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  Partner: UNT Libraries Government Documents Department
 Year: 1944
 Serial/Series Title: NACA Restricted Bulletin
 Collection: Technical Report Archive and Image Library
An automatically variable control linkage and its effect on the lateral-control characteristics of a high-speed fighter airplane
No Description digital.library.unt.edu/ark:/67531/metadc61488/
Calculation of stick forces for an elevator with a spring tab
No Description digital.library.unt.edu/ark:/67531/metadc61595/
Calculations of intake-air cooling resulting from water injection and of water recovery from exhaust gas
No Description digital.library.unt.edu/ark:/67531/metadc61929/
Comparative tests of the strength and tightness of commercial flush rivets of one type and NACA flush rivets in machine-countersunk and counterpunched joints
No Description digital.library.unt.edu/ark:/67531/metadc61746/
Cylinder-head cooling by means of a shield in the exhaust passage
No Description digital.library.unt.edu/ark:/67531/metadc61930/
Determination of desirable lengths of Z- and channel-section columns for local-instability tests
No Description digital.library.unt.edu/ark:/67531/metadc62253/
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/
Early detection of cracks resulting from fatigue stressing
No Description digital.library.unt.edu/ark:/67531/metadc62272/
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/
Effect of Changes in Aileron Rigging on the Stick Forces of a High-Speed Fighter Airplane
The effects of changes in aileron rigging between 2 deg up and 2 deg down on the stick forces were determined from wind-tunnel data for a finite-span wing model. These effects were investigated for ailerons deflecting equally in both directions and linearly with stick deflection. Data were analyzed for a Frise, a sealed internally balanced, and a beveled-trailing-edge aileron. The results of the analysis showed that only ailerons having linear hinge-moment characteristics are unaffected by changes in rigging and indicated that ailerons having decidedly nonlinear hinge-moment-coefficient curves, particularly for deflections near 0 deg, are very sensitive to changes in rigging. digital.library.unt.edu/ark:/67531/metadc61638/
Effect of inlet-air temperature and cylinder displacement on charge temperature of internal combustion engines
No Description digital.library.unt.edu/ark:/67531/metadc61864/
Effect of lateral shift of center of gravity on rudder deflection required for trim
No Description digital.library.unt.edu/ark:/67531/metadc61143/
The effect of oil consumption and piston cooling on knock-limited aircraft-engine performance
No Description digital.library.unt.edu/ark:/67531/metadc62324/
An electronic indicator for angular velocity and acceleration
No Description digital.library.unt.edu/ark:/67531/metadc62416/
End-zone water injection as a means of suppressing knock in a spark-ignition engine
No Description digital.library.unt.edu/ark:/67531/metadc62053/
An estimation of the internal-cooling requirements of an aircraft-engine cylinder when using oxygen boost
No Description digital.library.unt.edu/ark:/67531/metadc61956/
Flight investigation at high Mach numbers of several methods of measuring static pressure on an airplane wing
No Description digital.library.unt.edu/ark:/67531/metadc61475/
Heat-capacity lag in turbine-working fluids
No Description digital.library.unt.edu/ark:/67531/metadc62389/
An investigation of the characteristics of a propeller alcohol feed ring
No Description digital.library.unt.edu/ark:/67531/metadc61808/
The knock-limited performance of several fuels blended with S-2 reference fuel
No Description digital.library.unt.edu/ark:/67531/metadc62382/
Landing characteristics of a model of a flying boat with the depth of step reduced to zero by means of a retractable planing flap
No Description digital.library.unt.edu/ark:/67531/metadc61760/
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/
Material properties of two types of plastic-bonded glass cloth
No Description digital.library.unt.edu/ark:/67531/metadc62383/
Maximum lift coefficients of airplanes based on sum of wing and tail areas
No Description digital.library.unt.edu/ark:/67531/metadc60890/
Maximum rates of control motion obtained from ground tests
No Description digital.library.unt.edu/ark:/67531/metadc61507/
Method of mounting cylinder blocks of in-line engines on CUE crankcases
No Description digital.library.unt.edu/ark:/67531/metadc61908/
The NACA balanced-diaphragm dynamometer-torque indicator
No Description digital.library.unt.edu/ark:/67531/metadc62418/
Notes on unusual V-G records from transport airplanes
No Description digital.library.unt.edu/ark:/67531/metadc61139/
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/
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/
Preliminary tank experiments with a hydrofoil on a planing-tail seaplane hull
No Description digital.library.unt.edu/ark:/67531/metadc61786/
Relative effects of cylinder-head and inlet-mixture temperatures upon knock limits of fuels
No Description digital.library.unt.edu/ark:/67531/metadc62378/
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/
Some Notes on the Determination of the Stick-Free Neutral Point from Wind-Tunnel Data
Two graphical methods are presented for determining the stick-free neutral point, and they are extensions of the methods commonly used to determine the stick-free neutral point. A mathematical formula for computing the stick-free neutral point is also given. These methods may be applied to determine approximately the increase in tail size necessary to shift the neutral point (stick fixed or free) to any desired location on an airplane having inadequate longitudinal stability. digital.library.unt.edu/ark:/67531/metadc61013/
Some strength tests of stiffened curved sheets loaded in shear
No Description digital.library.unt.edu/ark:/67531/metadc60921/
Spinning of large airplanes
No Description digital.library.unt.edu/ark:/67531/metadc62551/
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/
Tests of beams having webs with large circular lightening holes
No Description digital.library.unt.edu/ark:/67531/metadc62210/
Tests of hydraulically expanded rivets
No Description digital.library.unt.edu/ark:/67531/metadc61749/
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/
Use of water injection to decrease gasoline consumption in an aircraft engine cruising at high power
No Description digital.library.unt.edu/ark:/67531/metadc61875/
XC-35 gust research project analysis of gust measurements
No Description digital.library.unt.edu/ark:/67531/metadc61106/