UNT Libraries Government Documents Department - 32,771 Matching Results

Search Results

prev Results: 19849 - 19872 next
open access

Variation of the pressure limits of flame propagation with tube diameter for propane-air mixtures

Description: An investigation was made of the variation of the pressure limits of flame propagation with tube diameter for quiescent propane with tube diameter for quiescent propane-air mixtures. Pressure limits were measured in glass tubes of six different inside diameters, with a precise apparatus. Critical diameters for flame propagation were calculated and the effect of pressure was determined. The critical diameters depended on the pressure to the -0.97 power for stoichiometric mixtures. The pressure d… more
Date: December 5, 1951
Creator: Belles, Frank E. & Simon, Dorothy M.
Item Type: Refine your search to only Report
open access

Recent data on controls

Description: "The accumulation of information on the characteristics of controls for high-speed airplanes has been rather rapid within recent months. In the present paper an attempt has been made to piece together some of this recent information in a form that might indicate the types of controls to be used advantageously on swept wings (both rigid and flexible), methods and gadgets for balancing trailing-edge flaps, and the characteristics of some all-movable tails" (p. 1).
Date: January 30, 1952
Creator: Stone, David G.
Item Type: Refine your search to only Report
open access

Wing load distribution on a swept wing airplane in flight at Mach numbers up to 1.11, and comparison with theory

Description: Report presenting flight tests to determine the pressure distribution over the wing of a swept-wing jet-propelled airplane over the flight range of lift coefficients for Mach numbers up to 1.11. Results regarding the section characteristics, load distribution, and trailing-edge loads are provided.
Date: April 14, 1952
Creator: Rolls, L. Stewart & Matteson, Frederick H.
Item Type: Refine your search to only Report
open access

Investigation of the liquid fluorine-liquid diborane propellant combination in a 100-pound-thrust rocket engine

Description: The experimental performance of liquid fluorine and liquid diborane was investigated in a 100-pound-thrust engine at a combustion pressure of 300 pounds per square inch absolute. Methods of handling and transporting liquid fluorine were developed. It was extremely difficult to obtain satisfactory operation because of the high flame speed and high combustion chamber temperatures. The maximum performance obtained was 280 pound seconds per pound, 88 percent of the theoretical maximum. The theoreti… more
Date: November 30, 1951
Creator: Ordin, Paul M.; Douglass, Howard W. & Rowe, William H.
Item Type: Refine your search to only Report
open access

Some Effects of Changing Solidity by Varying the Number of Blades on Performance of an Axial Flow Compressor Stage

Description: Report presenting an investigation to determine some of the basic problems and effects involved in a change of solidity accomplished by a change in the number of blades in an axial-flow-compressor rotor row and in a complete stage. Results regarding rotor performance and complete stage performance are provided.
Date: April 14, 1952
Creator: Standahar, Raymond M. & Serovy, George K.
Item Type: Refine your search to only Report
open access

Low-speed longitudinal characteristics of a 45 degrees sweptback wing of aspect ratio 8 with high-lift and stall-control devices at Reynolds numbers from 1,500,000 to 4,800,000

Description: Report presenting the low-speed longitudinal stability characteristics of a wing with 45 degrees of sweepback of the quarter-chord line, an aspect ratio of 8, a taper ratio of 0.45, and NACA 63(sub 1)A012 airfoil sections parallel to the air streams investigated in the 19-foot pressure tunnel. Results regarding the basic wing, wing with fences, wing with trailing-edge flaps, wing with leading-edge flaps, a combination of both flaps, fences with the flaps deflected, leading-edge roughness, and t… more
Date: February 28, 1952
Creator: Pratt, George L. & Shields, E. Rousseau
Item Type: Refine your search to only Report
open access

Longitudinal Stability and Drag Characteristics at Mach Numbers From 0.70 to 1.37 of Rocket-Propelled Models Having a Modified Triangular Wing

