Report presenting an investigation conducted with trimethyl borate azeotrope and pentaborane fuels in a turbojet combustor. The primary purposes of the study were to determine the effect of boron oxide deposits on the turbine-nozzle area, combustor pressure loss, temperature distribution, and combustion efficiency. Three distinct boron deposit patterns were noted in the investigation.

Report discussing the performance of an experimental quarter-sector annular combustor at conditions simulating supersonic flight of a cooled-turbine engine, as well as 20 different modification to the design. The final configuration was found to show no structural failures and little or no warping of liner parts after 40 hours of operation.

Report presenting an investigation of the damping-in-roll characteristics of a 35 degree sweptback wing, with and without vertical fins, through a range of Mach numbers in the high speed 7- by 10-foot tunnel utilizing a free-to-roll technique. The damping-in-roll coefficient increased in magnitude with Mach number in the manner indicated by theory and generally was found to increase in magnitude with angle of attack over the range tested.

Report presenting an investigation to determine the aerodynamic characteristics of a series of thin, rectangular wings in the 16-foot high-speed wind tunnel using the transonic bump technique over a range of Mach and Reynolds numbers. Lift, drag, and pitching moment characteristics are presented for wings of 4 different aspect ratios and NACA 63A0XX sections and with 5 different thickness-to-chord ratios.

Theoretical performance for liquid lithium and liquid fluorine as a rocket propellant was calculated with assumptions both of equilibrium and frozen composition during expansion. Parameters included were specific impulse, combustion-chamber temperature, nozzle-exit temperature, composition, mean molecular weight, characteristic velocity, coefficient of thrust, and ratio of nozzle-exit area to throat area. For chamber pressure of 300 pounds per square inch absolute and expansion to 1 atmosphere, the maximum equilibrium specific impulse calculated was 335.5 pound-seconds per pound. The effect of ionization on calculated performance was shown to be negligible by comparison of values of various parameters calculated both with and without ionized products of combustion.

Report presenting some experimental and theoretical studies of axisymmetric free jets exhausting from sonic and supersonic nozzles into still air and into supersonic streams as a way to investigate problems associated with propulsive jets. A variety of variables for each case are considered, including jet Mach number, nozzle divergence angle, jet static-pressure ratio, free-stream Mach number, and specific heat ratios.

"It is shown how Schrenk's empirical method of estimating the lift distribution over straight wings can be adapted to swept wings by replacing the elliptical distribution by a new "ideal" distribution which varies with sweep.The application of the method is discussed in detail and several comparisons are made to show the agreement of the proposed method with more rigorous ones. It is shown how first-order compressibility corrections applicable to subcritical speeds may be included in this method" (p. 1).

Report presenting an investigation to determine some effects of tail damping and wing-tail interference on the rolling effectiveness of ailerons and a spoiler on a modified-delta wing. Results regarding the effect of adding fixed tail surfaces, effect of moving the horizontal tail out of the plane of the wing, and a comparison with theory are provided.

Report describing the design and flight evaluation of an air-borne target simulator using precomputed relative kinematics for use in tracking studies of fighter aircraft equipped with scope-presentation type fire-control systems. Testing occurred in an F86D airplane equipped with a Hughes E-4 fire-control system. Results regarding relative kinematic programming considerations and restrictions to system evaluation are provided.

Report presenting free-flight tests of two rocket models at a range of Mach numbers to determine the control rolling effectiveness and system operation of an autorotating-vane spoiler on a missile configuration with an 80 degree delta, cruciform wing. Results indicated that the system operated fairly satisfactorily as a flicker-type roll control except at low supersonic speeds.

"An investigation has been conducted in the Langley Unitary Plan Wind tunnel to determine the static stability and drag characteristics of a 1/10-scale model of the AVCO booster vehicle. The tests were made at a constant Reynolds number, based on maximum nose diameter, of 1.09 x 10(exp 6)6 at Mach numbers of 1.60 and 2.00" (p. 1).