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  Partner: UNT Libraries Government Documents Department
 Serial/Series Title: NACA Restricted Bulletin
 Collection: Technical Report Archive and Image Library
Pressure lag in tubing used in flight research
Tests described in this report were undertaken to obtain a quantitative measure of the pressure lag in typical pressure-tubing systems used by the Ames Aeronautical Laboratory in flight research investigations. Lag measurements were made with both single-direction and oscillating pressure changes. Single-direction pressure changes were investigated to determine if the lag in orifice-pressure lines and in the research airspeed and altitude measuring systems of pursuit-type airplane undergoing flight tests was sufficient to cause an appreciable error in the record of a sudden pressure change. Oscillating pressure changes were investigated with particular reference to the accuracy of pressure peaks in pressure-distribution measurements during the time of buffeting conditions as found in stalls. (author). digital.library.unt.edu/ark:/67531/metadc65399/
Maximum lift coefficients of airplanes based on sum of wing and tail areas
No Description digital.library.unt.edu/ark:/67531/metadc60890/
Notes on the skipping of seaplanes
No Description digital.library.unt.edu/ark:/67531/metadc60899/
Effect of powered propellers on the aerodynamic characteristics and the porpoising stability of a dynamic model of a long-range flying boat
No Description digital.library.unt.edu/ark:/67531/metadc60893/
Preliminary investigation of the relation of the compressive strength of sheet-stiffener panels to the diameter of rivet used for attaching stiffeners to sheet
No Description digital.library.unt.edu/ark:/67531/metadc60963/
Comparison of structural efficiencies of diagonal-tension webs and truss webs of 24S-T aluminum alloy
No Description digital.library.unt.edu/ark:/67531/metadc60972/
Effect of variation in diameter and pitch of rivets on compressive strength of panels with Z-section stiffeners I : panels with close stiffener spacing that fail by local buckling
No Description digital.library.unt.edu/ark:/67531/metadc60974/
Critical compressive stress for curved sheet supported along all edges and elastically restrained against rotation along the unloaded edges
No Description digital.library.unt.edu/ark:/67531/metadc60915/
Some notes on the determination of the stick-fixed neutral point from wind-tunnel data
No Description digital.library.unt.edu/ark:/67531/metadc60941/
The landing stability of a powered dynamic model of a flying boat with a 30 degree v-step and with two depths of transverse step
No Description digital.library.unt.edu/ark:/67531/metadc60902/
Preliminary tests to determine the dynamic stability characteristics of various hydrofoil systems for seaplanes and surface boats
No Description digital.library.unt.edu/ark:/67531/metadc60900/
Some strength tests of stiffened curved sheets loaded in shear
No Description digital.library.unt.edu/ark:/67531/metadc60921/
Early detection of cracks resulting from fatigue stressing
No Description digital.library.unt.edu/ark:/67531/metadc62272/
A method for the determination of aromatics in hydrocarbon mixtures
No Description digital.library.unt.edu/ark:/67531/metadc62271/
Proposal for a propeller side-force factor
No Description digital.library.unt.edu/ark:/67531/metadc62133/
Tests of beams having webs with large circular lightening holes
No Description digital.library.unt.edu/ark:/67531/metadc62210/
Effects of fuel-vapor loss on knock-limited performance and inspection properties of aviation fuels
No Description digital.library.unt.edu/ark:/67531/metadc62314/
The Knock-Limited Performance of Fuel Blends Containing Spiropentane, Methylenecyclobutane, Di-Tert-Butyl Ether, Methyl Tert-Butyl Ether, and Triptane
Tests show that at inlet-air temperatures of 250 deg F and 100 deg F the knock-limited performance of the base fuel of blends, leaded with 4 ml TEL per gallon and containing 20 percent spiropentane, was reduced at fuel/air ratios below 0.085. The 20 percent methylenecyclobutane reduced the knock-limited power of the base fuel at fuel/air ratios below 0.112. Di-tert-butyl ether, methyl-tert-butyl ether, and triptane increased the knock-limited power of the base fuel at all fuel/air ratios and at both temperatures. digital.library.unt.edu/ark:/67531/metadc62316/
The effect of oil consumption and piston cooling on knock-limited aircraft-engine performance
No Description digital.library.unt.edu/ark:/67531/metadc62324/
Effects of compressibility and large angles of yaw on pressure indicated by a total-pressure tube
No Description digital.library.unt.edu/ark:/67531/metadc62407/
Determination of iron contamination of used lubricating oil for use in measuring rates of wear in aircraft engines
No Description digital.library.unt.edu/ark:/67531/metadc62322/
An electronic indicator for angular velocity and acceleration
No Description digital.library.unt.edu/ark:/67531/metadc62416/
Dilution of exhaust-gas samples from a multicylinder engine equipped with an exhaust-gas collector
No Description digital.library.unt.edu/ark:/67531/metadc62393/
Flight tests of a glider model towed by twin parallel towlines
No Description digital.library.unt.edu/ark:/67531/metadc62655/
