From Introduction: "This paper presents the results of an investigation conducted in the Langley 11-inch hypersonic tunnel to evaluate methods of increasing maximum lift-drag ratio."

Pressure distributions for a series of four boattailed bodies of revolution were obtained and compared with theory for a Mach number of 3.12, a Reynolds number range of 2 x 10 to 6th power to 14 x 10 to the 6th power, and angles of attack from zero to 9 degrees. Second-order theory adequately predicted the pressure distribution for regions free of the effects of cross-flow separation.

Memorandum presenting an analysis to determine the compressor pressure ratios and specific weight flows obtainable with single-stage air-cooled turbines for both nonafterburning and afterburning turbojet engines operating at a flight Mach number of 2 in the stratosphere. Wide ranges in turbine-inlet temperature, tip speed, hub-tip radius ratio, and coolant-flow ratio were considered.

From Introduction: "The purpose of this report is to present the results of the analysis and to compare them with the experimental results of the transonic turbine."

From Introduction: "In reference 1, in which the performance of conical supersonic scoop inlets on circular fuselages is reported, the drag of the bottom-inlet configuration was considerably higher than for the top inlet."

Memorandum presenting pulse techniques applied to strain gages for increasing the output level and extending the usable range. Bonded and unbonded strain gages which normally operate with exciting potentials between 3.5 and 14 volts operated satisfactorily with 200-volt pulses of 1-microsecond duration and a repetition rate of 350 per second. Results regarding maximum allowable voltages, effective pulse duration, sensitivity, minimum readable signal, effects of cable capacitance and inductance, sensitivity to external noise, and linearity are provided.

Note presenting the results of buckling tests of long square tubes loaded in compression, torsion, and combined compression and torsion and a comparison with theoretical compression and shear buckling curves and with theoretical interaction curves for the buckling of simply supported flat plates. Results regarding the pure compression and pure torsion buckling and combined compression and torsion buckling are provided.

Report presenting a method for determining the lateral-stability derivatives, transfer-function coefficients, and the modes for lateral motion from frequency-response data for a rigid aircraft. The method is based on the application of the vector technique to the equations of lateral motion, so that the three equations of lateral motion can be separated into six equations. Two numerical examples are given to demonstrate the use of the method.

"Results are reported of current studies at the Forest Products Laboratory to develop a metal-bonding adhesive with greater resistance to temperatures up to 600 degrees Fahrenheit that is easier to use than present ones. Most promising is a formulation of phenol and epoxy resins modified with hexamethylenetetramine and supplied for use as a dry tape supported on a glass-mat base" (p. 1).

Report presenting a low-speed investigation in the stability tunnel to determine and improve, if possible, the directional stability characteristics of two tandem helicopter fuselages, one representing a helicopter with overlapping rotors and the other a helicopter with nonoverlapping rotors. Results regarding the presentation of data, directional stability of overlap-type fuselage, and directional stability of nonoverlap-type fuselage are provided.

Report presenting an experimental investigation to define the downwash field and vortex-sheet shape behind a large-scale wing-fuselage combination with a 63 degree sweptback wing of aspect ratio 3.5. At positive angles of attack, the vortex sheet assumed a shape which initially bowed upward but flatten out downstream before the rolling-up process had occurred to an appreciable degree. Results regarding downwash data, shape and location of the vortex sheet, path of the vortex core, and comparison of theories with experimental results are provided.

An investigation was conducted on a 35 deg swept-wing fighter airplane to determine the effects of several blunt-trailing-edge modifications to the wing and tail on the high-speed stability and control characteristics and tracking performance. The results indicated significant improvement in the pitch-up characteristics for the blunt-aileron configuration at Mach numbers around 0.90. As a result of increased effectiveness of the blunt-trailing-edge aileron, the roll-off, customarily experienced with the unmodified airplane in wings-level flight between Mach numbers of about 0.9 and 1.0 was eliminated, The results also indicated that the increased effectiveness of the blunt aileron more than offset the large associated aileron hinge moment, resulting in significant improvement in the rolling performance at Mach numbers between 0.85 and 1.0. It appeared from these results that the tracking performance with the blunt-aileron configuration in the pitch-up and buffeting flight region at high Mach numbers was considerably improved over that of the unmodified airplane; however, the tracking errors of 8 to 15 mils were definitely unsatisfactory. A drag increment of about O.OOl5 due to the blunt ailerons was noted at Mach numbers to about 0.85. The drag increment was 0 at Mach numbers above 0.90.

