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  Partner: UNT Libraries Government Documents Department
 Collection: Technical Report Archive and Image Library
Table of interplanar spacings for crystal-structure determinations by X-ray diffraction with molybdenum, copper, cobalt, iron, and chromium radiations
For a simple diffraction pattern, the time required to calculate interplanar distances from measurements of the pattern is not excessive. If more than a few lines are present, however, or if several patterns are to be studied, it is very advantageous to have available a table giving interplanar spacings directly in terms of the linear measurements made on the film of the lines appearing on the diffraction pattern. The preparation of the table given here was undertaken when the expansion of research activities involving X-ray diffraction techniques indicated that such a table would greatly decrease the time required to analyze diffraction patterns. The table was prepared for use with K alpha(sub 1) radiation from the following target materials: molybdenum, copper, cobalt, iron, and chromium. digital.library.unt.edu/ark:/67531/metadc53677/
A Table of Radiation Characteristics for Uniformly Spaced Optimum Endfire Arrays with Equal Sidelobes
No Description digital.library.unt.edu/ark:/67531/metadc13274/
Table of sine and cosine integrals for arguments from 10 to 100
No Description digital.library.unt.edu/ark:/67531/metadc40300/
Table of wavenumbers: Volume 1, 2000 A to 7000 A
No Description digital.library.unt.edu/ark:/67531/metadc13219/
Table of Wavenumbers: Volume 2, 7000 A to 1000 mu
No Description digital.library.unt.edu/ark:/67531/metadc13221/
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/
Tables and charts for thermodynamic calculations involving air and fuels containing boron, carbon, hydrogen, and oxygen
No Description digital.library.unt.edu/ark:/67531/metadc62300/
Tables and Charts of Flow Parameters Across Oblique Shocks
Shock-wave equations have been evaluated for a range of Mach number in front of the shock from 1.05 to 4.0. Mach number behind the shock, pressure ratio, derivation of flow, and angle of shock are presented on charts. Values are also included for density ratio and change in entropy. digital.library.unt.edu/ark:/67531/metadc172508/
Tables and graphs of normal-shock parameters at hypersonic Mach numbers and selected altitudes
No Description digital.library.unt.edu/ark:/67531/metadc57249/
Tables for calibrating altimeters and computing altitudes based on the standard atmosphere
During 1925 the assumption of an isothermal atmosphere which was in general use as the standard for the calibration of altimeters in the United States was replaced by a standard atmosphere which assumes an altitude-temperature relation closely corresponding to the average of upper air observations at latitude 40 degrees in this country. The same standard atmosphere had already been adopted somewhat earlier in the United States as the aircraft performance standard. National Advisory Committee for Aeronautics Technical Reports nos. 147 and 218 give necessary constants, tables, and information. However, neither of these reports includes all of the tables required for the computation of actual altitudes nor those readily suitable for use in calibrating altimeters, since the altitude intervals for which data are given are not sufficiently small. The present report has been prepared specifically for these purposes. The formulas which define the standard atmosphere are given in this report, together with other formulas giving the corrections to be applied to the standard altitude in order to obtain the actual altitude when the necessary observations of pressure and temperature are available. The tables necessary for the use of this standard atmosphere in calibrating altimeters and in computing altitudes form the principal part of this report. An example of the computation of actual altitudes from observed pressures and temperatures are given in table IV. digital.library.unt.edu/ark:/67531/metadc65898/
Tables for computing various cases of beam columns
For a better understanding of these tables, the methods by which the cases are computed are discussed first. The importance of the buckling modules is pointed out. digital.library.unt.edu/ark:/67531/metadc63130/
Tables for determining reduction of energy and intensity of X-rays and gamma-rays at various scattering angles in small thickness of matter
No Description digital.library.unt.edu/ark:/67531/metadc55339/
Tables for pressure of air on coming to rest from various speeds
