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 Decade: 1940-1949
 Collection: National Advisory Committee for Aeronautics Collection
A theoretical investigation of the lateral oscillations of an airplane with free rudder with special reference to the effect of friction
No Description digital.library.unt.edu/ark:/67531/metadc279582/
The Measurement of Fuel-Air Ratio by Analysis for the Oxidized Exhaust Gas
An investigation was made to determine a method of measuring fuel-air ratio that could be used for test purposes in flight and for checking conventional equipment in the laboratory. Two single-cylinder test engines equipped with typical commercial engine cylinders were used. The fuel-air ratio of the mixture delivered to the engines was determined by direct measurement of the quantity of air and of fuel supplied and also by analysis of the oxidized exhaust gas and of the normal exhaust gas. Five fuels were used: gasoline that complied with Army-Navy fuel Specification No. AN-VV-F-781 and four mixtures of this gasoline with toluene, benzene, and xylene. The method of determining the fuel-air ratio described in this report involves the measurement of the carbon-dioxide content of the oxidized exhaust gas and the use of graphs for the presented equation. This method is considered useful in aircraft, in the field, or in the laboratory for a range of fuel-air ratios from 0.047 to 0.124. digital.library.unt.edu/ark:/67531/metadc279515/
Single-cylinder oil-control tests of porous chrome plated cylinder barrels for radial air-cooled engines
No Description digital.library.unt.edu/ark:/67531/metadc279560/
The flow of a compressible fluid past a curved surface
No Description digital.library.unt.edu/ark:/67531/metadc279581/
Analysis of wind-tunnel stability and control tests in terms of flying qualities in full-scale airplanes
No Description digital.library.unt.edu/ark:/67531/metadc279513/
Critical combinations of shear and transverse direct stress for an infinitely long flat plate with edges elastically restrained against rotation
No Description digital.library.unt.edu/ark:/67531/metadc279557/
Emergency measures for increasing the range of fighter airplanes
No Description digital.library.unt.edu/ark:/67531/metadc279475/
The knock-limited performance of S reference fuel plus 2 milliliters of triethylthallium per gallon
No Description digital.library.unt.edu/ark:/67531/metadc279453/
Fuel-evaporation loss as determined by the change in the specific gravity of the fuel in an aircraft fuel tank
No Description digital.library.unt.edu/ark:/67531/metadc279479/
Experiments on drag of revolving disks, cylinders and streamline rods at high speeds
No Description digital.library.unt.edu/ark:/67531/metadc279467/
Wall interference in a two-dimensional-flow wind tunnel with consideration of the effect of compressibility
No Description digital.library.unt.edu/ark:/67531/metadc279436/
The effect of altitude on cooling
No Description digital.library.unt.edu/ark:/67531/metadc279422/
Review of flight tests of NACA C and D cowlings on the XP-42 airplane
No Description digital.library.unt.edu/ark:/67531/metadc279477/
A method for studying the hunting oscillations of and airplane with a simple type of automatic control
No Description digital.library.unt.edu/ark:/67531/metadc279458/
A general representation for axial-flow fans and turbines
No Description digital.library.unt.edu/ark:/67531/metadc279615/
An investigation of a thermal ice-prevention system for a C-46 cargo airplane III : description of thermal ice-prevention equipment for wings, empennage, and windshield
No Description digital.library.unt.edu/ark:/67531/metadc279602/
Flight tests of several exhaust-gas-to-air heat exchangers in the B-17F airplane
No Description digital.library.unt.edu/ark:/67531/metadc279674/
Wind-tunnel investigation of the effects of spoilers on the characteristics of a low-drag airfoil equipped with a 0.25-chord slotted flap
No Description digital.library.unt.edu/ark:/67531/metadc279657/
Lifting-surface-theory aspect-ratio corrections to the lift and hinge-moment parameters for full-span elevators on horizontal tail surfaces
