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- [News Clip: Fireplace]
- Video footage from the KXAS-TV/NBC station in Fort Worth, Texas, to accompany a news story.
- [News Script: Moon experiments]
- Script from the WBAP-TV/NBC station in Fort Worth, Texas, relating a news story.
- Analysis of Bulk Shielding Facility Neutron Dosimeter Data
- Technical report calculating "effective removal cross sections" for Pb, Fe and O from measurements of fast neutron does in the water surrounding the BSF reactor. The values for Pb and Fe agree quite well with those previously determined from Lid tank data, whereas that for O is somewhat lower. [From Abstract]
- Compressibilities of gases
- Reproduction of thirteen graphs for computing compressibilities of various gases and for computing the volumes delivered from cylinders containing various gases.
- Practical Methods of Calculation Involved in the Experimental Study of an Autopilot and the Autopilot-Aircraft Combination
- Report presenting practical methods for making the calculations required for the analysis of an autopilot and an autopilot-aircraft combination from frequency-response data. From Summary: "Equations are derived for determining the servo-system error voltage for both displacement input signal and displacement plus rate of displacement input signals, the autopilot frequency response for addition of rate of displacement input signal, the servo-system frequency response for a change of gain, and the relation between open-loop and closed-loop frequency responses for the servo system and the autopilot-aircraft combination."
- Some Considerations on an Airfoil in an Oscillating Stream
- Report presenting information regarding the velocity potential, lift force, moment, and propulsive force on a two-dimensional airfoil in a stream of periodically varying angle of attack, as well as an application of the theoretical results.
- A Rapid Method for Estimating the Separation Point of a Compressible Laminar Boundary Layer
- Report presenting a method for quickly estimating the separation point of a laminar boundary layer in a compressible flow. The method should be usable for any two-dimensional flow in which classical boundary-layer assumptions are satisfied. Results obtained from a variety of calculations indicate that for all velocity gradients, the amount of velocity recovery possible before laminar separation occurs decreases as Mach number increases.
- Two matrix methods for calculating forcing functions from known responses
- Report presenting an analysis of two matrix methods for calculating responses of linear systems for given forcing functions and indicial responses in order to find a method suitable for solving the inverse problem of calculating forcing functions from known responses. The results of both methods are compared with exact solutions for both the direct and the inverse problems.
- A method of determining the effect of airplane stability on the gust load factor
- Report presenting the equations of motion of a conventional airplane penetrating a gust in order to determine the effects due to stability on the gust load factor. A numerical method is derived in matrix notation which affords a systematic procedure of solving the equations for a unit jump or arbitrary forcing function. Sample calculations were performed to illustrate the application of the equations.
- A Thermodynamic Study of the Turbine-Propeller Engine
- Report presenting equations and charts for computing the thrust, power output, fuel consumption, and other performance parameters of a turbine-propeller engine for any given set of operating conditions and component efficiencies. The total thrust horsepower per unit mass rate of air flow and specific fuel consumption for a wide range of flight and engine-design operating conditions are also presented.
- A Graphical Method for Plotting Amplitude and Phase Angle of Transfer Functions of Dynamic Systems Without Factoring Polynomials
- "A method is presented for obtaining amplitude and single plots for rational algebraic functions of an imaginary variable. Application of the method is illustrated by an example in which the frequency response of an automatically controlled aircraft is plotted. The method involves the use of templets but does not require the factoring of polynomials" (p. 1).
- The aerodynamic behavior of a harmonically oscillating finite sweptback wing in supersonic flow
- From Introduction: "The paper treats the case of a finite wing with leading edge ahead of the Mach line."
- The Longitudinal Stability of Elastic Swept Wings at Supersonic Speed
- Report presenting calculations of the longitudinal stability characteristics of elastic swept wings of high aspect ratio experiencing bending and torsional deformations by applying the linearized lifting-surface theory. Results of numerical calculations for a wing of aspect ratio 3.2 and 60 degrees of sweepback at Mach number 1.414 are provided. A discussion of the supersonic lifting-surface theory, comparison of aeroelastic effects at supersonic speed with incompressible flow solutions, and strip theory are also provided.
- The Local Buckling Strength of Lipped Z-Columns With Small Lip Width
- Report presenting a method for calculating the local buckling strength of lipped Z-columns with a small lip width. Some experimental data are presented to show agreement between theoretical and experimental results.
- Prandtl-Meyer Flow for a Diatomic Gas of Variable Specific Heat
- Report presenting tables and charts that give the results of an analysis accounting for variation in specific heats of a nonviscous compressible fluid during a Prandtl-Meyer flow process. The analysis results indicated that the effect of variation in specific heat on the magnitude of parameters pertinent to the flow is appreciable at high temperatures and high expansion pressure ratios.
- Stability of Alclad Plates
- Report presenting a theoretical solution for the buckling of Alclad plates on the basis of plasticity theory. Both the differential equation of equilibrium of the buckled plate and energy expression are provided. Results regarding the buckling of long simply supported plates under longitudinal compression and under shear and for a plate column are provided.
