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Charts for the Computation of Equilibrium Composition of Chemical Reactions in the Carbon-Hydrogen-Nitrogen System at Temperatures from 2000 to 5000 Degrees K

Description: Charts are provided for the estimation and progressive adjustment of two independent variables on which the calculations are based. Additional charts are provided for the graphical calculation of the composition.
Date: July 1948
Creator: Huff, Vearl N. & Calvert, Clyde S.
Partner: UNT Libraries Government Documents Department

Preliminary Survey of the Aircraft Fire Problem

Description: Memorandum presenting a review of information relating to aircraft fires to determine what new or further research might lead to a substantial reduction of the aircraft fire hazard in flight and following crashes. An examination of fuels, lubricants, and hydraulic fluids as inflammable liquids is presented, together with possible sources of ignition under the general categories of hot surfaces, electric sparks and arcs, flames, and hot gases.
Date: May 21, 1948
Creator: Cleveland Laboratory Aircraft Fire Research Panel
Partner: UNT Libraries Government Documents Department

Preliminary Study of Use of Nonstrategic Metals for and Application of Cooling to Blades of Turbine of J35 Turbojet Engine

Description: Memorandum presenting the modifications to the J35 engine that are necessitated with the use of non-strategic materials. Two proposals for cooling the rotor disk and blades are: finned hollow blades that are air cooled and blades with circular passages for liquid cooling in which the fuel could be used as the coolant.
Date: November 17, 1948
Creator: Turbine Cooling Research Branch
Partner: UNT Libraries Government Documents Department

The Method of Characteristics for the Determination of Supersonic Flow Over Bodies of Revolution at Small Angles of Attack

Description: Note presenting the use of the method of characteristics for the determination of the supersonic-flow properties around bodies of revolution at a small angle of attack. The system developed considers the effect of the variation of entropy due to the curved shock and determines a flow that exactly satisfies the boundary conditions in the limits of the simplifications assumed.
Date: February 1949
Creator: Ferri, Antonio
Partner: UNT Libraries Government Documents Department

A New Method of Analyzing Extreme-Value Data

Description: Note presenting a method for analyzing extreme-value data which may arise in a wide variety of applications. Discussion of the method is preceded by the necessary statistical theory which also furnishes a basis for evaluating the new method in relation to existing ones. Several appendices are also included for mathematical developments not included in the text.
Date: January 1954
Creator: Lieblein, Julius
Partner: UNT Libraries Government Documents Department

On the Use of a Damped Sine-Wave Elevator Motion for Computing the Design Maneuvering Horizontal-Tail Load

Description: Note presenting a damped sine-wave elevator motion used as a basis for computing the design maneuvering load on the horizontal tail. The results indicated that the maneuvering tail-load variation computed by operational methods with the assumed damped sine-wave elevator motion agreed closely with the loads computed by a method currently used by the US Air Force.
Date: January 1953
Creator: Sadoff, Melvin
Partner: UNT Libraries Government Documents Department

Preliminary Investigation of a Submerged Inlet and a Nose Inlet in the Transonic Flight Range With Free-Fall Models

Description: Memorandum presenting an NACA submerged inlet and an NACA series I nose inlet installed in bodies of 12.4 fineness ratio to determine the drag and pressure-recovery characteristics of each body-inlet configuration. The tests were conducted with large-scale free-fall models released at an altitude of 40,000 feet, for mass-flow ratios of about 0.4 and 0.7 over a Mach number range of about 0.70 to 1.10. Results regarding drag and ram-recovery ratios are provided.
Date: June 18, 1951
Creator: Selna, James
Partner: UNT Libraries Government Documents Department

Preliminary Investigation of Effects of Alpha-Particle Bombardment on the Creep Rate of Aluminum

Description: Memorandum presenting a preliminary investigation to determine the effects of alpha-particle bombardment on the creep rate of aluminum wire at 400 degrees Fahrenheit. The alpha radiation from an 85-millicurie polonium source appeared to decrease slightly the creep rate of the aluminum.
Date: July 3, 1947
Creator: Kittel, J. Howard
Partner: UNT Libraries Government Documents Department

Preliminary Investigation of a Variable Mass-Flow Supersonic Nose Inlet

Description: Memorandum presenting a method for varying the mass flow of supersonic inlets with a circular cross section and a central body. The method consists of changing the size of the entering stream tube by means of an inflatable boot on the surface of the central body.
Date: December 13, 1949
Creator: Hayes, Clyde
Partner: UNT Libraries Government Documents Department

Preliminary Wind-Tunnel Investigation at Low Speed of Stability and Control Characteristics of Swept Back Wings

Description: Note presenting tests conducted on untapered constant-span wings of 0, 30, 45, and 60 degrees sweepback. The purpose of the tests was to investigate the effect of sweepback on stability and control characteristics. The data showed large changes in longitudinal stability at moderate lift coefficients for the 45 and 60 degree sweptback wings.
Date: April 1946
Creator: Letko, William & Goodman, Alex
Partner: UNT Libraries Government Documents Department

Principle and Application of Complementary Energy Method for Thin Homogeneous and Sandwich Plates and Shells With Finite Deflections