In Technical Report no. 247 of the National Advisory Committee for Aeronautics theoretical formulas are given from which was computed a table for the pressure of air on coming to rest from various speeds, such as those of aircraft and propeller blades. In that report, the table gave incompressible and adiabatic stop pressures of air for even-speed intervals in miles per hour and for some even-speed intervals in knots per hour. Table II of the present report extends the above-mentioned table by including the stop pressures of air for even-speed intervals in miles per hour, feet per-second, knots per hour, kilometers per hour, and meters per second. The pressure values in table II are also more exact than values given in the previous table. To furnish the aeronautical engineer with ready numerical formulas for finding the pressure of air on coming to rest, table I has been derived for the standard values specified below it. This table first presents the theoretical pressure-speed formulas and their working forms in C. G. S. Units as given in NACA Technical Report No. 247, then furnishes additional working formulas for several special units of speed. (author). digital.library.unt.edu/ark:/67531/metadc65971/
Tables for the computation of wave drag of arrow wings of arbitrary airfoil section
No Description digital.library.unt.edu/ark:/67531/metadc57201/
Tables for the Computation of Wave Drag of Arrow Wings of Arbitrary Airfoil Section
Tables and computing instructions for the rapid evaluation of the wave drag of delta wings and of arrow wings having a ration of the tangent of the trailing-edge sweep angle to the tangent of the leading-edge sweep angle in the range from -1.0 to 0.8. The tables cover a range of both subsonic and supersonic leading edges. digital.library.unt.edu/ark:/67531/metadc100822/
Tables for the numerical determination of the Fourier transform of a function of time and the inverse Fourier transform of a function of frequency, with some applications to operational calculus methods
No Description digital.library.unt.edu/ark:/67531/metadc56982/
Tables of characteristic functions for solving boundary-value problems of the wave equation with application to supersonic interference
No Description digital.library.unt.edu/ark:/67531/metadc56278/
Tables of Chemical Kinetics : Homogeneous Reactions (Supplementary Tables)
No Description digital.library.unt.edu/ark:/67531/metadc13227/
Tables of Chemical Kinetics : Homogeneous Reactions (Supplementary Tables)
No Description digital.library.unt.edu/ark:/67531/metadc13226/
Tables of coefficients for the analysis of stresses about cutouts in circular semimonocoque cylinders with flexible rings
No Description digital.library.unt.edu/ark:/67531/metadc57587/
Tables of Einstein Functions: Vibrational Contributions to the Thermodynamic Functions
No Description digital.library.unt.edu/ark:/67531/metadc13243/
Tables of Electron Radial Functions and Tangents of Phase Shifts for Light Nuclei (Z=1 through 10)
No Description digital.library.unt.edu/ark:/67531/metadc13265/
Tables of exact laminar-boundary-layer solutions when the wall is porous and fluid properties are variable
No Description digital.library.unt.edu/ark:/67531/metadc55831/
Tables of hypergeometric functions for use in compressible-flow theory
No Description digital.library.unt.edu/ark:/67531/metadc54957/
Tables of Spectral-Line Intensities: Part 1 - Arranged by Elements
No Description digital.library.unt.edu/ark:/67531/metadc13183/
Tables of Spectral-Line Intensities: Part 1, Arranged by Elements
No Description digital.library.unt.edu/ark:/67531/metadc13222/
Tables of Spectral-Line Intensities: Part 2 - Arranged by Wavelengths
No Description digital.library.unt.edu/ark:/67531/metadc13184/
Tables of Spectral-Line Intensities: Part 2, Arranged by Wavelengths
No Description digital.library.unt.edu/ark:/67531/metadc13223/
Tables of stiffness and carry-over factor for flat rectangular plates under compression
No Description digital.library.unt.edu/ark:/67531/metadc62208/
Tables of stiffness and carry-over factor for structural members under axial load
Tables of stiffness and carry-over factor are presented for members in which the cross section and axial load do not vary along the length of the member. These tables are of use in solving problems in the stability of structural members under axial load as well as in application of the Cross method of moment distribution when the effects of axial load in the members are considered. The interval between successive values of the argument is small enough to make interpolation unnecessary in engineering calculations. digital.library.unt.edu/ark:/67531/metadc54393/
Tables of the Bessel functions Yo(x), Y1(x), Ko(x), 0<=x<=1
No Description digital.library.unt.edu/ark:/67531/metadc40299/
Tables of the confluent hypergeometric function F(n/2, 1/2; x) and related functions
No Description digital.library.unt.edu/ark:/67531/metadc40296/
Tables of the exponential function e [superscript x]
No Description digital.library.unt.edu/ark:/67531/metadc40297/
