"Time histories are presented of horizontal-tail loads, elevator loads, and deformations on a jet-powered bomber during abrupt pitching maneuvers at a pressure altitude of approximately 20,000 feet. The normal and pitching accelerations measured varied from -0.90b to 3.41g and from -0.73 to 0.80 radian per second per second (sic), respectively, with a Mach number variation of from 0.40 to o.75. The maximum horizontal-tail load measured was 17,250 pounds down. The maximum elevator load was 1900 pounds up. The stabilizer twisted a maximum of 0.76 degrees leading edge down at the tip. The greatest fuselage deflection at the tail was about 1.7 inches down" (p. 1).

Report discussing an investigation to determine the aerodynamic characteristics of a model of a tailless delta-wing airplane configuration with a leading edge swept back 60 degrees at a range of Mach numbers. Information about lift-curve slope, buffeting, drag rise, hinge-moment coefficients, transonic trim, and stability is provided.

"Forced-convection heat-transfer data have been obtained for water flowing in an electrically heated tube of circular cross section at water pressures of 200 and 2000 pounds per square inch, and temperatures in the nonboiling region, for water velocities ranging between 5 and 25 feet per second. The results indicate that conventional correlations can be used to predict heat-transfer coefficients for water at pressures up to 2000 pounds per square inch and temperatures in the nonboiling region" (p. 1).

Report presenting experiments conducted on conical convergent-divergent nozzles having included a range of divergence angles and expansion ratios over a wide range of nozzle pressure ratios with cold flow to determine the effect of divergence angle on the internal performance of the nozzles. Results regarding the performance characteristics, effect of divergence angle on overexpanded performance, and effect of divergence angle on nozzle air-flow characteristics are provided.

Report presenting an investigation to determine the pressure drag of various blunt-based conical afterbodies at a range of Mach numbers. A generalized series of bodies was included which incorporated convergent nozzles discharging unheated jets at various pressures from the base. Results regarding the afterbodies without the jet and afterbodies with the jet are provided.

Report presenting an investigation of a shock-positioning control on a 16-inch ramjet engine at a range of Mach numbers and angles of attack in the supersonic wind tunnel. The control operated at all conditions under which the engine could be manually operated. Prediction of the control-system dynamic behavior can be applied by treating the system as having pure dead time.

Report presenting an investigation of a shock-positioning control on a 16-inch ramjet engine at a range of Mach numbers and angles of attack in a supersonic wind tunnel. The static-pressure rise across the inlet normal shock was utilized in setting the diffuser at its critical condition. Results regarding the sensing pressures, engine performance, control set engine operation, pressure data, operation of the control during Mach number change, and other applications of control are provided.

Report presenting an investigation of the screeching characteristics of two flame-holder configurations in a full-scale transpiration-cooled afterburner. The investigation indicated that a porous wall of wire cloth may be effective in eliminating or reducing the tendency to screech in some high-performance afterburners, but further testing is required. Results regarding the diametrical V-gutter, single-ring V-gutter, and durability of wire cloth are provided.

Report presenting a free-flight investigation of the zero-lift rolling effectiveness and drag of 18 roll-control arrangements on a cruciform 80 degree delta-wing missile-like configuration over a range of Mach numbers. Testing was made of deflected surfaces, spoilers, and inlet-air-jet devices to give evidence to simple theory for deflected surfaces and to determine some effects of chordwise location for spoilers and blowing direction and spanwise location for jets near the wing trailing edge. All controls were found to be satisfactory roll-producing devices except canards located immediately forward of the main wings and spoilers.

Memorandum presenting an investigation in the 9-inch supersonic tunnel to ascertain the lift, drag, and pitching moments of typical body-bomb-bay configurations with and without the bomb. The bodies had elliptical, triangular, and teardrop cross sections. Results regarding effects of angle-of-attack variation and effects of Mach number variation are provided.

As-cast buckets of Guy alloy, a cast nickel-base material, were run in a J33-9 turbojet engine for cycles of 15 minutes at rated speed and 5 minutes at idle speed. Stress rupture, impace and engine-performance data indicate that Guy alloy may be considered for bucket use at a temperature of 1650 degrees F. Ductility and impact strength of Guy alloy is limited but appears to be adequate for bucket applications.

"A semigraphical analysis method has been devised to evaluate the effectiveness and dynamic stability of rolleron roll-rate dampers on missile configurations. The necessary charts, equations, and the analysis procedure have been presented. The greatest utility of these charts and of the method outlined is that, once a point on the charts has been established at a given flight condition, if the response is not acceptable than the necessary modifications to the parameters of the system are readily seen" (p. 1).

Report presenting an investigation in the 4- by 4-foot supersonic pressure tunnel to determine the static lateral and directional stability and control characteristics of a scale model of the Grumman F11F-1 airplane at Mach numbers of 1.41, 1.61, and 2.01. The complete model and various combinations of component parts were tested as well as various configuration changes including modified bodies and vertical tails. Results regarding the static lateral and directional stability, lateral and directional control, and variation of sideslip derivatives with Mach number are provided.

Report discussing an investigation of the thermal stabilities of a commercial grade of ethyl decaborane and decaborane at two temperatures. Equations developed from the results of the experiment are also provided. Ethyl decaborane was found to be more stable to pyrolysis than pentaborane but less stable than decaborane.