- Bending of Thin Plates With Compound Curvature
- Report presenting an analysis for the deformation of a doubly curved thin plate under edge loads or surface loads for small deflections. The method is particularly useful for a plate whose radius of curvature in one direction is large compared with its length and width dimensions.
- A Method for Estimating the Components of Lift of Wing-Body Combinations at Supersonic Speeds
- Report presenting the lift of wing-body combinations at supersonic speeds as obtained by means of an approximate linearized-theory analysis involving an assumption concerning the geometry of the body. A comparison with several groups of data is provided to show the accuracy of the method.
- Charts for the Analysis of One-Dimensional Steady Compressible Flow
- Report presenting charts of dimensionless parameters to facilitate the computation involved in the solution of equations of one-dimensional steady flow of a compressible field. The charts can be used for analyses involving constant or variable specific heats in the subsonic and supersonic ranges.
- Theoretical Lift Distribution and Upwash Velocities for Thin Wings at Supersonic Speeds
- Report presenting a method for calculating the upwash-velocity component in the vicinity of thin wings at supersonic speeds. The method is applied to obtain an expression for the upwash over wing tips of fairly general plan form and profile.
- An Investigation of Aircraft Heaters 29: Comparison of Several Methods of Calculating Heat Losses From Airfoils
- Report presenting a critical comparison and summary of the various methods proposed for calculating the unit thermal conductance on the outer surface of a heated wing involving both laminar and turbulent boundary layers, and a new equation is suggested that should indicate the effect of pressure gradient on laminar heat transfer.
- Calculation of Wing Spars
- The author presents a comparison and combination of the numerical and geometrical determinations of the maximum M, when calculating the maximum bay moment.
- A Method for Calculating the Lift and Center of Pressure of Wing-Body-Tail Combinations at Subsonic, Transonic, and Supersonic Speeds
- Report presenting a method for calculating the lift and pitching-moment characteristics of circular cylindrical bodies in combination with triangular, rectangular, or trapezoidal wings or tails through the subsonic, transonic, and supersonic speed ranges. A computing table and set of design charts are presented to reduce the calculations to routine operations. Information about lift, center of pressure, effects of wing incidence, and limitations and extensions of the method is provided.
- Method for Estimating Pitching-Moment Interference of Wing-Body Combinations at Supersonic Speed
- Report presenting an investigation into the effects of interference at supersonic speeds on the aerodynamic properties of wing-body combinations to determine the pitching moments. The correlation points of various wing-body shapes are provided and suggestions for modifications are made.
- Interference of Multiplane Wings Having Elliptical Lift Distribution
- In calculating the self-induction of a wing surface, elliptical lift distribution is assumed, while in calculating the mutual induction or interference of two wing surfaces, a uniform distribution of the lift along the wing has hitherto been assumed. Whether the results of these calculations are substantially altered by assuming an elliptical lift distribution (which is just as probable as uniform distribution) is examined here.
- Significance of the expression CL³/CD²
- Report presenting an analysis of the title coefficient as used in Kahn's formula for the ceiling.
- Introduction to the Problem of Rocket-Powered Aircraft Performance
- An introduction to the problem of determining the fundamental limitations on the performance possibilities of rocket-powered aircraft is presented. Previous material on the subject is reviewed and given in condensed form along with supplementary analyses. Some of the problems discussed are: 1) limiting velocity of a rocket projectile; 2) limiting velocity of a rocket jet; 3) jet efficiency; 4) nozzle characteristics; 5) maximum attainable altitudes; 6) ranges. Formulas are presented relating the performance of a rocket-powered aircraft to basic weight and nozzle dimensional parameters. The use of these formulas is illustrated by their application to the special case of a nonlifting rocket projectile.
- Determination of Stresses in Gas-turbine Disks Subjected to Plastic Flow and Creep
- From Summary: "A finite-difference method previously presented for computing elastic stresses in rotating disks is extended to include the computation of the disk stresses when plastic flow and creep are considered. A finite-difference method is employed to eliminate numerical integration and to permit nontechnical personnel to make the calculations with a minimum of engineering supervision. Illustrative examples are included to facilitated explanation of the procedure by carrying out the computations on a typical gas-turbine disk through a complete running cycle."
- Calculation of Aerodynamic Forces on a Propeller in Pitch or Yaw
- Report presenting an analysis to determine the applicability of existing propeller theory and the theory of oscillating airfoils to the problem of determining the magnitude of the forces on propellers in pitch or yaw. The steady-state method for calculating propeller forces appears to give satisfactory results.
- The Calculation of Certain Static Aeroelastic Phenomena of Wings With Tip Tanks or Boom-Mounted Lifting Surfaces
- Report presenting the use of the matrix-integration method for calculating static aeroelastic phenomena on a wing with concentrated aerodynamic forces at the tip due to tip tanks or boom-mounted lifting surfaces. The results indicate that the presence of a tip tank on an unswept wing tends to deteriorate its static aeroelastic characteristics and that a lift surface geared to the aileron and mounted on a boom ahead of the tip may improve the static aeroelastic characteristics to warrant consideration of a vane as a device for relieving adverse aeroelastic effects.
