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Adaptation of Combustion Principles to Aircraft Propulsion Volume 2: Combustion in Air-Breathing Jet Engines

Description: This volume continues the NACA study of combustion principles for aircraft propulsion. The various aspects of combustion pertinent to jet engines are organized and interpreted with quite extensive information, particularly for basic or fundamental. subject matter. The report concerns only air-breathing engines and hydrocarbon fuels, and not rocket engines and high-energy fuels.
Date: May 2, 1956
Creator: Fuels and Combustion Research Division
Partner: UNT Libraries Government Documents Department

The Aerodynamic Characteristics in Pitch of a 1/15-Scale Model of the Grumman F11F-1 Airplane at Mach Numbers of 1.41, 1.61, and 2.01, TED No. NACA DE 390

Description: "Tests have been made in the Langley 4- by 4-foot supersonic pressure tunnel at Mach numbers of 1.41, 1.61, and 2.01 to determine the static longitudinal stability and control characteristics of various arrangements of the Grumman F11F-1 airplane. Tests were made of the complete model and various combinations of its component parts and, in addition, the effects of various body modifications, a revised vertical tail, and wing fences on the longitudinal characteristics were determined" (p. 1).
Date: May 23, 1956
Creator: Driver, Cornelius
Partner: UNT Libraries Government Documents Department

Aerodynamic Damping at Mach Numbers of 1.3 and 1.6 of a Control Surface on a Two-Dimensional Wing by a Free-Oscillation Method

Description: Memorandum presenting tests at two supersonic speeds to obtain experimentally the aerodynamic damping characteristics of a control surface on a two-dimensional wing. The control surface had a chord of 1.67 inches and a span of 7.25 inches and was supplied in three materials with different mass, inertia, and stiffness properties. Results regarding the presentation of data and comparison with theory and comparison with control-surface data for a triangular wing are provided.
Date: May 1, 1956
Creator: Tuovila, W. J. & Hess, Robert W.
Partner: UNT Libraries Government Documents Department

Analytic evaluation of effect of inlet-air temperature and combustion pressure on combustion performance of boron slurries and blends of pentaborane in octene-1 : Supplement I - Influence of new boric-oxide vapor-pressure data on calculated performanc

Description: "The theoretical performance of pentaborane has been recalculated using recent data on the vapor pressure of boric oxide. Previous calculations were based upon vapor-pressure data obtained some years ago by a method not as accurate as that employed in current investigations. The recalculated performance data for pentaborane differ appreciably from previously published data and are considered more accurate for evaluation of the relative potentialities of boron-containing fuels" (p. 1).
Date: May 25, 1956
Creator: Tower, Leonard K.
Partner: UNT Libraries Government Documents Department

Approximate indicial lift functions for several wings of finite span in incompressible flow as obtained from oscillatory lift coefficients

Description: Report presenting the unsteady-lift functions for a wing undergoing a sudden change in sinking speed for delta wings with three aspect ratios and rectangular and elliptical wings with three aspect ratios. Results regarding the delta-plan-form K1 function, indical spanwise loading distributions, effect of plan-form shape on the K1 function, and effect of aspect ratio on the K1 and K2 functions are provided.
Date: May 1956
Creator: Drischler, Joseph A.
Partner: UNT Libraries Government Documents Department

Boundary Layer

Description: From Introduction: "The fundamental, practically the most important branch of the modern mechanics of a viscous fluid or a gas, is that branch which concerns itself with the study of the boundary layer. The presence of a boundary layer accounts for the origin of the resistance and lift force, the breakdown of the smooth flow about bodies, and other phenomena that are associated with the motion of a body in a real fluid. The concept of boundary layer was clearly formulated by the founder of aerodynamics, N. E. Joukowsky, in his well-known work "On the Form of Ships" published as early as 1890."
Date: May 1956
Creator: Loitsianskii, L. G.
Partner: UNT Libraries Government Documents Department

Boundary Layer Behind Shock or Thin Expansion Wave Moving Into Stationary Fluid

Description: Note presenting a determination of the boundary layer behind a shock or thin expansion wave advancing into a stationary fluid. The assumption of a thin expansion wave was found to be valid for weak expansions but becomes progressively less accurate for strong expansion waves. The turbulent-boundary-layer solutions in this report represent an extension of empirical, semi-infinite flat-plate, boundary-layer data to the case where the wall is moving.
Date: May 1956
Creator: Mirels, Harold
Partner: UNT Libraries Government Documents Department

