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31
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25
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317 Matching Results
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Maneuverability investigation of the F6C-3 airplane with special flight instruments
"This investigation was made for the purpose of obtaining information on the maneuverability of the F6C-3 airplane. It is the first of a series of similar investigations to be conducted on a number of military airplanes for the purpose of comparing the abilities of these airplanes to maneuver, and also to establish a fund of quantitative data which may be used in formulating standards of comparison for rating the maneuverability of any airplane. A large part of this initial investigation was necessarily devoted to the development and trial of methods suitable for use in subsequent investigations of this nature" (p. 117).
Date:
May 23, 1930
Creator:
Dearborn, C. H. & Kirschbaum, H. W.
System:
The UNT Digital Library
Negative Thrust and Torque Characteristics of an Adjustable-Pitch Metal Propeller
This report presents the results of a series of negative thrust and torque measurements made with a 4 foot diameter model of a conventional aluminum-alloy propeller. The tests were made in the 20-foot propeller-research tunnel of the National Advisory Committee for Aeronautics. The results show that the negative thrust is considerably affected by the shape and size of the body behind the propeller, that the maximum negative thrust increases with decrease in blade-angle setting, and that the drag of a locked propeller may be greatly reduced by feathering it into the wind.
Date:
May 23, 1933
Creator:
Hartman, Edwin P.
System:
The UNT Digital Library
Improved airplane windshields to provide vision in stormy weather
This report presents the results of wind tunnel tests to determine possible improvements in the design of airplane windshields, particularly with respect to the pilot's vision from the cabin in stormy weather.
Date:
May 23, 1934
Creator:
Clay, William C.
System:
The UNT Digital Library
Analysis of Columbia River mud
This report is a copy of a letter sent on May 23, 1944, concerning the analytical evaluation of Columbia River water by Clinton Laboratories.
Date:
May 23, 1944
Creator:
Hoff, M. R.
System:
The UNT Digital Library
An Experimental Investigation of NACA Submerged-Duct Entrances
The results of an investigation of submerged-duct entrances are presented. It is shown that this type of entrance possesses the following characteristics: 1) very high-critical-compressibility speeds throughout the range of high-speed inlet velocity ratios; 2) very low pressure losses for the air entering the duct at all inlet-velocity ratios; and, 3) low external drag. These characteristics are obtained by the proper shaping of the contour of the upstream approach to the submerged inlets and by proper alignment of the duct lip. Design data are presented and the application of these data to a specific high-speed fighter-airplane design is discussed.
Date:
May 23, 1945
Creator:
Frick, Charles W.; Davis, Wallace F.; Randall, Lauros & Mossman, Emmet A.
System:
The UNT Digital Library
The Analysis of Impurities in Various Stages of Recycled Carbon Tetrachloride and Correlation with Chlorination Properties
The following report discusses findings resulting from experiments on recycled carbon tetrachloride at various stages of the proposed purification process.
Date:
May 23, 1946
Creator:
Hudson, R. L.; Burkhart, L. E. & Larson, C. E.
System:
The UNT Digital Library
Thin Oblique Airfoils at Supersonic Speed
"The well-known methods of thin-airfoil theory have been extended to oblique or sweptback airfoils of finite aspect ratio moving at supersonic speeds. The cases considered thus far are symmetrical airfoils at zero lift having plan forms bounded by straight lines. Because of the conical form of the elementary flow fields, the results are comparable in simplicity to the results of the two-dimensional thin-airfoil theory for subsonic speeds" (p. 267).
Date:
May 23, 1946
Creator:
Jones, Robert T.
System:
The UNT Digital Library
Aerodynamic Characteristics of a 42 Degree Swept-Back Wing With Aspect Ratio 4 and NACA 64(Sub 1)-112 Airfoil Sections at Reynolds Numbers From 1,700,000 to 9,500,000
Report discussing testing on a 42 degree swept-back wing to determine its low-speed aerodynamic characteristics in pitch and yaw at high Reynolds numbers. The main effect of increasing the Reynolds number was delayed wing stalling to higher angles of attack. Roughness on the wing leading edge also had a large adverse effect on lift, drag, and pitching-moment characteristics at higher Reynolds numbers.
