Report presenting testing of the subsonic and transonic handling qualities of the Douglas D-558-II research airplane using several configurations of mid-semispan external stores in the altitude region of 20,000 to 40,000 feet. The configurations had an underslung pylon on each wing, pylons plus simulated 1000-pound bombs, and pylons with 150-gallon fuel tanks. Results regarding longitudinal stability and control characteristics, low-speed characteristics, and lateral stability and control characteristics are provided.

Report presenting an investigation at high subsonic speeds of a complete model with a highly tapered wing and several tail configurations. The complete model was tested with a wing-chord-plane tail, a T tail, and a biplane tail. A discussion regarding the lateral derivatives and sideslip characteristics is provided.

Report presenting testing of four multiweb wing structures similar to those on an airplane or missile at Mach number 2, sea-level static pressure, a 0 degree angle of attack, and stagnation temperature of 500 degrees Fahrenheit. Three models were made of 2024-T3 aluminum alloy and one was made from SAE 1010 steel; internal structure and skin thickness varied across the models. Results regarding model behavior, model temperatures, calculated skin temperatures, strain-gage results, model pressures, and calculated pressures are provided.

Report presenting testing of two identically constructed 2024-T3 aluminum-alloy multiweb-wing structures, models MW-2-(2) and MW-2-(3), under aerodynamic conditions similar to those encountered in supersonic flight at Mach number 2. Results regarding model temperatures, Stanton number, model pressures, model strains, behavior of Model MW-2-(2), and behavior of Model MW-2-(3) are provided.

Report discussing an investigation into the mutual interference loads on a supersonic bomber configuration and store during separation of the store. Tests were performed at several airplane angles of attack, store angles of attack, and airplane sidestep angles. The aerodynamic characteristics of the various components and coefficients of forces are provided in tables.

Report discussing zero-lift drag data for several bomb configurations at various Mach numbers. Seven configurations were tested with different combinations of interchangeable noses and tail cones with fins, some with different surface conditions. Surface conditions were not found to affect the drag, but the thickness of the tail fins and shape of the noses did change the shape of the drag curve.

Combustion blow-out velocities were determined for JP-4 solutions containing: (1) 10 % ethylene - decaborane reaction product, (2) 10% and 20% acetylene - diborane reaction product, and (3) 5.5%, 15.7%, and 30.7% methylacetylene - diborane reaction product. These were compared with blow-out velocities for JP-4, propylene oxide, and neohexane and previously reported data for JP-4 solutions of pentaborane. For those reaction products investigated, the blow-out velocities at a fixed equivalence ratio were higher for those materials containing higher boron concentrations; that is, blow-out velocity increased in the following order: (1) methylacetylene - diborane, (2) acetylene - diborane, and (3) ethylene - decaborane reaction products.

The heat of combustion of the product formed by the reaction acetylene and diborane was found to be 20,100 +/- 100 Btu per pound for the reaction of liquid fuel to gaseous carbon dioxide, gaseous water, and solid boric oxide. The measurements were made in a Parr oxygen-bomb calorimeter, and chemical analyses both of the sample and of the combustion products indicated combustion in the bomb calorimeter to have been 97 percent complete. The estimated net heat of combustion for complete combustion would therefore be 20,700 +/- 100 Btu per pound.

"The net heat of combustion of the product formed by the reaction of diborane with a mixture of acetylene and ethylene was found to be 20,440 +/- 150 Btu per pound for the reaction of liquid fuel to gaseous carbon dioxide, gaseous water, and solid boric oxide. The measurements were made in a Parr oxygen-bomb calorimeter, and the combustion was believed to be 98 percent complete. The estimated net-heat of combustion for complete combustion would therefore be 20,850 +/- 150 Btu per pound" (p. 1).

"Flutter tests have been conducted on two low-aspect-ratio wing plan forms under consideration by the Boeing Airplane Company for the 110A weapons system. These configurations had three heavy nacelles near the trailing edge, and flutter tests were made both with and without the nacelles. Up to a Mach number of 3.0 the dynamic pressure required for flutter of a wing with nacelles was generally higher than that of a wing without nacelles" (p. 1).

"Flutter tests have been conducted on two low-aspect-ratio wing plan forms under consideration by the Boeing Airplane Company for the 110A weapons system. These configuraiotns had three heavy nacelles near the trailing edge, and flutter tests were made both with and without the nacelles. Up to a Mach number of 3.0 the dynamic pressure required for flutter of a wing with nacelles was generally higher than that of a wing without nacelles" (p. 1).

