Report presenting simulator studies of a homing missile pursuing a constant-velocity nonmaneuvering target. The missile dynamics in pitch and roll, seeker method of deflection and control, and the missile-target geometry were simulated to determine whether the method of control and detection in conjunction with the missile dynamics were feasible.

Report presenting flight tests using a rocket-propelled 60 degree delta-wing body configuration, which included a NACA 0003-63 wing airfoil section. Drag at lift and stability data were obtained for a range of Mach numbers.

Report presenting an investigation in the 4- by 4-foot supersonic pressure tunnel to determine the static longitudinal and lateral stability and control characteristics of an 0.065-scale model of the Chance Vought Regulus II missile. The tests were made at three Mach and Reynolds numbers.

From Summary: "A method of computing span loads and the resulting rolling moments for sideslipping wings of arbitrary plan form in incompressible flow is derived. The method requires that the span load at zero sideslip be known for the wing under consideration. Because this information is available for a variety of wings, this requirement should not seriously restrict the application of the present method. The basic method derived herein requires a mechanical differentiation and integration to obtain the rolling moment for the general wing in sideslip."

Memorandum presenting a supersonic wind-tunnel investigation of the origin and distribution of store interference performed in the 4- by 4-foot supersonic pressure tunnel at Mach number 1.6. Separate forces on a store, a fuselage, a swept wing, and a swept-wing-fuselage combination were measured. The configuration investigated simulated a heavy bomber airplane with a large store or nacelle with frontal area equivalent to a twin-engine nacelle.

Memorandum presenting an experimental investigation of the adaptation of a transonic slotted tunnel to supersonic operation by enclosing the slots with fairings. The adaptation allows the extension of peak Mach number of the tunnel to be made at a reasonable cost in both time and effort, provided simplicity and ease of installation are taken into consideration during the design of the cover fairings. The nozzle is found to be sensitive to phenomena that will cause thickening of the boundary layer in the slot cover fairing.

Report discussing testing to determine the longitudinal and lateral stability and control characteristics of a Chance Vought Regulus II missile at several Mach and Reynolds numbers.

Report presenting an analysis and examination of a large volume of data from several recent stores-research programs. For a given wing plan form, store position and configuration of angle of attack have been shown to be the most important parameters in the evaluation of store side force.

Data obtained from the first flight test of a ram jet utilizing a magnesium slurry fuel are presented. The ram jet accelerated from a Mach number of 1.75 to a Mach number of 3.48 in 15.5 seconds. During this period a maximum values of air specific impulse and gross thrust coefficient were calculated to be 151 seconds and 0.658, respectively. The rocket gas generator used as a fuel-pumping system operated successfully.

"This report gives the results of a detailed study of the flutter characteristics of four representative aircraft wings. This study was made using the electric-analog computer at the California Institute of Technology. During the course of this investigation eight important parameters of each wing were varied and, in addition, the effects of mass, inertia, pitching spring, and location of a concentrated mass were investigated for all four wings and at several sweepback angles" (p. 1385).

Memorandum presenting an investigation conducted in the 4- by 4-foot supersonic pressure tunnel to determine the effects of wing vertical location and geometric dihedral on the aerodynamic characteristics in pitch and sideslip of a wing-body configuration at Mach number 2.01. The configurations investigated included a high-wing, midwing, and a low-wing arrangement.

Report presenting a scale rocket-propelled model of the Convair XF2Y-1 water-based fighter airplane in free flight in a range of Mach numbers. Results regarding stability characteristics, trim characteristics, drag characteristics, and inlet and duct characteristics are provided.

Report presenting the results of an investigation to determine the dynamic stability and control characteristics of a delta-wing vertically rising airplane model powered by a ducted fan. The model had flap-type control surfaces on the wings and vertical tail as well as movable eyelids at the rear of the tail pipe and air bled from the main duct and exhausted through movable nozzles near the wing tips. The model was found to generally fly smoothly and easily without automatic stabilization devices.

Report presenting an investigation at low speed to determine the static aerodynamic forces and moments on a canard missile model during launching from the midsemispan and wing-tip locations of a wing-fuselage combination with a 45 degree sweptback wing. When the missile was mounted under the wing at the midsemispan location, changes in chordwise position produced large changes in missile forces and moments.

Memorandum presenting an investigation of the dynamic stability of the Bell X-5 research airplane at 58.7 degrees sweepback and at altitudes of 40,000 feet and 25,000 feet over a Mach number range of 0.5 to 0.97. The results show that the longitudinal oscillatory motions are well damped over the entire Mach number range except for residual oscillations resulting primarily from engine gyroscopic coupling with the lateral oscillatory mode. The longitudinal and lateral frequency-response characteristics were obtained and some coupling effects were noted.

From Summary: "An investigation of a 0.034-scale model of the production version of the Chance Vought F7U-3 airplane has been conducted in the Langley 20-foot free-spinning tunnel. The inverted and erect spin and recovery characteristics of the model were determined for the combat loading with the model in the clean condition and the effect of extending slats was investigated. A brief investigation of pilot ejection was also performed."

Memorandum presenting tests of two rocket-powered models of a 45 degree swept-wing airplane configuration with different underwing fuel-tank installations located at approximately half the wing semispan. Results of the tests were compared with previously reported data from a similar configuration with no tanks and with isolated tank data. These results include trim, buffeting, drag, and static longitudinal stability are provided.