Report presenting an investigation of a configuration with a body of fineness ratio 16.9, a 52.5 degree sweptback wing of aspect ratio 3, taper ratio 0.2, and NACA 65A004 airfoil section, and an incline tail which was aeropulsed continuously in pitching during free flight with and without a sustainer rocket motor operating. The Mach number range covered was from 1.4 to 2.3. Results regarding drag, total normal force and pitching moment, wing normal-force-curve slope, flow conditions at the horizontal tail, and cross coupling 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.

Boundary-layer transition data at low ratios of wall to local stream temperature have been obtained during the free flight of a highly polished cone-cylinder to a maximum Mach number of 5.02 A maximum transition Reynolds number of 32 x 10(exp 6) occurred at a distance of 25.84 inches from the cone apex. The temperature ratio at transition for a local Mach number of 4.0 was approximately 1.30 as compared with theoretical infinite stability solutions of 1.47 and 1.65 by Dunn and Lin (three-dimensional) and Van Driest (two-dimensional), respectively.

Report presenting an investigation in the 4- by 4-foot supersonic pressure tunnel to determine the effects on the static longitudinal stability and control characteristics of various modifications to a 0.065-scale model of the Chance Vought Regulus II missile. Some of the modifications included control housing on top of the fuselage, two sizes of canard surfaces with fixed incidence angles, various angles of nose droop, and two types of inlet boundary-layer bleed diverters.

Report presenting a study to show the effect of fuel-air ratio and initial temperature on spark-ignition energy and to apply the results to a previously developed theory of ignition. Results regarding initial-temperature effect and fuel-air-ratio effect are provided.

"Some of the considerations involved in the design of aircraft fuel tanks for liquid hydrogen are discussed herein. Several of the physical properties of metals and thermal insulators in the temperature range from ambient to liquid-hydrogen temperatures are assembled. Calculations based on these properties indicate that it is possible to build a large-size liquid-hydrogen fuel tank which (1) will weigh less then 15 percent of the fuel weight, (2) will have a hydrogen vaporization rate less than 30 percent of the cruise fuel-flow rate, and (3) can be held in a stand-by condition and readied for flight in a short time" (p. 1).

Report presenting an investigation of several methods of straightening diffuser-exit total-pressure profiles produced by a typical half-conical double-shock side inlet at a free stream Mach number of 3.05. The methods included the use of longer subsonic diffusers, constant-area mixing sections at the diffuser exit, internal screens, a rapid acceleration of the flow at the diffuser exit, internal bleed, and a change in internal-flow passage shape obtained by raising the internal centerbody fairing from the floor into the diffuser duct. Each of the methods was found to be effective in reducing distortion.

"The zero-lift drag of a 1/7-scale model of the Convair B-58 external store was obtained at mach numbers between 0.8 and 2.45 at corresponding Reynolds numbers per foot of 3.5 x 10 to the 6th power and 15.3 X 10 to the 6th power. The experimental drag data are compared with calculated values at both subsonic and supersonic speeds and show good agreement. In addition to the drag data, some static stability derivatives and damping factors were also obtained and are presented with the predicted values of these derivatives for completeness and for comparison" (p. 1).

From Summary: "A flight test has been conducted to determine the longitudinal stability and control characteristics of a 0.125-scale model of the McDonnell F-101A airplane for the Mach number range between 0.82 and 1.84. The variation of lift-curve slope with Mach number was gradual with a maximum value of 0.107 occurring at a Mach number of 0.95. The minimum drag coefficient (including base and internal drag) has a value of 0.020 at a Mach number of 0.87. The drag rise begins at a Mach number of 0.90, and at Mach number of 1.10 the minimum drag is 0.070. Above this Mach number there is a gradual increase in minimum drag coefficient to a value of 0.074 when the Mach number is 1.83."

Report presenting measurements of recovery temperatures on a slender cone-cylinder with a 12 degree vertex angle and a 1.25-inch-diameter cylinder for a range of Mach numbers. Results regarding the visual evidence, temperature distributions, pressure distributions, summary figures, correlation of temperature patterns with boundary-layer transition and separation, and recovery factors are provided.