Description: "A modified triangular wing of aspect ratio 2.53 having an airfoil section 3.7 percent thick at the root and 5.98 percent thick at the tip was designed in an attempt to improve the lift and drag characteristics of triangular wings. Free-flight drag and stability tests were made using rocket-propelled models equipped with the modified wing. The Mach number range of the test was from 0.70 to 1.37" (p. 1).
Date: May 2, 1952
Creator: Chapman, Rowe, Jr. & Morrow, John D.
Item Type: Refine your search to only Report
open access

Fundamental Flame Velocities of Pure Hydrocarbons 3: Extension of Tube Method of High Flame Velocities - Acetylene-Air Mixtures

Description: Memorandum presenting an extension of the tube method of measuring flame velocities to fundamental flame velocities of 141 centimeters per second. The extension was accomplished by reducing the flame-tube diameter from 25 to 12.5 millimeters. Results regarding the gas flow and spatial flame velocity, flame surface area, and fundamental flame velocity are provided.
Date: December 3, 1951
Creator: Levine, Oscar & Gerstein, Melvin
Item Type: Refine your search to only Report
open access

Study of the physical properties of petrolatum-stabilized magnesium-hydrocarbon slurry fuels

Description: Magnesium-hydrocarbon slurries containing a moderate proportion of petrolatum have physical properties such that they offer promise as experimental aircraft fuels. The settling of the magnesium is greatly retarded by the petrolatum, and the slurries can easily be remixed to their original condition after storage. Successive batches which have closely similar properties can be prepared readily. The apparent viscosity of these slurries increased rapidly with increasing magnesium concentration, wi… more
Date: January 6, 1954
Creator: Pinns, Murray L. & Goodman, Irving A.
Item Type: Refine your search to only Report
open access

Preliminary investigation of the altitude performance of pentaborane and a pentaborane : JP-4 blend in an experimental 9.5-inch-diameter tubular combustor

Description: From Summary: "A preliminary investigation was conducted to determine the altitude performance of pentaborane and a blend fuel of 64.2 percent pentaborane in JP-4 fuel in a tubular combustor of a current production type turbojet engine. Deposits on the liner barrel and dome were virtually nonexistent. The combustion efficiency of 90 to 94 percent for pentaborane and approximately 90 percent for the blend. Outlet temperature profiles were marginal; however, the developed combustor provided lower… more
Date: April 1, 1957
Creator: Kaufman, Warner B. & Branstetter, J. Robert
Item Type: Refine your search to only Report
open access

Preliminary investigation of performance and starting characteristics of liquid fluorine: Liquid oxygen mixtures with jet fuel

Description: From Summary: "The performance of jet fuel with an oxidant mixture containing 70 percent liquid fluorine and 30 percent liquid oxygen by weight was investigated in a 500-pound-thrust engine operating at a chamber pressure of 300 pounds per square inch absolute. A one-oxidant-on-one-fuel skewed-hole impinging-jet injector was evaluated in a chamber of characteristic length equal to 50 inches. A maximum experimental specific impulse of 268 pound-seconds per pound was obtained at 25 percent fuel, … more
Date: January 6, 1954
Creator: Rothenberg, Edward A. & Ordin, Paul M.
Item Type: Refine your search to only Report
open access

Preliminary investigation of the combustion of a 50 percent pentaborane - 50 percent JP-4 fuel blend in a turbojet combustor at simulated altitude conditions

Description: A preliminary investigation was conducted to determine the combustion characteristics of a fuel composed of 50 percent pentaborane and 50 percent JP-4 (MIL-F-5624A) by weight in a turbojet combustor. A combustor designed to fit the housing of a J33-A-23 turbojet engine was selected for convenience. The fuel was evaluated at two engine conditions simulating altitudes of 40,000 and 57,000 feet, an engine speed of 85 percent of rated rpm, and a flight Mach number of 0.6. The pentaborane blend was … more
Date: March 11, 1957
Creator: Branstetter, J. Robert; Kaufman, Warner B. & Gibbs, James B.
Item Type: Refine your search to only Report
open access

