From Summary: "The results of force tests made at low speed are presented to show the effect of longitudinal static stability produced by drooping the tip of a 63 degree sweptback wing. Five semispan wing models were tested: two incorporated curved drooped tips, two with abruptly drooped tips, and one without droop. The most favorable stability characteristics were measured for a model with an abruptly drooped tip, a fence, and a leading-edge flap; however, the use of these same auxiliary devices on the undrooped wing was nearly as effective."

Report presenting the results of flight tests conducted to determine the effect of number of fins on the drag of a pointed body moving at low supersonic velocities. The data indicated that the interference drag increased with increased number of ins up to a Mach number of 1.35, but above that value, the effect is reversed to the end of the test Mach number.

Report presenting a flight investigation to determine the comparative performance of AN-F-58 and AN-F-32 fuels in a 4000-pound-thrust turbojet engine. The fuels were equivalent over the range of conditions investigated. Results regarding corrected net thrust, corrected jet-fuel consumption, variation of corrected tail-pipe temperature, combustor blow-out speeds, and visual observations of the jet exhaust are provided.

Memorandum presenting testing of an experimental Custer Channel Wing airplane in the full-scale tunnel to investigate the lift characteristics of a channel-propeller combination and the flow phenomena in and about a channel wing.

Report presenting some equations that give the interference on the trailing-vortex system of a uniformly loaded finite-span wing in a circular tunnel containing partly open and partly closed walls, with special reference to symmetrical arrangements of the open and closed portions. Methods are given for extending the equations to include tunnel shapes other than circular.

From Summary: "An analytical method for calculating the aerodynamic loading on wing-tip-tank combinations in subsonic flow is developed by using a simple horseshoe vortex-image system for the case of the tank axis in the plane of the wing. An illustrative example is given in the appendix, in which wing and tip-tank loadings are calculated for three configurations. The calculated results are shown to be in good agreement with experimental data."

Report presenting a theoretical study of certain anomalies in the behavior of a ram-jet engine engine tip-mounted on a rotating helicopter blade that appears to be related to centrifugal effects distorting the fuel-spray pattern. Results regarding the cases calculated, results of the calculations, particle-path distortion, and limiting direction of particle paths are provided.

Report presenting an investigation of the effects of slot width, depth, shape, and spacing on the center-line pressure distribution in rectangular tunnels of constant cross section with several height-to-width ratios. Results are presented in the form of center-line static-pressure distributions and calculated static-pressure and angle-of-flow distributions along the slotted boundary.

Report presenting measurements of the damping in roll of cruciform triangular wings of aspect ratios 0.64, 1.28, and 2.31 at supersonic Mach numbers from 1.5 to 6.0. The models were launched from rifled guns and the time history of the model roll position in free flight was explored. Results regarding the comparison with theory, transonic effects, and comparison with results at other facilities are provided.

Memorandum presenting an experimental investigation to determine the flutter characteristics of several rectangular wings of variable aspect ratio at a range of Mach numbers. The wings were solid aluminum or steel and were 2, 4, and 6 percent thick. Results regarding the flutter at low and high angles of attack are provided.

Report presenting preliminary flight-measured chordwise pressure distributions, which have been obtained at a wing midsemispan station of the Douglas X-3 research airplane through a range of angles of attack and Mach numbers. An exploration of the section aerodynamic characteristics is also provided.

Memorandum presenting a force-test investigation to determine whether the static stability characteristics of a twisted and cambered 68.7 degree delta wing could be approximated by a plane wing of similar plan form with dihedral. Results regarding longitudinal characteristics and lateral characteristics are provided.