Report presenting an investigation on a transonic bump to determine the aerodynamic characteristics of a series of triangular wings. Four basic triangular-wing plan forms with different aspect ratios, taper ratios, and combinations of tip clipping were tested over a range of Mach and Reynolds numbers. Results regarding angle of attack, drag coefficient, pitching-moment coefficient with lift coefficient, and various curves are provided.

"The equations presented in this report give the interference on the trailing-vortex system of a uniformly loaded finite-span wing in a circular tunnel containing partly open and partly closed walls, with special reference to symmetrical arrangements of the open and closed portions. Methods are given for extending the equations to include tunnel shapes other than circular. The rectangular tunnel is used to demonstrate these methods. The equations are also extended to nonuniformly loaded wings" (p. 361).

Report presenting an investigation to evaluate the overall performance characteristics of several annular nose inlets in the supersonic wind tunnel at a Mach number of 3.85. The four experimental configurations investigated consisted of a one-cone, a one-cone with low angle cowl, a two-cone, and an isentropic inlet. Results regarding the internal-flow performance, force measurements at zero angle of attack, overall performance comparison at zero angle of attack, and angle-of-attack force measurement are provided.

Report presenting tests to determine the flight characteristics of an F-86A airplane equipped with an area-suction boundary-layer-control system on the flaps and to investigate the possible operational problems which may arise on a flight installation of boundary-layer control. Results regarding the airplane with slatted leading edge, suction requirements, airplane with suction flap and various leading-edge configurations, factors affecting flap lift increment, and operational characteristics of boundary-layer control are provided.

Report presenting an investigation of several wingless missile configurations for a range of Mach numbers to determine their lift, drag, and pitching-moment coefficients. Results for missiles having nose controls and missiles having tail controls are provided. The results were also compared to a conventional missile with wings.

A compilation of the six technical papers presented at the NACA Conference on Engine Stall and Surge on February 3, 1955 at the Lewis Flight Propulsion Laboratory. A list of conference attendees is also provided.

Memorandum presenting a determination of the performance of a single-cylinder spark-ignition engine modified to operate on a compression-ignition cycle with a compression ratio of 8.0. Experimental data were obtained at an inlet-manifold pressure of 100 inches of mercury absolute, fuel-air ratios of 0.040 and 0.025, and engine exhaust pressures of 30 to 100 inches of mercury absolute. Results regarding single-cylinder-engine experimental data and full-scale-engine calculations are provided.

Report presenting investigations to determine the antiknock effectiveness of various additive-water solutions used as internal coolants in conjunction with AN-F-28, Amendment-2, fuel in a modified CFR engine.

Report presenting a correlation of carbon deposition of 19 fuels in a turbojet combustor as a function of the boiling point and of the flame height at the sooting point of the fuels in a simple wick lamp for a particular combustor operating at a single set of conditions. Two similar investigations with different combustors, operating conditions, and nine different fuels yielded similar correlations on the same graph.

Report presenting the results of tests of four model wings of aspect ratios 1, 2, 4, and 6 and with NACA 65(sub 1)-210 sections. The experimental lift-curve slope is compared with predictions from theory. Results regarding lift, drag, and pitching moment, lift-curve slope, drag divergence, minimum drag, and pitching moment are provided.

Report presenting the effects of fuel properties and change in simulated engine operating conditions on carbon deposition in an annular turbojet combustor. The fuel properties examined included specific gravity, volumetric average boiling temperature, hydrocarbon type, and hydrogen-carbon weight ratio. The fuels included hydrocarbons of the paraffinic, olefinic, and aromatic types as well as fuel mixtures.

Ignition delays of alkyl thiophosphites were obtained in a modified open-cup apparatus and a small-scale rocket engine apparatus. At -40 F, mixed alkyl thiophosphites gave short delays with white fuming nitric acid containing 2 percent water and red fuming nitric acids of widely varying compositions. At -40 F and higher, triethyl trithiophosphite blended with as much as 40 percent n-heptane gave satisfactory self-igniting properties at temperatures as low as -76 F.