Report presenting a brief experimental investigation of a method for designing fuselage side air inlets with high internal total-pressure recovery and zero spillage drag at a specified design inlet mass-flow ratio. With a scoop designed according to the concept, near-zero spillage drag can be attained at the design inlet mass-flow ratio through a range of Mach numbers. Results regarding pressure recovery and drag due to the scoop are provided.

Report discussing testing of a multijet 60 degree delta-wing airplane configuration with twin-engine exhausts at specified locations under the wing. Data was obtained for jet-on and jet-off conditions between a range of Mach numbers. Results are presented for the effect of jet on drag, jet effect on lift, static longitudinal stability, and dynamic longitudinal stability.

Report presenting the longitudinal and lateral stability characteristics of a 40 degree swept-wing fighter model with and without horizontal tails of 0 degrees and 22.5 degrees negative dihedral for a range of Mach numbers, angles of attack, and sideslip.

Engine dynamics and controls data are presented for a ram-jet engine which was operated in a free-jet facility at a Mach number of 2.76 and altitudes from 68,000 to 82,000 feet. The predominant engine dynamic characteristics was dead time, with values ranging from 0.018 to 0.053 sec. The control systems were designed to hold a constant ratio of a diffuser static pressure to an inlet-cone reference static pressure.

"The effect of dissolved oxygen in the filter-clogging characteristics of three JP-4 and two JP-5 fuels was studied at 300 degrees to 400 degrees F in a bench- scale rig, employing filter paper as the filter medium. The residence time of the fuel at the high temperature was approximately 6 seconds" (p. 1).

For constant-mechanical-speed operation, the two-spool thrust values are as great as or greater than the one-spool thrust values over the entire flight range considered, while the specific fuel consumption for the two engines agrees within 1 percent. The maximum difference in thrust occurs at Mach 2.8 in the stratosphere, where the two-spool thrust advantage is about 9 percent for operation with the after burning.

Memorandum presenting an annotated bibliography of NACA reports containing information of interest to designers and manufacturers of controls for turbojet engines. The eleven major topics include starting, acceleration, flame-out, temperature control, stability and dynamics of small disturbances, combustion dynamics, engine inlet diffuser control, steady-state engine performance, fuel systems, sensors, and general control system theory.

From Introduction: "The purpose of the flight investigation described herein was as a "proof" check of the system and to determine what effect several variables which could not be practicably simulated would have on the operation."

The effect of the design characteristics of various condensing chambers on magnesium build-up at the chamber inlet was investigated. The condensing chambers are used in the vapor-condensation process for making magnesium slurries. A complete description of the various chamber designs and the procedure used in testing the chambers is given. The results are evaluated on the basis of clogging and total magnesium distilled per run. Orifice design was also considered.

Report discussing testing on a model of the General Electric P-1 nuclear powerplant to determine its internal aerodynamic characteristics. The main purposes of testing were to measure the mass-flow distribution of air, to measure the total-pressure losses for the duct components and complete model, and to determine modifications necessary to attain the desired performance characteristics.

Report presenting an investigation at sea-level static conditions to determine the effects of radial discharge of cooling air from turbine rotor blades on turbine performance in two turbojet engines, one with a centrifugal compressor and the other with an axial-flow compressor. Results regarding the performance characteristics, efficiency comparisons, and some interpretation are provided.

An investigation of the performance and operating characteristics of two variable-thrust injectors over a wide thrust range using mixed oxides of nitrogen and ammonia. Specific impulse, characteristic velocity, thrust coefficient, and overall efficiency are presented as functions of thrust. A maximum thrust range of 12 during one run was obtained with a triplet impinging-jet injector.

Report presenting the experimental values of damping in roll of the Bell X-1A airplane and its components at 5 Mach numbers at zero angle of attack. The wing was found to be the predominant contributor to the damping in roll throughout the range of Mach numbers, but the contributions of other airplane components were significant in the range of 2.22 to 2.41.

Report presenting a description of the Ames 2- by 2-foot transonic wind tunnel, its uses in testing, and a preliminary evaluation of the wall interference in the tunnel.