Date:
May 23, 1947
Creator:
Neely, Robert H. & Conner, D. William
System:
The UNT Digital Library
Cooling Characteristics of the V-1650-7 Engine, 1, Coolant-Flow Distribution, Cylinder Temperatures, and Heat Rejections at Typical Operating Conditions
From Summary: "An investigation was conducted to determine the coolant-flow distribution, the cylinder temperatures, and the heat rejections of the V-1650-7 engine . The tests were run a t several power levels varying from minimum fuel consumption to war emergency power and at each power level the coolant flows corresponded to the extremes of those likely to be encountered in typical airplane installations, A mixture of 30-percent ethylene glycol and 70-percent water was used as the coolant. The temperature of each cylinder was measured between the exhaust valves, between the intake valves, in the center of the head, on the exhaust-valve guide, at the top of the barrel on the exhaust side, and on each exhaust spark-plug gasket."
Date:
May 23, 1947
Creator:
Povolny, John H. & Bogdan, Louis J.
System:
The UNT Digital Library
Low-speed wind-tunnel investigation of the longitudinal stability characteristics of a model equipped with a variable-sweep wing
Report presenting an investigation to determine the longitudinal stability characteristics of a complete model equipped with a variable-sweep wing at four different angles of sweepback. The primary objective was to study various wing modifications and an external-flap arrangement designed to minimize the shift in neutral point accompanying the change in sweep angle.
Date:
May 23, 1949
Creator:
Donlan, Charles J. & Sleeman, William C., Jr.
System:
The UNT Digital Library
Redox Committee: Conference notes, meeting of May 23, 1949
Discussions included the aluminum nitrate recovery process; specifications for process pumps; a review of the safety of the Redox process; plans for the proposed Waste Tank Farm, retention basin, diversion box, and cribs; and a request from the US AEC for a concise summary of the entire Redox program.
Date:
May 23, 1949
Creator:
Greager, O. H.; MacCready, W. K. & Seckendorff, E. W.
System:
The UNT Digital Library
An Investigation of a Supersonic Aircraft Configuration Having a Tapered Wing With Circular-Arc Sections and 40 Degree Sweepback: A Pressure-Distribution Study of the Aerodynamic Characteristics of the Wing at Mach Number 1.59
Memorandum presenting a pressure-distribution investigation of a wing of a complete supersonic aircraft configuration as conducted in the 4- by 4-foot supersonic tunnel at Mach number 1.59 based on the mean aerodynamic chord. The experimental life and drag coefficients were less than those predicted by linear theory. Results regarding section pressure characteristics, section characteristics, spanwise characteristics, and overall wing characteristics are provided.
Date:
May 23, 1950
Creator:
Cooper, Morton & Spearman, M. Leroy
System:
The UNT Digital Library
Rolling Effectiveness of a Thin Tapered Wing Having Partial-Span Ailerons as Determined by Rocket-Powered Test Vehicles
"The rolling effectiveness of a thin, tapered, and essentially unswept wing having outboard partial-span plain ailerons has been determined by means of rocket-powered test vehicles. The rolling power decreased abruptly in the Mach number range from 0.85 to 0.95 and more gradually at higher speeds. At the maximum Mach number of the tests (1.95), the rolling effectiveness was only 20 percent of that at a Mach number of 0.85" (p. 1).
Date:
May 23, 1950
Creator:
Sandahl, Carl A. & Strass, H. Kurt
System:
The UNT Digital Library
Comparison of Zero-Lift Drags Determined by Flight Tests at Transonic Speeds of Symmetrically Mounted Nacelles in Various Spanwise Positions on a 45 Degrees Sweptback Wing and Body Combination
Report presenting testing of rocket-powered models flown at transonic speeds to determine the effect of nacelle location on zero-lift drag. Low drag was obtained between M = 0.80 and M = 0.91 for all the nacelle positions investigated. Nacelles located at the wing tips gave the lowest drag, which was less than the drag of the combination without the nacelles over most of the speed range.
Date:
May 23, 1951
Creator:
Pepper, William B., Jr. & Hoffman, Sherwood
System:
The UNT Digital Library
Drag interference between a pointed cylindrical body and triangular wings of various aspect ratios at Mach numbers of 1.50 and 2.02
The drag of a body alone, six triangular wings of various aspect ratios, and the combinations were measured at Mach numbers of 1.50 and 2.02 at a Reynolds number of 5.5 million (based on the body length). The experimental drag-interference results were in accordance with calculations based on NACA RM A9E19, 1949, with skin-friction effects taken into account, the interference effect being principally the result of fixing transition on the body by adding a wing.
Date:
May 23, 1951
Creator:
Katzen, Elliott D. & Kaattari, George E.