A limited number of lifting-surface-theory solutions for wings with chordwise loadings resulting from angle of attack, parabolic-ac camber, and flap deflection are now available. These solutions were studied with the purpose of determining methods of extrapolating the results in such a way that they could be used to determine lifting-surface-theory values of the aspect-ratio corrections to the lift and hinge-moment parameters for both angle-of-attack and flap-deflection-type loading that could be used to predict the characteristics of horizontal tail surfaces from section data with sufficient accuracy for engineering purposes. Such a method was devised for horizontal tail surfaces with full-span elevators. In spite of the fact that the theory involved is rather complex, the method is simple to apply and may be applied without any knowledge of lifting-surface theory. A comparison of experimental finite-span and section value and of the estimated values of the lift and hinge-moment parameters for three horizontal tail surfaces was made to provide an experimental verification of the method suggested. (author). digital.library.unt.edu/ark:/67531/metadc279678/
Design of nozzles for the individual cylinder exhaust jet propulsion system
No Description digital.library.unt.edu/ark:/67531/metadc279672/
Thermodynamic design of double-panel, air-heated windshields for ice prevention
No Description digital.library.unt.edu/ark:/67531/metadc279628/
An experimental investigation of rectangular exhaust-gas ejectors applicable for engine cooling
No Description digital.library.unt.edu/ark:/67531/metadc279654/
Flight studies of the horizontal-tail loads experienced by a fighter airplane in abrupt maneuvers
No Description digital.library.unt.edu/ark:/67531/metadc279611/
NACA Mach number indicator for use in high-speed tunnels
No Description digital.library.unt.edu/ark:/67531/metadc279639/
An investigation of a thermal ice-prevention system for a C-46 cargo airplane VI : dry-air performance of thermal system at several twin- and single-engine operating conditions at various altitudes
No Description digital.library.unt.edu/ark:/67531/metadc279617/
An investigation of a thermal ice-prevention system for a C-46 cargo airplane V : effect of thermal system on airplane cruise performance
No Description digital.library.unt.edu/ark:/67531/metadc279663/
On the flow of a compressible fluid by the hodography method I : unification and extension of present-day results
No Description digital.library.unt.edu/ark:/67531/metadc279666/
Air-consumption parameters for automatic mixture control of aircraft engines
No Description digital.library.unt.edu/ark:/67531/metadc279682/
Profile-drag coefficients of conventional and low-drag airfoils as obtained in flight
No Description digital.library.unt.edu/ark:/67531/metadc279640/
A method for determining the rate of heat transfer from a wing or streamline body
No Description digital.library.unt.edu/ark:/67531/metadc279474/
A method of estimating the knock rating of hydrocarbon fuel blend
The usefulness of the knock ratings of pure hydrocarbon compounds would be increased if some reliable method of calculating the knock ratings of fuel blends was known. The purpose of this study was to investigate the possibility of developing a method of predicting the knock ratings of fuel blends. digital.library.unt.edu/ark:/67531/metadc279419/
Compressible potential flow with circulation about a circular cylinder
No Description digital.library.unt.edu/ark:/67531/metadc279487/
Compressibility and heating effects on pressure loss and cooling of a baffled cylinder barrel
No Description digital.library.unt.edu/ark:/67531/metadc279452/
Nitrided-steel piston rings for engines of high specific power
No Description digital.library.unt.edu/ark:/67531/metadc279433/
Comparison of Vee-Type and Conventional Tail Surfaces in Combination with Fuselage and Wing in the Variable-Density Tunnel
The pitching and the yawing moments of a vee-type and a conventional type of tail surface were measured. The tests were made in the presence of a fuselage and a wing-fuselage combination in such a way as to determine the moments contributed by the tail surfaces. The results showed that the vee-type tail tested, with a dihedral angle of 35.3 deg, was about 71 percent as effective in pitch as the conventional tail and had a yawing-moment to pitching-moment ratio of 0.3. The conventional tail, the panels of which were all congruent to those of the vee-type tail, had a yawing-moment to pitching-moment ratio of 0.48. These ratios are in fair agreement with values calculated by methods shown in this and previous reports. The values of the measured moments were reduced from 15 to 25 percent of the calculated value by fuselage interference. digital.library.unt.edu/ark:/67531/metadc279435/
An investigation of a thermal ice-prevention system for a C-46 cargo airplane II : the design, construction, and preliminary tests of the exhaust-air heat exchanger
No Description digital.library.unt.edu/ark:/67531/metadc279494/
On the flow of a compressible fluid by the hodography method II : fundamental set of particular flow solutions of the Chaplygin differential equation
No Description digital.library.unt.edu/ark:/67531/metadc279417/