Description: Note presenting the principle of complementary energy in the nonlinear elasticity theory, which is shown to be derivable from the principle of potential energy by a Legendre type of transformation. The expression of the complementary energy is derived for homogeneous and sandwich plates and shells with large deflections. The stress-strain relations are derived for homogeneous shells, sandwich plates, and sandwich shells.
Date: February 1952
Creator: Wang, Chi-Teh
Partner: UNT Libraries Government Documents Department

Problem of Slip Flow in Aerodynamics

Description: Memorandum presenting a survey of the present status of theory in the field of slip-flow aerodynamics, which leads to the conclusion that the Navier-Stokes equations of motion together with first-order velocity slip and temperature jump at any boundary are sufficient insofar as experimental confirmation is available.
Date: March 4, 1957
Creator: Street, Robert E.
Partner: UNT Libraries Government Documents Department

Preliminary Indications of the Cooling Achieved by Ejecting Water Upstream From the Stagnation Point of Hemispherical, 80 Degree Conical, and Flat-Faced Nose Shapes at a Stagnation Temperature of 4,000 F

Description: Memorandum presenting an investigation of the effectiveness of water-vaporization cooling that would be obtained by ejecting water upstream from the stagnation point conducted in a liquid-fuel rocket jet as a stagnation temperature of 4000 degrees Fahrenheit.
Date: October 23, 1957
Creator: Rashis, Bernard
Partner: UNT Libraries Government Documents Department

Analytical Study of Shimmy of Airplane Wheels

Description: The problem of shimmy of a castering wheel, such as the nose wheel of a tricycle gear airplane, is treated analytically. The flexibility of the tire is considered to be the primary cause of shimmy. The rather simple theory developed agrees rather well with previous experimental results. The author suggests that shimmy may be eliminated through a suitable choice of landing gear dimensions in lieu of a damper.
Date: September 1952
Creator: Bourcier de Carbon, Christian
Partner: UNT Libraries Government Documents Department

Bending of Beams of Thin Sections

Description: The tendency toward economy of material and lightness of structure has long since led to the increased application of beams having large ratios of moment of area W to cross-sectional area F. This paper tries to provide an answer to how thin the beams can be.
Date: April 1936
Creator: Huber, Maximilian T.
Partner: UNT Libraries Government Documents Department

Airplane Stability in Taxying

Description: The stability analysis of an airplane while rolling is much more simplified to the extent that it can be obtained for numerical data which can be put to practical use in the design of landing gear dimensions. Every landing gear type attains to a critical ground friction coefficient that decides the beginning of instability, i.e., nosing over. This study has, in addition, a certain interest for the use of wheel brakes.
Date: September 1932
Creator: Anderlik, E.
Partner: UNT Libraries Government Documents Department

Airplane Drag

Description: It has been less well understood that the induced drag (or, better said, the undesired increase in the induced drag as compared with the theoretical minimum calculated by Prandtl) plays a decisive role in the process of taking off and therefore in the requisite engine power. This paper seeks to clarify the induced drag.
Date: December 1929
Creator: Töpfer, Carl
Partner: UNT Libraries Government Documents Department

The Aerodynamic Effect of a Retractable Landing Gear

Description: "Tests were conducted in the N.A.C.A. full scale wind tunnel at the request of the Army Air Corps to determine the effect of retractable landing gear openings in the bottom surface of a wing upon the characteristics of a Lockheed Altair airplane. The tests were extended to include the determination of the lift and drag characteristics throughout the angle-of-attack range with the landing gear both retracted and extended. Covering the wheel openings in the wing with sheet metal when the wheels were extended reduced the drag only 2 percent at a lift coefficient of 1.0, which was assumed for the take-off condition" (p. 1).
Date: March 1933
Creator: DeFrance, Smith J.
Partner: UNT Libraries Government Documents Department

Aerodynamic Factors Affecting the Ability of a Pilot to Return an Airplane to Level From a Banked Attitude by Use of the Rudder Alone and Without Change of Heading

Description: Report presenting a study of the aerodynamic factors upon which the ability to perform the maneuver depends in an attempt to obtain a better understanding of the conditions involved and, if possible, to evolve criterions that may be used during design.
Date: October 1941
Creator: Harmon, S. M.
Partner: UNT Libraries Government Documents Department

The Air Propeller, Its Strength and Correct Shape

Description: It is possible to give a propeller such a shape that, under given conditions, viz., a definite speed of revolution and flying speed, the bending stresses in the blades will assume quite an insignificant magnitude.
Date: February 1923
Creator: Dietsius, H.
Partner: UNT Libraries Government Documents Department

Airfoil Section Data From Tests of 10 Practical-Construction Sections of Helicopter Rotor Blades Submitted by the Sikorsky Aircraft Division, United Aircraft Corporation

Description: Report presenting 10 practical-construction models of sections of helicopter rotor blades tested in the NACA two-dimensional low-turbulence pressure tunnel at atmospheric pressure. Lift, drag, and pitching-moment characteristics of blades representing the present method of construction of the YR-4A helicopter were determined.
Date: September 1944
Creator: Tetervin, Neal
Partner: UNT Libraries Government Documents Department