Memorandum presenting a theoretical investigation to determine the reasons for poor airplane response to longitudinal control. Some effects of airplane configuration on the response, primarily for short time periods, were also determined. Results regarding a comparison of three airplanes, the effect of changes on airplane B, and the effect of changes on airplane C are provided.

From Introduction: "A theoretical investigation was conducted in order to determine what effect the differences in aerodynamic characteristics would have on the short-time response to elevator control of this type of airplane as compared with the responses of a conventional airplane, without regard to any possible psychological influences. The results of this investigation are presented in this paper."

From Summary: "Calculated velocity and temperature distributions, as well as relations among Nusselt number, Reynolds number, and friction factor, are presented. The effect of variation of fluid properties across the tube on the Nusselt number and friction factor correlations can be eliminated by evaluating the properties at a reference temperature which is a function of both the wall temperature and the ratio of wall-to-bulk temperatures."

The performance characteristics of the 19B-8 and 19XB-1 turbojet engines and the windmilling-drag characteristics of the 19B-6 engine were determined in the Cleveland altitude wind tunnel. The investigations were conducted on the 19B-8 engine at simulated altitudes from 5000 to 25,000 feet with various free-stream ram-pressure ratios and on the 19XB--1 engine at simulated altitudes from 5000 to 30,000 feet with approximately static free-stream conditions.

This report contains the results of the wind tunnel investigation of the pressure distribution on the flying mock-up of the Consolidated Vultee XP-92 airplane. Data are presented for the pressure distribution over the wing, vertical tail and the fuselage, and for the pressure loss and rate of flow through the ducted fuselage. Data are also presented for the calibration of two airspeed indicators, and for the calibration of angle-of-attack and sideslip-angle indicator vanes.

Report presenting an experimental investigation to determine the performance of seven full-size ejector configurations over a range of secondary to primary air-flow ratios, primary total- to ambient-pressure ratios, and primary gas temperatures. Results regarding primary-nozzle performance, ejector performance, typical ejector characteristics, effect of operating temperatures on ejector flow characteristics, and effect of geometry on ejector performance are provided.

The performance of a 13-stage development compressor for the J40-WE-24 engine has been determined at equivalent speeds from 30 to 112 percent of design. The design total-pressure ratio of 6.0 and the design weight flow of 164 pounds per second were not attained, An analysis was conducted to determine the reasons for the poor performance at the design and over-design speed. The analysis indicated that most of the difficulty could be attributed to the fact that the first stage was overcompromised to favor part-speed performance,.

Report discussing an investigation into chord-extension controls, conventional ailerons, and spoilers on a 45 degree swept-back wing of aspect ratio 4.5 and taper ratio 0.5. Measurements of the lift, drag, pitching moments, rolling moments, and rates of roll produced by the various controls are described. The results on a semispan model and a full-span model are described.

Quarterly report discussing the progress made with various projects at Argonne National Laboratory during the period from January to March 1948.

From abstract: "The mass spectra of the α-amino acids have been obtained in a mass spectrometer equipped with a heated crucible ion source. Correlations of these data have been made with the molecular formulae of the ion fragments, and mechanisms leading to these fragments are proposed. Comparisons of these data have been made with the mass spectra of the ethyl esters of the amino acids and with other carboxylic acids and their esters."

"At the request of the Army Air Corps, an investigation of the pressure distribution over PW-9 wing models was conducted in the atmospheric wind tunnel of the National Advisory Committee for Aeronautics. The primary purpose of these tests was to obtain wind-tunnel data on the load distribution on the cellule to be correlated with similar information obtained in flight tests, both to be used for design purposes. Because of the importance of the conditions beyond the stall as affecting the control and stability, this investigation was extended through 90 degree angle of attack" (p. 335).

"The static lateral, directional, and longitudinal stability characteristics of a 0.06-scale model of the Martin B-61A missile (Matador) were investigated in the Langley 8-foot transonic tunnel at Mach numbers from 0.80 t o 1.12. Six-component force and moment data were obtained from strain-gage measurements. The characteristics of a spoiler and of wing-tip end plates were also investigated. The Reynolds number of the tests based on the mean aerodynamic chord of the wing was approximately 1.6 X 10(exp 6)" (p. 1).

Report presenting the effects of flame-immersed blades on combustion stability and efficiency, which were determined at various combustor-inlet conditions by use of several geometric blade arrangements, two fuels, two fuel-injection systems, and two blade temperatures. Specific combustor configurations with flame-immersed blades showed marked improvement in stability and efficiency. The operational life of the blades was also observed to be excellent.

Discussing the importance to mapping of the Salt-Bluff contacts at King tut Mesa

This report discusses the development of a method for creating leak-proof closures in aluminum sample casings in order to pass a standard bubble-test inspection.

"Strain-gage measurements were taken under operating conditions from blades of various stages of the 19XB axial-flow compressor in an effort to determine the reason for failures in the seventh and tenth stages. First bending-mode vibrations were detected in the first five stages of the compressor caused by each integral multiple of rotor speed from three through ten. Lead-wire failures in the last five stages resulted in incomplete data" (p. 1).

"A low-speed investigation in the Langley propeller-research tunnel of annular air inlets designed to avoid compression shocks and attendant boundary-layer separation on the fuselage ahead of the inlets at transonic flight speeds by maintaining substream flow velocities on the fuselage nose was reported in NACA RM No. L6J04. In the present investigation, one of the original annular inlets was converted by the installation of a canopy and a nose-wheel fairing into a twin side inlet in order to study problems involved in applying such an inlet to a fighter-type airplane. Extensive measurements of pressures on the surface of the model and surveys of the internal flow were conducted at angles of attack of 0 degrees, 3 degrees, and 6 degrees over a wide range of inlet-velocity ratio" (p. 1).

Report discussing an investigation of a delta-wing model with the leading edge swept back 60 degrees. Testing indicated that the gust load is greater than would be predicted by using a slope of the lift curve determined from steady-flow force tests. An aspect-ratio relation was determined for this type of wing with the selected apex angle, but it does not appear to be applicable to other wings with different apex angles.

Calculations indicative of the power loss for 75 in.radius gap splitters are given.

This report presents the results of performance test conducted on a six-cylinder commercial fuel-injection pump that was adjusted to give uniform fuel distribution among the cylinders at a throttle setting of 0.00038 pound per injection and a pump speed of 750 revolutions per minute. The throttle setting and pump speed were then varied through the operating range to determine the uniformity of distribution and regularity of injection.

Introduction: A limited test progress on Alloghany-Ludlum type 347 stainless steel plate which failed the Huey test (ASTN A-262-44T) has been completed.

Abstract: "The possibility of detecting small quantities of uranium with an X-ray spectrometer was investigated. An X-ray spectrograph was modified by substituting a geiger counter for the photographic film. Both primary and secondary methods of excitation were studied. Radiation background of high intensity and variability limits the sensitivity of the present apparatus to 1%. Suggestions are made for increasing the sensitivity of the method."

Report discussing an investigation to determine the low-speed aerodynamic characteristics of a North American FJ-3 airplane with a segmented spoiler-slot-deflector lateral control system installed ahead of convention ailerons and operated as individual units and as combined segments. The longitudinal characteristics of the plane, the spoiler-slot-deflector effectiveness, and spoiler-deflector hinge-moment data are all described.

The solubility constants are presented for He , Kr , Xe , O2 , N2 , and air in H20 . Inter-diffusion constants for gases and the diffusion of gases in water are given.