From Summary: "The investigation of air-launched ram-jet engines has been extended to include a study of models with a nominal design free-stream Mach number of 2.40. These models require auxiliary thrust in order to attain a flight speed at which the ram jet becomes self-accelerating. A rocket-boosting technique for providing this auxiliary thrust is described and time histories of two rocket-boosted ram-jet flights are presented. In one flight, the model attained a maximum Mach number of 2.20 before a fuel system failure resulted in the destruction of the engine. Performance data for this model are presented in terms of thrust and drag coefficients, diffuser pressure recovery, mass-flow ratio, combustion efficiency, specific fuel consumption, and over-all engine efficiency."

Report presenting an investigation to correlate the isothermal contour lines formed downstream of a single jet of liquid ammonia directed normal to an air stream. Criteria are presented to facilitate the design of jet-engine thrust-augmentation systems utilizing the injection of liquid ammonia to cool the air at the compressor inlet.

Report presenting an investigation on a model of a 40 degree swept-wing fighter airplane to determine modifications which would eliminate the pitch-up that occurred near maximum lift during flight testing. The effects of high-lift and stall control devices, horizontal-tail locations, external stores, and various inlets on the longitudinal characteristics of the model were investigated.

Memorandum presenting an investigation conducted to determine the effect on the low-speed resistance and spray characteristics and static transverse stability of a modification which extended the bow of a scale model of a nose-inlet transonic seaplane configuration. The investigation was made with and without tip floats. The change was found to result in a 50-percent reduction in the hump resistance, increased engine-inlet clearance, reduced low-speed spray and hull-side flow, and acceptable spray and resistance at 25-percent overload.

Report presenting results of evaluation flights of F-86 series aircraft equipped with two types of boundary-layer control, which differed significantly in regards to the type of lift increment produced. The report presents the comments of 16 Air Force, Navy, contractor, and NACA pilots as to the reasons for their choice of minimum, comfortable approach speed on the several configurations tested.

Report presenting an investigation in the high-speed tunnel at Mach numbers from 0.80 to 0.92 to determine the effects of fuselage shape on the aerodynamic characteristics of a model with low and high wing arrangements. Results regarding longitudinal stability characteristics and lateral stability characteristics of the different component combinations are provided.

"An investigation was conducted to determine the knock-limited blending characteristics of leaded fuels containing selected aromatic fuel components (benzene, toluene, mixed xylenes, and cumene). Each of the aromatics was blended with an alkylate blending agent and with a virgin base stock. The blending characteristics of the resulting fuels were determined in a full-scale aircraft-engine cylinder" (p. 1).

Report presenting heat-transfer measurements for a flat-face cylinder-flare configuration in free flight up to Mach number 2.7. Skin temperatures were measured at 12 points along the configuration. Information about the heating rates was compared to data obtained from theoretical calculations.

An investigation of the antiknock effectiveness of various additive-water solutions when used as internal coolants has been conducted at the NACA Cleveland laboratory. Nine compounds have been previously run in a CFR engine and the results are presented. In an effort to find a good anti-knock-coolant additive with more desirable physical properties than those of the nine compounds previously investigated, water solutions of four alkyl amines, three alkanolamines, six amides, and eight heterocyclic compounds were investigated and the results are presented.

Report presenting a wind-tunnel investigation of several wingless missile configurations. Lift, drag, and pitching-moment coefficients were measured for a range of Mach numbers. Results regarding the missiles with nose controls and missiles with tail controls are provided.

Report presenting wind-tunnel measurements of the forces and moments of a model of an airplane with pitch-up tendencies at angles of attack up to 70 degrees. The model had an unswept, low-aspect-ratio wing, a long fuselage, and a high horizontal tail. Results regarding longitudinal and lateral directional characteristics, effects of wing-tip tanks and tip-tank fins, and longitudinal characteristics of the fuselage-tail combination are provided.

Report presenting an investigation to determine some of the effects of lip geometry on drag and pressure recovery of a normal-shock nose inlet. Lip bluntness, lip camber, and forebody angle were all explored as possible variables. Total-pressure recoveries, external drags, duct total-pressure distributions, lip and forebody pressure distributions, and Schileren photographs are provided.