Chrysotile-Asbestos Deposits of Arizona: Supplement to Information Circular 7706

Description: Report issued by the U.S. Bureau of Mines discussing asbestos mining and production in Arizona. As a supplement to a previous report, 18 additional Arizona mining districts are presented and described. This report includes tables, maps, illustrations, and photographs.
Date: May 1956
Creator: Stewart, Lincoln A.
Partner: UNT Libraries Government Documents Department

Comparison between experimental and predicted downwash at a Mach number of 0.25 behind a wing-body combination having a triangular wing of aspect ratio of 2.0

Description: A study to evaluate a method for predicting the downwash in a transverse plane behind a wing-body combination throughout a range of angles of attack. The wing-body combination had a ratio of maximum body diameter to wing span of 0.259, a triangular wing with an aspect ratio of 2.0, and a body of revolution with a fineness ratio of 12.5. Results regarding span loading, downwash, and vortex cores are provided.
Date: May 1956
Creator: Sorensen, Norman E. & Hopkins, Edward J.
Partner: UNT Libraries Government Documents Department

Comparison of experimental and theoretical normal-force distributions (including Reynolds number effects) on an ogive-cylinder body at Mach number 1.98

Description: Effects of Reynolds number and angle of attack on the pressure distribution and normal-force characteristics of a body of revolution consisting of a fineness ratio 3 ogival nose tangent to a cylindrical afterbody 7 diameters long have been determined. The test Mach number was 1.98 and the angle-of-attack range from 0 degree to 20 degrees. The Reynolds numbers, based on body diameter, were 0.15 x 10(6) and 0.45 x 10(6). The experimental results are compared with theory.
Date: May 1956
Creator: Perkins, Edward W. & Jorgensen, Leland H.
Partner: UNT Libraries Government Documents Department

Comparison of the experimental and theoretical distributions of lift on a slender inclined body of revolution at M = 2

Description: Report presenting pressure distributions and force characteristics for a body of revolution consisting of a fineness ratio of 5.75, circular-arc, ogival nose tangent to a cylindrical afterbody for a range of angles of attack. Comparison of the theoretical and experimental pressure distributions shows that for zero lift, both slender-body theory and higher-order theories yield results that are in good agreement with theory.
Date: May 1956
Creator: Perkins, Edward W. & Kuehn, Donald M.
Partner: UNT Libraries Government Documents Department

Comparison of the Isotopic Abundance of U^235 and U^238 and the Radium Activity Ratios in Colorado Plateau Uranium Ores

Description: From abstract: "The isotopic abundances of uranium and the radium activity ratios of 11 samples of uranium ore from the Colorado Plateau have been measured." Experimental data and discussion is included with information regarding the samples used.
Date: May 1956
Creator: Senftle, F. E.; Stieff, Lorin; Cuttitta, Frank & Kuroda, P. K.
Partner: UNT Libraries Government Documents Department

Correlation of creep-buckling tests with theory

Description: Report presenting the results of short-time creep-buckling and creep-bending tests of 2024-T4 aluminum-alloy columns of slenderness ratio 111 are presented. Tests were performed at 600 degrees Fahrenheit and strain measurements were taken with high-temperature electric-resistance strain gages.
Date: May 23, 1956
Creator: Patel, Sharad A.; Kempner, Joseph; Erickson, Burton & Mobassery, Abol H.
Partner: UNT Libraries Government Documents Department

CRYOGENIC DATA BOOK

Description: Increased activities in Cryogenic Engineering have brought about the need for a compilation of available data. The purpose of the Cryogenic Data Book is to provide a condensed source of reliable data and reference information for those working in the cryogenic field. Specifically the data were compiled with a view toward the design of liquid hydrogen bubble chambers.
Date: May 15, 1956
Creator: Engineerin, National Bureau of Standards. Cryogenic; Chelton, Dudley B.; Mann, Douglas B.; Byrns, R.A. & Hoard, H.S.
Partner: UNT Libraries Government Documents Department