System:
The UNT Digital Library
Review of some recent data on buffet boundaries
Report presenting a study of a large amount of data pertaining to high-speed buffet boundaries of various airplane configurations. The data indicate a strong influence of wing configuration on buffet boundaries. Results regarding low-lift buffeting, high-lift buffeting, buffet boundaries, and buffet intensity are provided.
Date:
May 23, 1951
Creator:
Purser, Paul E. & Wyss, John A.
System:
The UNT Digital Library
Effects of horizontal-tail position and aspect ratio on low-speed static longitudinal stability and control characteristics of a 60 degree triangular-wing model having twin triangular all-movable tails
Report presenting a low-speed investigation in the stability tunnel to determine the effects of tail height, length, and aspect ratio on the static longitudinal stability and control characteristics of a 60 degree triangular-wing model with twin triangular all-movable tails located near the wing tips.
Date:
May 23, 1952
Creator:
Jaquet, Byron M.
System:
The UNT Digital Library
Health-Physics Monthly Information Report. April 1952
None
Date:
May 23, 1952
Creator:
Bradley, J. E. & Burbage, J. J.
System:
The UNT Digital Library
Time-History Data of Maneuvers Performed by an F-86A Airplane During Squadron Operational Training
"Preliminary results of one phase of a control-motion study program are presented in the form of plots of load factor.and angular acceleration against indicated airspeed and of time histories of several measured quantities. The results were obtained from 197 maneuvers performed by an F-86A jet-fighter airplane during normal squadron operational training. Most of the tactical maneuvers of which the F-86A is capable were performed at pressure altitudes ranging from 0 to 32,000 feet and at indicated airspeeds ranging from 95 to 650 miles per hour" (p. 1).
Date:
May 23, 1952
Creator:
Henderson, Campbell; Thornton, James & Mayo, Alton
System:
The UNT Digital Library
25 Process Assistance. For Period of May 2, 1955 to May 13, 1955
None
Date:
May 23, 1955
Creator:
Culler, F L
System:
The UNT Digital Library
Axial-Flow Compressor Rotating-Stall and Rotor-Blade Vibration Survey
Report presenting a compressor-rotor-blade vibration survey on a production turbojet engine incorporating a 13-stage axial-flow compressor with a pressure ratio of approximately 7 and an air flow of 120 pounds per second. The investigation was conducted due to the major problem that fatigue failures of compressor rotor blades have caused in the development of the axial-flow compressor. Results regarding rotating stall characteristics, rotor-blade vibration, and fourth-stage rotor-blade failure are provided.
Date:
May 23, 1955
Creator:
Calvert, Howard F.; Medeiros, Arthur A. & Garrett, Floyd B.
System:
The UNT Digital Library
Equation of State of Water
A generalization of the Fermi-Thomas model for application of mixtures. This study attempts to determine the equation of state of water up to pressure of 10,000 megabars and temperatures of several thousand electron-volts.
Date:
May 23, 1955
Creator:
Latter, Albert L. & Latter, Richard
System:
The UNT Digital Library
Hanford Atomic Products Operation monthly report for April 1955
This document presents a summary of work and progress at the Hanford Engineer Works for April 1955. The report is divided into sections by department. A plant wide general summary is included at the beginning of the report, after which the departmental summaries begin. The Manufacturing Department reports plant statistics, and summaries for the Metal Preparation, Reactor and Separation sections. The Engineering Department`s section summarizes work for the Technical, Design, and Project Sections. Costs for the various departments are presented in the Financial Department`s summary. The Medical, Radiological Sciences, Utilities and General Services, Employee and Public Relations, and Community Real Estate and Services departments have sections presenting their monthly statistics, work, progress, and summaries.
Date:
May 23, 1955
Creator:
unknown
System:
The UNT Digital Library
Investigation of a high-pressure-ratio eight-stage axial-flow research compressor with two transonic inlet stages 5: preliminary analysis of over-all performance of modified compressor
Report presenting an investigation of the overall performance of a modified eight-stage axial-flow compressor as part of the investigation of the problems encountered in a high-pressure-ratio axial-flow compressor with transonic inlet stages. The maximum total pressure ratio obtained at design speed was 11.0 at an equivalent weight flow of 70.9 pounds per second with an adiabatic efficiency of 0.81. Results regarding modified compressor performance and comparison with predicted performance are provided.
Date:
May 23, 1955
Creator:
Standahar, Raymond M. & Geye, Richard P.
System:
The UNT Digital Library