Aerodynamics of slender bodies at Mach number of 3.12 and Reynolds numbers from 2 x 10(exp 6) to 15 x 10(exp 6) 4: aerodynamic characteristics of series of four bodies having near-parabolic noses and cylindrical afterbodies

Description: Pressure distributions and forces for a series of four bodies of revolution having nose-fineness ratios varying from 4 to 10 have been obtained and compared with theory for a Mach number of 3.12, a Reynolds number range of 2x10(sup)6 to 14x10(sup)6, and angles of attack from zero to 9 degrees. In general, a comparison of the experimental data with a second-order theory showed good agreement for the range of variables investigated.
Date: January 25, 1954
Creator: Jack, John R. & Moskowitz, Barry
Item Type: Refine your search to only Report
open access

Preliminary investigation of performance of variable-throat extended-plug-type nozzles over wide range of nozzle pressure ratios

Description: From Summary: "As part of an overall program for the experimental investigation of large-scale jet nozzles, a preliminary evaluation of the internal performance characteristics of several variable-throat extended-plug-type nozzles was obtained over a range of nozzle pressure rations from 2 to 15 with nozzle throat variations as great as 2:1. The extended-plug nozzle attained peak thrust coefficients as high as those which have been attained with fixed-geometry convergent-divergent nozzles. The … more
Date: February 5, 1954
Creator: Ciepluch, Carl C.; Krull, H. George & Steffen, Fred W.
Item Type: Refine your search to only Report
open access

Effect of Ice Formations on Section Drag of Swept NACA 63A-009 Airfoil With Partical-Span Leading-Edge Slat for Various Modes of Thermal Ice Protection

Description: Studies were made to determine the effect of ice formations on the section drag of a 6.9-foot-chord 36 degree swept NACA 63A-009 airfoil with partial-span leading-edge slat. In general, the icing of a thin swept airfoil will result in greater aerodynamic penalties than for a thick unswept airfoil. Glaze-ice formations at the leading edge of the airfoil caused large increases in section drag even at liquid-water content of 0.39 gram per cubic meter. The use of an ice-free parting strip in the st… more
Date: March 15, 1954
Creator: von Glahn, Uwe H. & Gray, Vernon H.
Item Type: Refine your search to only Report
open access

Altitude Wind Tunnel Investigation of High-Temperature Afterburners

Description: From Introduction: "During previous investigations of afterburning conducted at the NACA Lewis laboratory (references 1 to 4, for example), the objective of obtaining high exhaust-gas temperatures and, consequently, maximum thrust augmentation was compromised to some extent in order to alleviate the problem of afterburner shell cooling. The primary objective of the investigation reported herein was therefore the attainment of maximum exhaust-gas temperature imposed by the cooling techniques pre… more
Date: June 26, 1952
Creator: Conrad, E. William & Campbell, Carl E.
Item Type: Refine your search to only Report
open access

An Experimental Investigation of the Combustion Properties of a Hydrocarbon Fuel and Several Magnesium and Boron Slurries

Description: Memorandum presenting an investigation conducted to explore the characteristics of metal-hydrocarbon combustion, to determine the effect of fuel-air ratio on the combustion efficiency, and to determine how the metal and hydrocarbon separately contribute to the overall combustion of several slurries. Results regarding an evaluation of the sampling method, combustion efficiency, effective metal weight fraction, effective hydrogen-carbon ratio, and heat of combustion per pound of air are provided.
Date: April 28, 1952
Creator: Lord, Albert M.
Item Type: Refine your search to only Report
open access

An approximation to the effect of geometric dihedral on the rolling moment due to sideslip for wings at transonic and supersonic speeds

Description: Report presenting a simple geometric relation that allows the effect of geometric dihedral on the rolling moment due to sideslip at transonic and supersonic speeds to be estimated if the damping in roll or rolling moment due to differential wing incidence is known. There is no experimental information available to check certain equations, but the approximations look promising at this time.
Date: April 1952
Creator: Purser, Paul E.
Item Type: Refine your search to only Report
open access

