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.

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.

"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).

"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.

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.

Report presenting an investigation to determine the effect of a distributed granular-type roughness on boundary-layer transition at several temperatures. The roughness was not found to introduce any disturbances of significant magnitude to influence transition. Surface cooling did not increase the value of the critical roughness Reynolds number for a distributed granular-type roughness either.

Memorandum presenting experimental force and moment characteristics, including lift-drag ratios, which have been measured and briefly studied for two families of wing-body combinations. One family consisted of essentially arrow wings with half conical bodies. The other consisted of a fineness-ratio-12 body of revolution alone and with flat-plate triangular wings of aspect ratios ranging from 0.375 to 1.8.

Memorandum presenting an investigation in the 4- by 4-foot supersonic pressure tunnel at Mach number 2.01 to determine the longitudinal and lateral stability and control characteristics of a 60 degree delta-wing airplane configuration equipped with a trapezoidal canard control and with wing trailing-edge flap controls. The investigation included studies of the flap control with and without canard surface and studies of the canard control alone and with the flap control.

Report discussing heat data obtained on concave and convex hemispherical nose shapes and hemispherical depressions on a blunted 30-degree nose cone at a variety of Mach numbers. Both hot-jet tests and flight tests were carried out.

"An investigation of the aerodynamic characteristics of several hypersonic missile configurations with various canard controls for an angle-of-attack range from 0 deg to about 28 deg at sideslip angles of about 0 deg and 4 deg at a Mach number of 2.01 has been made in the Langley 4- by 4-foot supersonic pressure tunnel. The configurations tested were a body alone which had a ratio of length to diameter of 10, the body with a 10 deg flare, the body with cruciform fins of 5 deg or 15 deg apex angle, and a flare-stabilized rocket model with a modified Von Karman nose" (p. 1). Various canard surfaces for pitch control only were tested on the body with the 10 deg flare and on the body with both sets of fins. The results indicated that the addition of a flared afterbody or cruciform fins produced configurations which were longitudinally and directionally stable. The body with 5 deg fins should be capable of producing higher normal accelerations than the flared body. A l l of the canard surfaces were effective longitudinal controls which produced net positive increments of normal force and pitching moments which progressively decreased with increasing angle of attack.

Memorandum presenting a comparison of the performance of two aerodynamically similar single-stage rotors of different chord length. Results regarding short-chord-rotor performance, long-chord-rotor performance, comparison of overall performance, blade-element performance, rotating stall, and separation-parameter analysis are provided.

Report presenting a study to determine the relative importance of the factors that place an inherent limitation on the minimum obtainable miss distance for a beam-rider navigation system operating in the presence of glint noise and target evasive maneuver. The factors considered include missile natural frequencies and damping ratios, missile steady-state acceleration capabilities, target evasive maneuver characteristics, and angular scintillation noise characteristics.

Report presenting a study of the performance of a modified compressor over a range of weight flows at a constant Reynolds number. The chords of the first two stages of the eight-stage axial-flow compressor had two transonic inlet stages doubled. Results regarding the long-chord-compressor performance and a comparison of long-chord and medium-chord compressors are provided.

Report presenting an investigation of the static stability and control characteristics of a canard airplane configuration without analysis for a range of Mach numbers from 0.70 to 2.22. This configuration consisted of a triangular wing and triangular canard, a low aspect ratio vertical tail, and a modified Sears-Haack body. Data are presented for various combinations of the body, canard, wing, and vertical tail at severla angles of sideslip, angles of attack, and canard deflection angles.

Report presenting an investigation conducted in the 9- by 9-inch Mach number 4 blowdown jet to determine the aerodynamic characteristics of two double-wedge-section delta wings of aspect ratio 1.3 and 2.3 to angles of attack of 50 degrees at a Mach number of 4.07. The results are compared with the predictions of linear theory, two-dimensional shock-expansion theory, Newtonian-impact theory, and a method which utilizes the shock-wave and expansion-wave equations expanded by the two-dimensional hypersonic-flow similarity parameter.

Report presenting testing of some of the flutter characteristics of a 1/4-scale model of the X-1E airplane wing and aileron in the transonic tunnel. The wing was tested as part of a complete model of an airplane over a Mach number range of 0.4 to 1.05 and a range of angles of attack. No stall flutter or classical flutter was encountered, but the results indicate that unstable aerodynamic damping is present on the ailerons at transonic speeds. Results regarding free play, angle of attack, aileron viscous dampers, and aileron tabs are provided.

Report presenting a description of an NACA propeller research vehicle, the McDonnell XF-88B airplane, and the results of testing undertaken with it to determine the aerodynamic characteristics of a supersonic propeller at speeds up to a flight Mach number of 1.01. Results regarding thrust distributions, variation of aerodynamic characteristics with Mach number, installation effects, and a comparison of experimental results with theoretical calculations and other data are presented. The propeller efficiency was measured at 78 to 79 percent and thrust distributions were of a uniform nature.

Report discussing the flutter characteristics of several control-surface configurations, including a wing with tip ailerons, an all-movable stabilizer, vertical tails with trailing-edge rudders, a t-tail, and some simple models of all-movable controls. Some trends of the configurations and suggestions for improving the flutter characteristics are provided.

Report presenting an experimental investigation to determine the effects of simulated engine nacelles on the flutter characteristics of a cambered A-plan-form wing with 45 degree sweepback of the leading edge, an aspect ratio of 3.6, and a taper ratio of 0.14. Results regarding a wing-mount fixed and a model with wing mount free are provided.

Free oscillation test to determine hinge moment of trailing-edge, flap control surface with various hinge-line positions at transonic speed. Results show that oscillating amplitude has a large effect on the control aerodynamic damping derivative and that the damping is unstable in the test Mach number range above about 0.90 for the hinge positions tested.

Report presenting free-oscillation tests to determine the dynamic hinge-moment characteristics of a trailing-edge, flap-type control surface with various hinge-like positions. Oscillating amplitude was found to have a large effect on the control aerodynamic damping derivative and the damping was found to be unstable in the test Mach number range above 0.90 for the hinge positions tested. Results regarding damping moments and flutter characteristics, spring moments, and effect of hinge-line position and comparison with theory are provided.

Memorandum presenting the results of some investigations of separation on heat transfer and a method of reducing separation and shows the heat transfer in regions of separation and reattachment for a few specific shapes. The results show that heat transfer in a separated region is strongly affected by the extent of separation, the location of the reattachment point, and the location of transition along the separated boundary.

"Methods and techniques developed for the study of buffeting by use of wind-tunnel models are described. Requirements on model damping and frequency characteristics, the model support system, and the effects of wind-tunnel turbulence on buffet tests are outlined. The results are shown of a recent comparison of buffet loads measured on a research airplane with thin unswept wings and on two different models of the airplane in two different wind tunnels" (p. 1).

Report describing the design and flight evaluation of an air-borne target simulator using precomputed relative kinematics for use in tracking studies of fighter aircraft equipped with scope-presentation type fire-control systems. Testing occurred in an F86D airplane equipped with a Hughes E-4 fire-control system. Results regarding relative kinematic programming considerations and restrictions to system evaluation are provided.