Report presenting the effect of channel geometry on flame quenching, as calculated on the basis of average active particle chain lengths, is related among six different geometries: plane parallel plates of infinite extent, cylindrical tubes, rectangular slots, cylindrical annuli, and tubes of elliptical and equilaterally triangular shape. The results indicated that the observed variation of flame quenching as a function of quenching geometry may be successfully predicted for a range of pressures and for rich as well as lean propane-air flames.

Report presenting an investigation of an experimental 15-stage axial-flow compressor to determine the effect of inlet-annulus area blockage on disrupting the rotating stall and altering the overall performance and stall characteristics of the compressor. It is part of a general investigation to determine how to alleviate the general problems of blade vibration and poor off-design performance associated with compressor rotating stall.

Report presenting an investigation at subsonic, transonic, and supersonic speeds of the effect of lip shape on drag, pressure recovery, and mass flow of a nose-inlet air-induction system. Four lips of varying degrees of bluntness were tested on a fuselage model at a range of Mach numbers and angles of attack. Results regarding pressure recovery, net drag, and analysis are provided.

Memorandum presenting an investigation of the effect of the addition of approximately 6 percent nickel, cobalt, or platinum on some properties of molybdenum disilicide. These additions resulted in appreciably lowering the modulus-of-rupture strength from that of unalloyed molybdenum disilicide. Results regarding density and particle-size analysis, chemical analysis of bars, metallographic and x-ray analysis, density and resistivity, modulus-of-rupture strengths, thermal shock tests, and oxidation resistance are provided.

Report presenting an investigation of a silicone-diester blend (SD-17) in various bench studies and in a turbopropeller engine to determine its suitability as a lubricant for aircraft engines. The performance of the fluid was satisfactory during more than 17 hours of operation in a T-38 engine with power levels from 1745 to 2400 horsepower. Results regarding bench studies and turbopropeller engine study are provided.

Note describing the preparation and evaluation of 25 binary and ternary alloys with liquidus temperatures in the range of 2000 to 2500 degrees Fahrenheit as part of an investigation of potential brazing alloys for molybdenum for use at elevated temperatures. Three commercial alloys were also investigated.

Report presenting an evaluation of an aircraft radio altimeter for use in a method of airspeed calibration differing from the radar-photothedolite method of a previous study only in that the geometric altitude is obtained from an aircraft radio altimeter. The accuracy and airspeed calibrations for the two methods were found to be similar.

Memorandum presenting a rocket-propelled model of a representative 35 degree sweptback wing airplane design at high subsonic Mach numbers to investigate the possibility of the existence of coupled longitudinal and lateral motions. The data indicate the existence of sustained longitudinal motions of appreciable amplitude forced by lateral oscillations. The longitudinal motions had twice the frequency of the lateral oscillations and are shown to be the result of aerodynamic moments due to sideslip and inertial cross coupling.

"A considerable weight reduction in the turbine wheel of an aircraft gas turbine is attained through the use of high-aspect-ratio rotor blading. An experimental investigation was made to compare the performance of a turbine of conservative aerodynamic design having shrouded rotor blades with an aspect ratio of 4.48 with that obtained from both a shrouded and an unshrouded rotor design with aspect ratio of 2.24. The use of high-aspect-ratio rotor blades had a negligible effect on the turbine efficiency" (p. 1).

Report presenting experiments conducted as part of the general rocket-research program to determine the heat-transfer and fluid-friction characteristics of white fuming nitric acid over a specific set of conditions.

Report presenting an investigation of a conservatively designed experimental cold-air turbine with and without a shroud band on the rotor blades. The tip of the rotor blade was oriented toward the tangential direction so that the adverse effect of blade-tip scraping would not be appreciable. The efficiency for the unshrouded-rotor configuration was about one point higher than for the shrouded rotor.

"The performance of liquid fluorine and liquid ammonia as a propellant combination was evaluated in 1000-pound-thrust rocket engines operated at a chamber pressure of 600 pounds per square inch absolute. Values of specific impulse, characteristic velocity, thrust coefficient, and heat rejection were obtained as functions of propellant mixture ratio for each of four injectors: a triplet, a showerhead, and two like-on-like types" (p. 1).