End-zone water injection as a means of suppressing knock in a spark-ignition engine
No Description digital.library.unt.edu/ark:/67531/metadc62053/
Tests of 10 inch 24S-T aluminum-alloy shear panels with 1-1/2 inch holes II : panels having holes with notched edges
No Description digital.library.unt.edu/ark:/67531/metadc62248/
The Effect of Artificial Aging on the Tensile Properties of Alclad 24S-T and 24S-T Aluminum Alloy
An experimental study was made to determine the effect of artificial aging on the tensile properties of alclad 24S-T and 24S-T aluminum-alloy sheet material. The results of the tests show that certain combinations of aging time and temperature cause a marked increase in the yield strength and a small increase in the ultimate strength; these increases are accompanied by a very large decrease in elongation. A curve is presented that shows the maximum yield strengths that can be obtained by aging this material at various combinations of time and temperature. The higher values of yield stress are obtained in material aged at relatively longer times and lower temperatures. digital.library.unt.edu/ark:/67531/metadc62249/
Static-pressure error of an airspeed installation on an airplane in high-speed dives and pullouts
No Description digital.library.unt.edu/ark:/67531/metadc62411/
The NACA balanced-diaphragm dynamometer-torque indicator
No Description digital.library.unt.edu/ark:/67531/metadc62418/
Tests of 10-inch 24S-T aluminum-alloy shear panels with 1-1/2-inch holes I
No Description digital.library.unt.edu/ark:/67531/metadc62245/
The longitudinal shear strength required in double-angle columns of 24S-T aluminum alloy
No Description digital.library.unt.edu/ark:/67531/metadc62242/
Lead susceptibility of several fuels as determined in an air-cooled aircraft-engine cylinder
No Description digital.library.unt.edu/ark:/67531/metadc62308/
Computation of the mean tangential velocity of the air leaving the blade tips of a centrifugal supercharger
No Description digital.library.unt.edu/ark:/67531/metadc62510/
Investigation of methods of supporting single-thickness specimens in a fixture for determination of compressive stress-strain curves
No Description digital.library.unt.edu/ark:/67531/metadc62425/
A preignition indicator for aircraft engines
No Description digital.library.unt.edu/ark:/67531/metadc62420/
Spinning of large airplanes
No Description digital.library.unt.edu/ark:/67531/metadc62551/
Use of stagnation temperature in calculating rate of heat transfer in aircraft heat exchangers
No Description digital.library.unt.edu/ark:/67531/metadc62447/
Heat-capacity lag in turbine-working fluids
No Description digital.library.unt.edu/ark:/67531/metadc62389/
Material properties of two types of plastic-bonded glass cloth
No Description digital.library.unt.edu/ark:/67531/metadc62383/
Effect of varying percentages of exhaust gas on engine performance
No Description digital.library.unt.edu/ark:/67531/metadc62385/
The knock-limited performance of several fuels blended with S-2 reference fuel
No Description digital.library.unt.edu/ark:/67531/metadc62382/
The effect of angle of bend between plate elements on the local instability of formed Z-sections
No Description digital.library.unt.edu/ark:/67531/metadc62250/
Determination of desirable lengths of Z- and channel-section columns for local-instability tests
No Description digital.library.unt.edu/ark:/67531/metadc62253/
Relative effects of cylinder-head and inlet-mixture temperatures upon knock limits of fuels
No Description digital.library.unt.edu/ark:/67531/metadc62378/
Maximum rates of control motion obtained from ground tests
No Description digital.library.unt.edu/ark:/67531/metadc61507/
Some effects of propeller operation on the distribution of the load on the vertical tail surface of a typical pursuit airplane
No Description digital.library.unt.edu/ark:/67531/metadc61504/
Effect of lateral shift of center of gravity on rudder deflection required for trim
No Description digital.library.unt.edu/ark:/67531/metadc61143/
A positive-replica technique for examining finished metal surfaces and its application to aircraft engine cylinders
No Description digital.library.unt.edu/ark:/67531/metadc61913/
Tables and charts for the evaluation of profile drag from wake surveys at high subsonic speeds
No Description digital.library.unt.edu/ark:/67531/metadc61260/
Use of Internal Coolant as a Means of Permitting Increase in Engine Take-Off Power
Engine tests, together with estimates made at Langley Memorial Aeronautical Laboratory, indicate that a 25-percent increase in take-off power can be obtained with present-day aircraft engines without increasing either the knock limit of the fuel or the external cooling requirements of the engine. This increase in power with present fuels and present external cooling is made possible through the use of an internal coolant inducted through the inlet manifold. Estimates on aircraft indicate that this 25-percent increase in power will permit an approximate usable increase of 8.5 percent in the take-off load of existing military airplanes. This increase in load is equivalent to an increase in the weight of gasoline normally carried of between 30 and 65 percent. digital.library.unt.edu/ark:/67531/metadc61928/
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