Report discussing an investigation to determine the effects of aeroelasticity on the rolling effectiveness of a model of a McDonnell F3H-1 airplane wing. The plane was found to be subject to aeroelastic losses that varied with Mach number and altitude.

Report presenting an investigation of wings of aspect ratios of 4, 3, and 2 with a plan-form taper ratio of 0.5 and a thickness taper ratio of 0.33 to determine their transonic longitudinal characteristics and effects of tapering thickness ratio. Results regarding the combined effects of aspect ratio and thickness ratio and effects of tapered thickness ratio are provided.

Report presenting an investigation to determine the aerodynamic characteristics of a cruciform 70 degree delta-wing missile configuration with 70 degree delta canard control surfaces at M = 1.41 in the 4- by 4-foot supersonic pressure tunnel. Modifications to the configuration included variation of the body length and canard area and the substitution of a series of very small span wings for the cruciform delta wings and canard controls.

Report presenting an investigation to determine the effects of aeroelasticity on the rolling effectiveness of an 8.06-percent-scale model of the McDonnell F3H-1 airplane wing. The investigation used rocket-propelled models in free flight over a range of Mach numbers. The results indicate that the airplane is subject to aeroelastic losses varying from about 7 percent at Mach number 0.5 to 46 percent at Mach number 0.90 at sea level.

Report discussing details of curium's chemical properties, including gamma radiation, solubility, and absorption. A procedure for separating curium from americium and the preparation of terbium tetrafluoride, which lead to its discovery, is also included.

"An investigation at medium to high subsonic speeds has been conducted in the Langley low-turbulence pressure tunnel to determine the static stability and control characteristics and to measure the fin normal forces and moments for a model of a wingless fin-controlled missile. With the horizontal-fin deflection limited to a maximum of 6 degrees, longitudinally stable and trimmed flight could not be maintained beyond an angle of attack of 17 degrees for a Mach number of 0.88 and beyond 20 degrees for a Mach number of 0.50 for any center-of-gravity location without the use of some auxiliary stability or control device such as jet vanes" (p. 1).