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  Partner: UNT Libraries Government Documents Department
 Language: English
 Collection: Technical Report Archive and Image Library
Results 15391 - 15414 of 18,906
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High-altitude flight cooling investigation of a radial air-cooled engine

High-altitude flight cooling investigation of a radial air-cooled engine

Date: August 1, 1947
Creator: Manganiello, Eugene J; Valerino, Michael F & Bell, E Barton
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Exhaust-valve temperatures in a liquid-cooled aircraft-engine cylinder as affected by engine operating variables

Exhaust-valve temperatures in a liquid-cooled aircraft-engine cylinder as affected by engine operating variables

Date: February 1, 1947
Creator: Sutor, Alois T; Corrington, Lester C & Dudugjian, Carl
Description: None
Contributing Partner: UNT Libraries Government Documents Department
An Improved Continuous-Indicating Dew-Point Meter

An Improved Continuous-Indicating Dew-Point Meter

Date: February 1, 1947
Creator: Friswold, Frank A; Lewis, Ralph D; Wheeler, JR & Clyde, R
Description: None
Contributing Partner: UNT Libraries Government Documents Department
In-line aircraft-engine bearing loads III : main-bearing loads

In-line aircraft-engine bearing loads III : main-bearing loads

Date: February 1, 1947
Creator: Macks, E Fred & Shaw, Milton C
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The infrared spectra of spiropentane methylenecyclobutane and 2-methyl-1-butene

The infrared spectra of spiropentane methylenecyclobutane and 2-methyl-1-butene

Date: October 1, 1946
Creator: Cleaves, Alden P & Sherrick, Mildred E
Description: The infrared spectra of spiropentane, methylenecyclobutane, and 2-methyl-1-butene were measured in the region from 3 to 14 microns with a rock salt prism spectrometer of medium dispersion. The pure samples were prepared at the NACA Cleveland Laboratory. The vapors of these three C5 hydrocarbons were investigated at room temperature and at pressures in the range from 80 to 300 millimeters of mercury absolute in a 10-centimeter cell. The spectra were compared with each other and with Ramon spectra for the same compounds.
Contributing Partner: UNT Libraries Government Documents Department
An investigation of the effect of blade curvature on centrifugal-impeller performance

An investigation of the effect of blade curvature on centrifugal-impeller performance

Date: May 1, 1947
Creator: Anderson, Robert J & Ritter, William K
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Tank Tests to Show the Effect Rivet Heads on the Water Performance of a Seaplane-Float

Tank Tests to Show the Effect Rivet Heads on the Water Performance of a Seaplane-Float

Date: July 1938
Creator: Parkinson, J. B.
Description: A 1/3.5 full-sized model of a seaplane float constructed from lines supplied by the Bureau of Aeronautics, Navy Department, was tested first with smooth painted bottom surfaces and then with round-head rivets, plate laps, and keel plates fitted to simulate the actual bottom of a metal float. A percentage increase in water resistance caused by the added roughness was found to be from 5 to 20 percent at the hump speed and from 15 to 40 percent at high speeds. The effect of the roughness of the afterbody was found to be negligible except at high trims. The model data were extrapolated to full size by the usual method that assumes the forces to vary according to Froude's law and, in the case of the smooth model, by a method of separation that takes into account the effect of scale on the frictional resistance. It was concluded that the effect of rivet heads on the take-off performance of a relatively high-powered float seaplane is of little consequence, but it may be of greater importance in the case of more moderately powered flying boats.
Contributing Partner: UNT Libraries Government Documents Department
Tank tests of auxiliary vanes as a substitute for planing area

Tank tests of auxiliary vanes as a substitute for planing area

Date: February 1934
Creator: Parkinson, John B.
Description: The results of towing tests made on two models at the request of the Bureau of Aeronautics, Navy Department, are presented. The first model represents the hull of the U.S. Navy PN-8 flying boat, in which the sponsors of the original hull are removed and auxiliary lifting vanes are fitted at the chines immediately forward of the main step. The tests showed that the altered form gave a large increase in hump resistance and a very undesirable spray formation through a large part of the speed range.
Contributing Partner: UNT Libraries Government Documents Department
Tests of N-85, N-86 and N-87 airfoil sections in the 11-inch high speed wind tunnel

Tests of N-85, N-86 and N-87 airfoil sections in the 11-inch high speed wind tunnel

Date: September 1938
Creator: Stack, John & Lindsey, W. F.
Description: Three airfoils, the N-85, the N-86, and the N-87, were tested at the request of the Bureau of Aeronautics, Navy Department, to determine the suitability of these sections for use as propeller-blade sections. Further tests of the NACA 0009-64 airfoil were also made to measure the aerodynamic effect of thickening the trailing edge in accordance with current propeller practice. The N-86 and the N-87 airfoils appear to be nearly equivalent aerodynamically and both are superior to the N-85 airfoil. Comparison of those airfoils with the previously developed NACA 2409-34 airfoils indicate that the NACA 2409-34 is superior, particularly at high speeds. Thickening the trailing edge appears to have a detrimental effect, although the effect may be small if the trailing-edge radius is less than 0.5 percent of the cord. The N-86 and the N-87 airfoils appear to be nearly equivalent.
Contributing Partner: UNT Libraries Government Documents Department
Shear Lag in a Plywood Sheet-Stringer Combination Used for the Chord Member of a Box Beam

Shear Lag in a Plywood Sheet-Stringer Combination Used for the Chord Member of a Box Beam

