Report presenting an investigation of the stress distribution in the roots of the first three stages of the J6S axial-flow compressor in order to explain root failures experienced in service. Root failures were producible in the lab when high vibratory stresses were combined with simulated centrifugal loads. Results regarding fatigue tests on the original J6S blade roots and on two redesigned blade roots as well as a comparison of the different root designs are provided.

Report presenting a theory of reduction of convective heat transfer to a surface in supersonic flow by periodically imposing a large-scale vortical motion on the boundary layer and an experimental investigation of that theory. Results regarding the pulsating flow phenomena, heat-transfer characteristics, and aerodynamic characteristics are provided.

Report presenting an investigation in the transonic tunnel to determine the effects of adding external, pylon-suspended stores to a model of the Douglas D-558-II research airplane. Tests were made for two spanwise store locations and covered a range of angles of attack and Mach numbers. Results regarding the drag, lift, and pitching-moment characteristics are provided.

Report presenting an evaluation of the interaction between a flat plate and a nearby jet issuing from a convergent nozzle over a range of pressure ratios and free-stream Mach numbers. The effect on the interaction of the presence of streamline, blunt-base, and curved-base fairings between the plate and parabolic afterbody housing the exit nozzle was also investigated.

A high-solidity low-aspect-ratio transonic rotor with an inlet hub-tip ratio of 0.52 was investigated experimentally. The rotor developed a total-pressure tatio of 1.93 and an efficiency of 92 percent at an equivalent wheel tip speed of 1036 feet per second. The feasibility of using this rotor as a component of an inlet stage of an axial-flow compressor was investigated.

Report presenting a supersonic flight investigation of a roll-stabilized acceleration control missile for a Mach number range from 1.4 to 1.7. The control system operation was found to be satisfactory and applicable to some present-day missiles using linear acceleration commands. Results regarding analysis, preflight simulator results, a comparison between simulator and analytical results, flight test results, and a comparison between the flight test and preflight simulator results are presented.

Report presenting an investigation in the 16-foot transonic tunnel to determine the effects of leading-edge droop on the pressure distribution on a 45 degree sweptback wing with an aspect ratio of 4, a taper ratio of 0.6, and NACA 65A006 airfoil sections parallel to the plane of symmetry. Results regarding the chordwise pressure distributions, wing-panel characteristics, wing-section characteristics, and maximum additional normal load on wing leading edge are provided.

Report presenting an investigation to determine the aerodynamic characteristics of the NACA 4-(5)(05)-037 six- and eight-blade, dual-rotation propellers operating at positive and negative thrust at a range of Mach numbers when operating at near static conditions. The propellers were operated in combination with a long spinner and at a variety of blade angles.

The problem of determining the shape of slender boattail bodies of revolution for minimum wave drag has been reexamined. It was found that minimum solutions for Ward's slender-body drag equation can exist only for the restricted class of bodies for which the rate of change of cross-sectional area at the base is zero. In order to eliminate this restriction, certain higher order terms must be retained in the drag equation and isoperimetric relations. The minimum problem for the isoperimetric conditions of given length, volume, and base area is treated as an example. According to Ward's drag equation, the resulting body shapes have slightly less drag than those determined by previous investigators.

Memorandum presenting a five-stage axial-flow compressor with all rotor rows operating with transonic relative inlet Mach numbers designed as a research unit to study the potentialities and problems arising from the compounding of transonic stages. The report presents all design values and procedures, blade-row velocity diagrams, and the selection of blade shapes.

"The relation of Whitcomb's "area rule" to the linear formulas for wave drag at lightly supersonic speeds is discussed. By adopting an approximate relation between the source strength and the geometry of a wing-body combination, the wave-drag theory is expressed in terms involving the areas intercepted by oblique planes or Mach planes. The resulting formulas are checked by comparison with the drag measurements obtained in wind-tunnel experiments and in experiments with falling models in free air. Finally, a theory for determining wing-body shapes of minimum drag at supersonic Mach numbers is discussed and some preliminary experiments are reported" (p. 757).