Wind-tunnel procedure for determination of critical stability and control characteristics of airplanes
No Description digital.library.unt.edu/ark:/67531/metadc279429/
Correlation of exhaust-valve temperatures with engine operating conditions and valve design
No Description digital.library.unt.edu/ark:/67531/metadc279466/
The propeller and cooling-air-flow characteristics of a twin-engine airplane model equipped with NACA D(sub S)-type cowlings and with propellers of NACA 16-series airfoil sections
No Description digital.library.unt.edu/ark:/67531/metadc279496/
The calculation of span LCAD distributions of swept-back wings
Span load distributions of swept-back wings have been calculated. The method used was to replace the wing with a bound vortex at the quarter-chord line and to calculate the downwash due to the system of bound and trailing vortices to conform at the three-quarter-chord line to the slope of the flat-plate wing surface. Results are given for constant-chord and 5:1 tapered plan forms, for sweep-back angles of 0 degrees, 30 degrees, and 45 degrees, and for aspect ratios of 3, 6, and 9. Some comments on the stalling of swept-back wings are included. digital.library.unt.edu/ark:/67531/metadc279443/
A method for calculating heat transfer in the laminar flow region of bodies
No Description digital.library.unt.edu/ark:/67531/metadc279431/
Calculations of economy of 18-cylinder radial aircraft engine with exhaust-gas turbine geared to the crankshaft at cruising speed
No Description digital.library.unt.edu/ark:/67531/metadc279432/
NACA Investigation of a Jet-Propulsion System Applicable to Flight
Following a brief history of the NACA investigation of jet-propulsion, a discussion is given of the general investigation and analyses leading to the construction of the jet-propulsion ground-test mock-up. The results of burning experiments and of test measurements designed to allow quantitative flight-performance predictions of the system are presented and correlated with calculations. These calculations are then used to determine the performance of the system on the ground and in the air at various speeds and altitudes under various burning conditions. The application of the system to an experimental airplane is described and some performance predictions for this airplane are made. It was found that the main fire could be restricted to an intense, small, and short annular blue flame burning steadily and under control in the intended combustion space. With these readily obtainable combustion conditions, the combustion chamber the nozzle walls and the surrounding structure could be maintained at normal temperatures. The system investigated was found to be capable of burning one-half the intake air up the fuel rates of 3 pounds per second. Calculations were shown to agree well with experiment. It was concluded that the basic features of the jet-propulsion system investigation in the ground-test mock-up were sufficiently developed to be considered applicable to flight installation. Calculations indicated that an airplane utilizing this jet-propulsion system would have unusual capabilities in the high-speed range above the speeds of conventional aircraft and would, in addition, have moderately long cruising ranges if only the engine were used. digital.library.unt.edu/ark:/67531/metadc279418/
A Concise Theoretical Method for Profile-Drag Calculation; Advance Report
In this report a method is presented for the calculation of the profile drag of airfoil sections. The method requlres only a knowledge of the theoretical velocity distribution and can be applied readily once this dlstribution is ascertained. Comparison of calculated and experimental drag characteristics for several airfoils shows a satisfactory agreement. Sample calculatlons are included. digital.library.unt.edu/ark:/67531/metadc279600/
Spin tests of two models of a low-wing monoplane to investigate scale effect in the model test range
No Description digital.library.unt.edu/ark:/67531/metadc279675/
Determination of general relations for the behavior of turbulent boundary layers
No Description digital.library.unt.edu/ark:/67531/metadc279609/
The development and application of high-critical-speed nose inlets
No Description digital.library.unt.edu/ark:/67531/metadc279653/
Analysis of heat and compressibility effects in internal flow systems and high-speed tests of a ram-jet system
No Description digital.library.unt.edu/ark:/67531/metadc279610/
Ditching tests with 1/10-size model of the Army A-20A airplane I : calm-water tests in NACA tank no.2
No Description digital.library.unt.edu/ark:/67531/metadc279645/
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