Date: March 1, 1948
Creator: Borsari, Palamede & Yu, Ai-Ting
Description: Theoretical and experimental investigations were made of the distribution of strains in a plywood sheet-stringer combination used as the chord member of a box beam acted upon by bending loads. The theoretical solution was obtained with the help of the principle of minimum potential energy and certain simplifying assumptions. Strain measurements were made on a build-up box beam by means of electrical-resistance strain gages connected with strain indicators. A very satisfactory agreement between the theoretical and experimental strains was obtained.
Contributing Partner: UNT Libraries Government Documents Department
Empirical Relation Between Induced Velocity, Thrust, and Rate of Descent of a Helicopter Rotor as Determined by Wind-Tunnel Tests on Four Model Rotors

Empirical Relation Between Induced Velocity, Thrust, and Rate of Descent of a Helicopter Rotor as Determined by Wind-Tunnel Tests on Four Model Rotors

Date: October 1, 1951
Creator: Castles, Walter, Jr & Gray, Robin B
Description: The empirical relation between the induced velocity, thrust, and rate of vertical descent of a helicopter rotor was calculated from wind tunnel force tests on four model rotors by the application of blade-element theory to the measured values of the thrust, torque, blade angle, and equivalent free-stream rate of descent. The model tests covered the useful range of C(sub t)/sigma(sub e) (where C(sub t) is the thrust coefficient and sigma(sub e) is the effective solidity) and the range of vertical descent from hovering to descent velocities slightly greater than those for autorotation. The three bladed models, each of which had an effective solidity of 0.05 and NACA 0015 blade airfoil sections, were as follows: (1) constant-chord, untwisted blades of 3-ft radius; (2) untwisted blades of 3-ft radius having a 3/1 taper; (3) constant-chord blades of 3-ft radius having a linear twist of 12 degrees (washout) from axis of rotation to tip; and (4) constant-chord, untwisted blades of 2-ft radius. Because of the incorporation of a correction for blade dynamic twist and the use of a method of measuring the approximate equivalent free-stream velocity, it is believed that the data obtained from this program are more applicable to free-flight calculations than ...
Contributing Partner: UNT Libraries Government Documents Department
Calculation of transonic flows past thin airfoils by integral method

Calculation of transonic flows past thin airfoils by integral method

Date: July 1, 1950
Creator: Perl, William
Description: None
Contributing Partner: UNT Libraries Government Documents Department
An approximate method of determining the subsonic flow in an arbitrary stream filament of revolution cut by arbitrary turbomachine blades

An approximate method of determining the subsonic flow in an arbitrary stream filament of revolution cut by arbitrary turbomachine blades

Date: June 1, 1952
Creator: Wu, Chung-Hua; Brown, Curtis A & Prian, Vasily D
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Chart for simplifying calculations of pressure drop of a high-speed compressible fluid under simultaneous action of friction and heat transfer - application to combustion-chamber cooling passages

Chart for simplifying calculations of pressure drop of a high-speed compressible fluid under simultaneous action of friction and heat transfer - application to combustion-chamber cooling passages

Date: March 1, 1950
Creator: Sibulkin, Merwin & Koffel, William K
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Charts for the analysis of one-dimensional steady compressible flow

Charts for the analysis of one-dimensional steady compressible flow

Date: January 1, 1948
Creator: Turner, L Richard; Addie, Albert N & Zimmerman, Richard H
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Charts for estimating downwash behind rectangular, trapezoidal, and triangular wings at supersonic speeds

Charts for estimating downwash behind rectangular, trapezoidal, and triangular wings at supersonic speeds

Date: August 1, 1950
Creator: Haefeli, Rudolph C; Mirels, Harold & Cummings, John L
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Charts for the computation of equilibrium composition of chemical reactions in the carbon-hydrogen-oxygen-nitrogen system at temperatures from 2000 to 5000 K

Charts for the computation of equilibrium composition of chemical reactions in the carbon-hydrogen-oxygen-nitrogen system at temperatures from 2000 to 5000 K

Date: July 1, 1948
Creator: Huff, Vearl N & Calvert, Clyde S
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Charts of thermodynamic properties of air and combustion products from 300 degrees to 3500 degrees R

Charts of thermodynamic properties of air and combustion products from 300 degrees to 3500 degrees R

Date: April 1, 1950
Creator: English, Robert E & Wachtl, William W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effect of heat-capacity lag on a variety of turbine-nozzle flow processes

Effect of heat-capacity lag on a variety of turbine-nozzle flow processes

Date: October 1, 1950
Creator: Spooner, Robert B
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effect of heat and power extraction on turbojet-engine performance III : analytical determination of effects of shaft-power extraction

Effect of heat and power extraction on turbojet-engine performance III : analytical determination of effects of shaft-power extraction

Date: October 1, 1950
Creator: Koutz, Stanley L; Hensley, Reece V & Rom, Frank E
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effect of humidity on performance of turbojet engines

Effect of humidity on performance of turbojet engines

Date: June 1, 1950
Creator: Samuels, John C & Gale, B M
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effect of hydrocarbon type and chain length on uniform flame movement in quiescent fuel-air mixtures

Effect of hydrocarbon type and chain length on uniform flame movement in quiescent fuel-air mixtures

Date: June 1, 1948
Creator: Reynolds, Thaine W & Ebersole, Earl R
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effect of heat and power extraction on turbojet-engine performance I : analytical method of performance evaluation with compressor-outlet air bleed

Effect of heat and power extraction on turbojet-engine performance I : analytical method of performance evaluation with compressor-outlet air bleed

Date: March 1, 1950
Creator: Hensley, Reece V; Rom, Frank E & Koutz, Stanley L
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effect of heat and power extraction on turbojet-engine performance II : effect of compressor-outlet air bleed for specific modes of engine operation

Effect of heat and power extraction on turbojet-engine performance II : effect of compressor-outlet air bleed for specific modes of engine operation

Date: August 1, 1950
Creator: Rom, Frank E & Koutz, Stanley L
Description: None
Contributing Partner: UNT Libraries Government Documents Department