From Introduction: "The configuration described in this paper represents one approach to such an airplane and the results of the wind-tunnel and tank evaluations are presented. In the present investigation, the aerodynamic longitudinal characteristics over a Mach number range from 0.6 to 1.97 were obtained."

Report discussing the hydrodynamic planing-lift forces of a model of a rectangular jet with several boundaries with slots in them in order to obtain varying boundary solidities. The lift coefficients at the different boundary solidities were compared to computed values from an equation. Information about the effects of boundary solidity, the level of optimum solidity, and the effects of speed is provided.

Memorandum presenting an investigation of the effectiveness of water-vaporization cooling that would be obtained by ejecting water upstream from the stagnation point conducted in a liquid-fuel rocket jet as a stagnation temperature of 4000 degrees Fahrenheit.

Report presenting two-dimensional porous-wall cascade tests of specified NACA blade sections at typical compressor hub conditions at speeds up to choking. For typical compressor blade hub sections, the angle of attack for best operation at high Mach numbers is about 6 degrees higher than the design angle of attack for low speeds. Results regarding the 65-series blade tests and circular-arc blade-section tests are provided.

Report presenting testing of a highly polished 9-inch-diameter hemisphere-cylinder in flight in order to obtain boundary-layer transition and heat-transfer data. Results regarding the free-stream conditions, pressure measurements, temperature measurements, heat-transfer measurements, and transition and transition parameters are provided.

"The performance of a full-scale translating-spike inlet was obtained at Mach numbers of 1.8 and 2.0 and at angles of attach from 0 deg to 6 deg. Comparisons were made between the full-scale production inlet configuration and a geometrically similar quarter-scale model. The inlet pressure-recovery, cowl pressure-distribution, and compressor-face distortion characteristics of the full-scale inlet agreed fairly well with the quarter-scale results" (p. 1).

Report presenting an investigation of an inlet with combined external and internal supersonic compression, formed by spike and cowl oblique shocks, and an overall length of 2.5 inlet diameters at a range of Mach numbers over a range of angles of attack. With proper boundary layer control on the centerbody, this method of internal compression did not adversely affect the high performance of the inlet.

Memorandum presenting the results of experimental and theoretical data on nine cowls to determine the effect of initial lip angle and projected frontal area on the cowl pressure drag coefficient at Mach numbers from 1.90 to 3.88. Results regarding the surface pressure coefficients, pressure distributions, effect of lip angle, projected cowl area, and Mach number on the cowl pressure drag coefficients are provided.

Memorandum presenting an analysis to determine, for control design purposes, the approximate response of pressures in the ramjet engine to changes in fuel flow. In the first part, the response after dead time is treated by the linearized lumped-parameter method. In the second, the dead time occurring between the change in fuel flow and the beginning of the pressure response is discussed.

Report presenting an investigation to determine the effects of simulated engine nacelles and wing-root freedoms on the flutter characteristics of a cambered, modified, swept, tapered, semispan wing through a range of Mach numbers. Wings were tested with and without nacelles and with the model restrained, free to roll, and free to translate in the vertical direction. Results regarding the effect of nacelles, flutter boundary, and effect of wing-mount freedom are provided.

Report presenting an experimental investigation made in the supersonic flutter tunnel to determine the effects of simulated engine nacelles and wing-root freedoms on the flutter characteristics of a cambered, modified, swept, tapered, semispan wing over a range of Mach numbers. Results regarding the effect of nacelles, flutter boundary, and effect of wing-mount freedom are provided.

Report presenting flight and analog-simulator tests with a prototype automatic interceptor in order to study the effects of elevating the radar-boresight axis on the stability and tracking performance of the system. Results regarding effects of interceptor rolling motion upon tracking errors, similarity of flight results and analog-computer results, effect of elevating the radar-boresight axis upon stability, effect of elevating the radar-boresight axis upon the required bank-angle feedback, and application of the principle of elevated radar-boresight axis are provided.

Report presenting flight and analog-simulator tests with a prototype automatic interceptor in order to study the effects of elevating the radar-boresight axis on the stability and tracking performance of the system. The interceptor was designed to perform the lead-pursuit type of attacks and test runs were made in flight and on the analog simulator with and without lead-angle computation. Results regarding the effects of interceptor rolling motion upon tracking errors, similarity of flight results and analog-computer results, effect of elevating the radar-boresight axis upon stability, and application of the principle of elevated radar-boresight axis are provided.