Flight Determination of the Drag and Longitudinal Stability and Control Characteristics of a Rocket-Powered Model of a 60 Degrees Delta-Wing Airplane From Mach Numbers 0.75 to 1.70

Description: Report discussing an investigation to determine the aerodynamic characteristics of a model of a tailless delta-wing airplane configuration with a leading edge swept back 60 degrees at a range of Mach numbers. Information about lift-curve slope, buffeting, drag rise, hinge-moment coefficients, transonic trim, and stability is provided.
Date: November 29, 1951
Creator: Mitcham, Grady L.; Crabill, Norman L. & Stevens, Joseph E.
Item Type: Refine your search to only Report
open access

Gust-Tunnel Investigation of a Delta-Wing Model With the Leading Edge Swept Back 60 Degrees

Description: Report discussing an investigation of a delta-wing model with the leading edge swept back 60 degrees. Testing indicated that the gust load is greater than would be predicted by using a slope of the lift curve determined from steady-flow force tests. An aspect-ratio relation was determined for this type of wing with the selected apex angle, but it does not appear to be applicable to other wings with different apex angles.
Date: April 9, 1952
Creator: Pierce, Harold B. & Johns, Slaton L.
Item Type: Refine your search to only Report
open access

Flight Measurements at Mach Numbers From 1.1 to 1.9 of the Zero-Lift Drag of a Twin-Engine Supersonic Ram-Jet Configuration

Description: Report presenting a flight investigation to determine the zero-lift drag characteristics of a twin-engine supersonic ramjet configuration in order to make performance calculations below the design Mach number. Data was obtained over a range of Mach numbers for two power-off ramjet models with and without nacelles. Information about the variation of Reynolds number, total and external drag coefficients, and model-component drag coefficients is provided.
Date: June 23, 1952
Creator: Leiss, Abraham
Item Type: Refine your search to only Report
open access

Transonic Flight Tests to Compare the Zero-Lift Drags of 45 Degree Sweptback Wings of Aspect Ratio 3.55 and 6.0 With and Without Nacelles at the Wing Tips

Description: Report presenting tests of rocket-propelled models at transonic speeds to compare the zero-lift drags of 45 degree sweptback wings with and without solid nacelles at the wing tips. The wing drag coefficient was lowered at high subsonic and supersonic speeds when the aspect ratio was reduced from 6.0 to 3.55. Results regarding the favorability of the wing-tip nacelles and the force-break Mach number of the varying configurations are also provided.
Date: March 6, 1952
Creator: Hoffman, Sherwood & Mapp, Richard C., Jr.
Item Type: Refine your search to only Report
open access

Investigation of performance of several double-shroud ejectors and effect of variable-area exhaust nozzle on single ejector performance

Description: Report presenting an investigation to determine the characteristics of a double-shroud cooling-air ejector. The performance of a single-shroud ejector with a clamshell-type variable-area actuating nozzle was compared with that of an ejector having a conical nozzle. Results regarding the mechanics of ejector flow systems, effect of variable-area primary nozzle on ejector performance, double-shroud-ejector performance, and application of data are provided.
Date: July 15, 1952
Creator: Ellis, C. W.; Hollister, D. P. & Wilsted, H. D.
Item Type: Refine your search to only Report
open access

Wind-tunnel investigation of the aerodynamic characteristics in pitch of wing-fuselage combinations at high subsonic speeds: Aspect-ratio series

Description: Report presenting an investigation in the 7- by 10-foot tunnel to determine the effect of aspect ratio on the aerodynamic characteristics in pitch of wing-fuselage combinations with 45 degrees sweepback at the quarter-chord line and 0.6 taper ratio at high subsonic speeds. Results regarding the lift characteristics, pitching-moment characteristics, drag characteristics, and lift-drag ratios are provided.
Date: April 1, 1952
Creator: Kuhn, Richard E. & Wiggins, James W.
Item Type: Refine your search to only Report
Back to Top of Screen