- Calculation of Aerodynamic Forces on an Inclined Dual-Rotating Propeller
- Report presenting a method for calculating the aerodynamic forces on the blades of a dual-rotating propeller with its thrust axis inclined to the air stream. Comparison of the fluctuating aerodynamic forces due to pitched or yawed operation of a dual-rotating propeller show that the fluctuation in forces on the front component tend to be greater than those on the rear component.
- Formulas for the Elastic Constants of Plates With Integral Waffle-Like Stiffening
- Report presenting formulas for fifteen elastic constants associated with bending, stretching, twisting, and shearing of plates with closely spaced integral ribbing in a variety of configurations and proportions. Four coefficients are provided for each rib and the experimental means of determining them are described.
- Determination of elastic stresses in gas-turbine disks
- A method is presented for the calculation of elastic stresses in symmetrical disks typical of those of a high-temperature gas turbine. The method is essentially a finite-difference solution of the equilibrium and compatibility equations for elastic stresses in a symmetrical disk. Account can be taken of point-to-point variations in disk thickness, in temperature, in elastic modulus, in coefficient of thermal expansion, in material density, and in Poisson's ratio. No numerical integration or trial-and-error procedures are involved and the computations can be performed in rapid and routine fashion by nontechnical computers with little engineering supervision. Checks on problems for which exact mathematical solutions are known indicate that the method yields results of high accuracy. Illustrative examples are presented to show the manner of treating solid disks, disks with central holes, and disks constructed either of a single material or two or more welded materials. The effect of shrink fitting is taken into account by a very simple device.
- Evaluation of the Induced-Velocity Field of an Idealized Helicopter Rotor
- Report presenting a concept of a simplified vortex system of a rotor wake in order to obtain a formula for the normal component of induced velocity along the fore-and-aft diameter of the rotor disk of a helicopter rotors.
- Theoretical calculation of the power spectra of the rolling and yawing moments on a wing in random turbulence
- The correlation functions and power spectra of the rolling and yawing moments on an airplane wing due to the three components of continuous random turbulence are calculated. The rolling moments to the longitudinal (horizontal) and normal (vertical) components depend on the spanwise distributions of instantaneous gust intensity, which are taken into account by using the inherent properties of symmetry of isotropic turbulence. The results consist of expressions for correlation functions or spectra of the rolling moment in terms of the point correlation functions of the two components of turbulence.
- Formulas for Use in Boundary-Layer Calculations on Low-Drag Wings
- Report presenting information regarding the calculation of the transition point, velocity distribution in laminar and turbulent boundary layers, and thickness of the boundary layer, both laminar and turbulent, of low-drag wings.
- [Personal notes, undated]
- Personal notes from the Charles B. Moore Collection. The document has calculations on the top left-hand corner of the paper.
- [Personal notes, undated]
- Personal notes from the Charles B. Moore Collection. The document has lists and calculations on the front and back of the paper.
- [Personal notes, undated]
- Personal notes from the Charles B. Moore Collection. The document has lists and calculations on the front and back of the paper. Moore also names people and places in these notes.
- [Personal notes, undated]
- Personal notes from the Charles B. Moore Collection. The document has lists and calculations on the front and back of the paper.
- [Personal notes, undated]
- Personal notes from the Charles B. Moore Collection. The document has calculations on the front and back of the paper.
- [Personal notes, undated]
- Personal notes from the Charles B. Moore Collection. The document has financial information and calculations on the front and back of the paper.
- [Personal notes, undated]
- Personal notes from the Charles B. Moore Collection. The document has lists, financial information, and calculations on the front and back of the paper.
- [H. S. Moore Notes Against C. B. Moore]
- List of monetary figures labeled "H. S. Moore notes against C. B. Moore" written on a scrap of paper. The back of the paper has a handwritten note, "Notes Recto &c."
- Betatron Scraping at RHIC: General Remarks and Sample Calculations
- A betatron scraper is a physical aperture whose primary purpose is to intercept particle trajectories whose amplitude is outside the dynamic aperture.
- [Handwritten calculations on notepad]
- A notepad page containing handwritten mathematic calculations. The notepad is branded with a logo that reads, "Swissotel Atlanta."
- [Voting Process]
- Document containing voting scores for the Extra Mile Award nominees. The document also contains photocopies of a calculator sheet.
- The Feeding of Farm Animals
- Report discussing the general principles of the feeding of farm animals based on experiments and investigations as well as the observations of successful animal feeders. The discussion includes suggested rations for various animals and purposes.
- The Feeding of Farm Animals
- Report discussing the general principles of the feeding of farm animals based on experiments and investigations as well as the observations of successful animal feeders. The discussion includes suggested rations for various animals and purposes.
- [News Clip: SMU's Univac is dedicated]
- Video footage from the WBAP-TV station in Fort Worth, Texas to accompany a news story about dedication ceremonies for the Univac mainframe computer at Southern Methodist University in Dallas.