation to determine the effects of taper ratio and body indentation on the aerodynamic loading characteristics of a 45 degree sweptback wing in the presence of a body in the transonic pressure tunnel for a range of Mach numbers and angles of attack. Results regarding the effect of wing-body-juncture seals, general effects of the variables, effect of taper ratio, effects of body indentation, and comparisons with other data are provided.

Report presenting a flight investigation over a range of altitudes and lift to determine the wing loads of the Bell X-5 research airplane at a sweep angle of 58.7 degrees at subsonic and transonic Mach numbers. Testing indicated that wing loads exhibit nonlinear trends over the angle-of-attack range from zero to maximum wing lift.