Tables of the Racah Coefficients
Report containing tables of the Racah Coefficients. digital.library.unt.edu/ark:/67531/metadc100490/
Tables of thermodynamic functions for analysis of aircraft-propulsion systems
No Description digital.library.unt.edu/ark:/67531/metadc55767/
Tables of thermodynamic properties of ammonia
A report containing tables of thermodynamic properties of ammonia. digital.library.unt.edu/ark:/67531/metadc100736/
Tables of various Mach number functions for specific-heat ratios from 1.28 to 1.38
No Description digital.library.unt.edu/ark:/67531/metadc56412/
Tables of wing-aileron coefficients of oscillating air forces for two-dimensional supersonic flow
No Description digital.library.unt.edu/ark:/67531/metadc55414/
Tabulated Analyses of Representative Crude Petroleums of the United States
No Description digital.library.unt.edu/ark:/67531/metadc12468/
Tabulated Analyses of Texas Crude Oils
Report issued by the Bureau of Mines discussing analyses of Texas crude oils. As stated in the introduction, "this paper makes available in condensed tabular form under one cover all analyses of Texas crude oils made by the Bureau of Mines to March 1939" (p. 1). This report includes tables, and a map. digital.library.unt.edu/ark:/67531/metadc66423/
Tabulated Analyses of Texas Crude Oils
Report issued by the U.S. Bureau of Mines covering the crude oils from different regions of Texas. Analysis of the properties of each oil sample from the different regions of the state are presented. This report includes tables, and a map. digital.library.unt.edu/ark:/67531/metadc38400/
Tabulated Pressure Coefficient Data from a Tail Loads Investigation on a 1/15-Scale Model of the Goodyear XZP5K Airship
This paper contains tail and hull loads data obtained in an investigation of a l/15-scale model of the Goodyear XZP5K airship. Data are presented in the form of tabulated pressure coefficients over a pitch and yaw range of +/-20 deg and 0 deg to 30 deg respectively, with various rudder and elevator deflections. Two tail configurations of different plan forms were tested on the model. The investigation was conducted in the Langley full-scale tunnel at a Reynolds number of approximately 16.5 x 10(exp 6) based on hull length, which corresponds to a Mach number of about 0.12. digital.library.unt.edu/ark:/67531/metadc64569/
Tabulated pressure coefficients and aerodynamic characteristics measured in flight on the wing of the D-558-I research airplane through a Mach number range of 0.80 to 0.89 and throughout the normal-force-coefficient range at Mach numbers of 0.61, 0.7
No Description digital.library.unt.edu/ark:/67531/metadc58883/
Tabulated pressure coefficients and aerodynamic characteristics measured in flight on the wing of the douglas d-558-i airplane for a 1 g stall, a speed run to a mach number of 0.90, and a wind-up turn at a mach number of 0.86
No Description digital.library.unt.edu/ark:/67531/metadc53006/
Tabulated pressure coefficients and aerodynamic characteristics measured on the wing of the Bell X-1 airplane in an unaccelerated low-speed stall, in push-overs at Mach numbers of 0.83 and 0.99, and in a pull-up at a Mach number of 1.16
No Description digital.library.unt.edu/ark:/67531/metadc58931/
Tabulated pressure coefficients and aerodynamic characteristics measured on the wing of the Bell X-1 airplane in an unaccelerated stall and in pull-ups at Mach numbers of 0.74, 0.75, 0.94, and 0.97
No Description digital.library.unt.edu/ark:/67531/metadc58774/
Tabulated pressure coefficients and aerodynamic characteristics measured on the wing of the Bell X-1 airplane in level flight at Mach numbers from 0.79 to 1.00 and in a pull-up at a Mach number of 0.96
No Description digital.library.unt.edu/ark:/67531/metadc58585/
Tabulated pressure coefficients and aerodynamic characteristics measured on the wing of the Bell X-1 airplane in pull-ups at Mach numbers from 0.53 to 0.99
No Description digital.library.unt.edu/ark:/67531/metadc58614/
Tabulated pressure data for a 60 degree delta-wing-body-tail model with a hot jet exhausting from a pylon-mounted nacelle
No Description digital.library.unt.edu/ark:/67531/metadc63806/
Tabulated Pressure Data for a Series of Controls on a 40 Deg Sweptback Wing at Mach Numbers of 1.61 and 2.01
An investigation has been made at Mach numbers of 1.61 and 2.01 and Reynolds numbers of 1.7 x l0(exp 6) and 3.6 x l0(exp 6) to determine the pressure distributions over a swept wing with a series of 14 control configurations. The wing had 40 deg of sweep of the quarter-chord line, an aspect ratio of 3.1, and a taper ratio of 0.4. Measurements were made at angles of attack from 0 deg to +/- 15 deg for control deflections from -60 deg to 60 deg. This report contains tabulated pressure data for the complete range of test conditions. digital.library.unt.edu/ark:/67531/metadc53003/