Report presenting an investigation of ten divergent- and two cylindrical-shroud ejectors to determine internal ejector performance over a range of pressure ratios and expansion area ratios for Mach numbers up to about 3. Results regarding jet-thrust and air-handling characteristics and net-thrust performance are provided.

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 1.61 in which separate forces on a store, a fuselage, a swept wing, and a swept-wing-fuselage combination were measured. The report presents data on a configuration which simulated a heavy-bomber airplane with stores of several shapes and sizes.

Report presenting a supersonic wind-tunnel investigation of the origin and distribution of store interference in the 4- by 4-foot supersonic pressure tunnel at Mach number 1.61. The separate forces on a store, a fuselage, a swept wing, and a swept-wing-fuselage combination were measured. Results regarding drag, lift, pitching moment, side force, and yawing moment are provided.

Report presenting a preliminary study to determine the possibility of utilizing a wingless configuration as a guided missile. The results indicated that the maximum trimmed lift coefficient developed by the wingless missile was somewhat smaller than that of the winged missile at a Mach number of 2.4.

Report presenting an investigation of an airplane configuration model with a 45 degree swept wing of aspect ratio 4.0 and a taper ratio 0.3 with a low swept horizontal tail to determine its longitudinal stability. Longitudinal aerodynamic coefficients and stability derivatives are presented as functions of Mach number over the test range. The results are compared to wind tunnel and rocket model data and generally show good agreement.

Memorandum presenting a preliminary free-flight study of the drag and stability of a series of short-span missile configurations with 80, 85, and 90 degrees of fin leading-edge sweep. Increasing the fin sweep decreased the drag markedly.

Report discussing tests performed with a rocket-boosted model of the McDonnell F4H-1 airplane at transonic and supersonic speeds. Special attention is given to the external drag coefficient at various Mach numbers. Large pitching oscillations were also noted at Mach numbers between 0.20 and 1.17, which made it impossible to determine the drag at that range.

Report discussing testing on two wing-fuselage models with 45 degree sweptback wings and various missile arrangements, one with pylons underneath the wing and one with the missiles semisubmerged in the sides of the fuselage. A comparison of the drag of both types of models was made.

Report discussing a series of experiments involving the reaction of water with decaborane and HEF-3, a boron fuel containing ethyldecaborane. The chemical properties of the hydrolysis reaction are described. Two isomers were also prepared to assist with the syntheses, and their melting points, molecular weights, and solubilities in certain solvents are included.

Report presenting the results of an investigation of cross-sectional-area distribution, nacelle configuration, and landing-gear-fairing configuration on the minimum drag characteristics of a model of a four-engine bomber airplane with a low-aspect-ratio triangular wing. The lateral stability characteristics are also included.

Memorandum presenting results of tests for possible flutter of a dynamically and elastically scaled model of a proposed all-movable horizontal tail surface for the North American X-15 airplane. Tests at Mach number 6.86 were made on the scaled model and on several other configurations with lower stiffnesses.

Memorandum presenting an investigation to determine the dynamic lateral stability characteristics of a configuration of the North American X-15 research airplane. Of specific concern were characteristic modes, period and damping, airplane response to yaw and roll controls, ratio of roll to sideslip in the Dutch-roll oscillation, and the roll-coupling problem. Results regarding stability-boundary plots, characteristic roots, roll-to-sideslip ratio, and time histories are provided.

"An investigation has been made at Mach numbers of 1.61 and 2.01 and Reynolds numbers of 1.7 x l0(exp 6) and 3.6 x l0(exp 6) to determine the pressure distributions over a swept wing with a series of 14 control configurations. The wing had 40 deg of sweep of the quarter-chord line, an aspect ratio of 3.1, and a taper ratio of 0.4. Measurements were made at angles of attack from 0 deg to +/- 15 deg for control deflections from -60 deg to 60 deg. This report contains tabulated pressure data for the complete range of test conditions" (p. 1).