Memorandum presenting flight tests conducted with a director-type radar fire-control system, with scope presentation of the steering information, to determine the effects of attack-display smoothing on the pilot's tracking and steering effectiveness in tail-chase and lead-collision beam attacks. Results regarding tail-chase attacks and lead-collision beam attacks are provided.

The trajectories of droplets in the air flowing past an NACA 651-212 airfoil at an angle of attack of 40 were determined. The collection efficiency, the area of droplet impingement, and the rate of droplet impingement were calculated from the trajectories and are presented herein.

"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 80 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" (p. 1).

Report presenting an investigation to determine the performance characteristics of a side inlet with boundary-layer control operating in the presence of laminar and turbulent initial boundary layers at a free-stream Mach number of 2.93. Results regarding mass-flow and total-pressure referencing, visual-flow observations, inlet performance, and boundary-layer-scoop performance are provided.

From Introduction: "Previous investigations of a number of internal configurations in the same afterburner shell are reported in reference 1 and 2. In the investigation reported herein, the performance and operational characteristics of three afterburner internal configurations were evaluated."

Report presenting a determination of the characteristics of a particular vane configuration in the jet of a 6.25-inch Deacon solid-fuel rocket motor from static testing. The vanes were oscillated during the test to provide comprehensive data over a range of deflection angles. The effects of the rocket jet on two vane materials, the aerodynamic characteristics of the vanes, and the influence of jet vanes on rocket-motor performance were determined.

Report presenting an investigation to determine the effects of partial-span single slotted and double slotted flaps at various deflections on the longitudinal aerodynamic characteristics of a sweptback-wing-fuselage combination. Results regarding the lift characteristics, pitching-moment characteristics, drag characteristics, and effect of flap-bracket alignment are provided.

Memorandum presenting an investigation in the 300 mph 7- by 10-foot tunnel to determine the lateral control characteristics of a deflector and slot arrangement in conjunction with a flap-type spoiler aileron. The wing had a sweepback of 45 degrees at the quarter-chord line, an aspect ratio of 4, a taper ratio of 0.6, and an NACA 65A006 airfoil section parallel to the free air stream.

Report presenting the effects of sweepback on the occurrence and principal characteristics of single-degree-of-freedom aileron flutter for a wing-aileron combination. Testing occurred over a range of Mach and Reynolds number and angles of attack. Results regarding the measurements of aileron motion, effect of sweep, variation of lift coefficient, and use of shadowgraph technique for visualizing flow are provided.

Report presenting free-flight testing of conical-shock nose inlet models with cowls of fineness ratio 3 with five different profiles. Three of the profiles were mostly conic with different lip shapes, one was parabolic, and one was NACA 1-series. Results regarding the basic data, effect of cone position, comparison of profile shapes, and effect of mass-flow ratio are provided.

Report discussing an investigation to determine the stability and control characteristics of a supersonic aircraft configuration with a 40 degree sweptback wing and equipped with spoiler lateral control devices at Mach number 1.61. The effects of various types of spoilers, spoiler span, spoiler projection, and chordwise location were investigated, as well as the hinge-moment characteristics of the plain spoiler.

Memorandum presenting an investigation conducted in the full-scale tunnel to determine the aerodynamic and structural deflection characteristics of the Goodyear Inflatoplane over a range of test velocities from minimum stall speed up to speeds giving load factors for wing buckling. The airplane was developed as a potential way to rescue downed pilots in enemy territory. An exploration of the stability, stalling characteristics, buckling, and chosen configuration is provided.

"The results are presented of an experimental investigation conducted to determine the static longitudinal and lateral-direction aerodynamic characteristics of basic and modified versions of a conventional upward ejected pilot-seat combination, a sled-type upward ejected pilot-seat combination, and a downward ejected pilot-seat combination" (p. 1). The drag coefficient, lift coefficient, rolling-moment coefficient, pitching-moment coefficient, yawing-moment coefficient, and side-force coefficient are provided.

Report presenting an investigation of a canard-type configuration designed for supersonic cruise flight in the Unitary Plan wind tunnel. Tests were conducted over a range of angles of attack and angles of sideslip. Results regarding the effect of forebody configuration, effects of Reynolds number and transition, effect of canard and elevon deflection, and effect of vertical surfaces are provided.