You limited your search to:

  Partner: UNT Libraries Government Documents Department
 Serial/Series Title: NACA Restricted Bulletin
 Collection: Technical Report Archive and Image Library
An electronic indicator for angular velocity and acceleration
No Description digital.library.unt.edu/ark:/67531/metadc62416/
Emergency measures for increasing the range of fighter airplanes
No Description digital.library.unt.edu/ark:/67531/metadc279475/
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/
Flight tests of a glider model towed by twin parallel towlines
No Description digital.library.unt.edu/ark:/67531/metadc62655/
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/
Heat-capacity lag in turbine-working fluids
No Description digital.library.unt.edu/ark:/67531/metadc62389/
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/
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 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 knock-limited performance of S reference fuel plus 2 milliliters of triethylthallium per gallon
No Description digital.library.unt.edu/ark:/67531/metadc279453/
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/
Lead susceptibility of several fuels as determined in an air-cooled aircraft-engine cylinder
No Description digital.library.unt.edu/ark:/67531/metadc62308/
The longitudinal shear strength required in double-angle columns of 24S-T aluminum alloy
No Description digital.library.unt.edu/ark:/67531/metadc62242/
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/
A method for the determination of aromatics in hydrocarbon mixtures
No Description digital.library.unt.edu/ark:/67531/metadc62271/
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/
NACA procedure for flight tests of aileron characteristics of airplanes
No Description digital.library.unt.edu/ark:/67531/metadc61631/
Notes on the skipping of seaplanes
No Description digital.library.unt.edu/ark:/67531/metadc60899/
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/
A preignition indicator for aircraft engines
No Description digital.library.unt.edu/ark:/67531/metadc62420/
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/
A preliminary study of machine-countersunk flush rivets subjected to a combined static and alternating shear load
No Description digital.library.unt.edu/ark:/67531/metadc61745/
Preliminary tank experiments with a hydrofoil on a planing-tail seaplane hull
No Description digital.library.unt.edu/ark:/67531/metadc61786/
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/
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/
Proposal for a propeller side-force factor
No Description digital.library.unt.edu/ark:/67531/metadc62133/
Relative effects of cylinder-head and inlet-mixture temperatures upon knock limits of fuels
No Description digital.library.unt.edu/ark:/67531/metadc62378/
Resume of hinge-moment data for unshielded horn- balanced control surfaces
No Description digital.library.unt.edu/ark:/67531/metadc61491/
Shear tests on DuPont explosive rivets with the countersunk head milled flush after expansion
No Description digital.library.unt.edu/ark:/67531/metadc61753/
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-fixed neutral point from wind-tunnel data
No Description digital.library.unt.edu/ark:/67531/metadc60941/
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/
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/
A study of the effects of radii of gyration and altitude on aileron effectiveness at high speed
No Description digital.library.unt.edu/ark:/67531/metadc61620/
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/
Test data on the shear strength of joints assembled with round-head and brazier-head rivets
No Description digital.library.unt.edu/ark:/67531/metadc61850/
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/
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/