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  Partner: UNT Libraries Government Documents Department
 Resource Type: Report
 Decade: 1950-1959
Some theoretical low-speed span loading characteristics of swept wings in roll and sideslip

Some theoretical low-speed span loading characteristics of swept wings in roll and sideslip

Date: January 1, 1950
Creator: Bird, John D
Description: The Weissinger method for determining additional span loading for incompressible flow is used to find the damping in roll, the lateral center of pressure of the rolling for wing plan forms of various aspect ratios, taper ratios, and sweep angles. In addition, the applicability of the method to the determination of certain other aerodynamic derivatives is investigated, and corrections for the first-order effects of compressibility are indicated. The agreement obtained between experimentally and theoretically determined values for the aerodynamic coefficients indicates that the method of Weissinger is well suited to the calculation of such resulting aerodynamic derivatives of wings as do not involve considerations of tip suction.
Contributing Partner: UNT Libraries Government Documents Department
Some Thermodynamic Properties of Freon-114

Some Thermodynamic Properties of Freon-114

Date: September 3, 1959
Creator: Van Wie, N. H. & Ebel, Robert A.
Description: Introduction: The thermodynamic properties of Freon-114 presented herein supplement those of Volume I and encompass a range of temperature above the critical to 400 F &176 F.
Contributing Partner: UNT Libraries Government Documents Department
Some torsional-damping measurements of laminated beams as applied to the propeller stall-flutter problem

Some torsional-damping measurements of laminated beams as applied to the propeller stall-flutter problem

Date: April 29, 1953
Creator: Heath, Atwood R , Jr
Description: The structural damping in the torsion mode of vibration of a series of untwisted, laminated thin beams simulating propeller blades is presented. The number of lamination were varied, as well as the bonding material and the method of joining lamination. Application of the data to the calculation of the minimum flutter speed of thin propeller blades indicates that appreciable gains in the minimum flutter speed may be obtained for laminated blades using a Cycleweld bond.
Contributing Partner: UNT Libraries Government Documents Department
Some transonic aerodynamic charcteristics of a model similar to the mcdonnell f3h-2n airplane

Some transonic aerodynamic charcteristics of a model similar to the mcdonnell f3h-2n airplane

Date: May 15, 1956
Creator: Crabill, N. L. & Jackson, B. G.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Some wind-tunnel experiments on single-degree-of-freedom flutter of ailerons in the high subsonic speed range

Some wind-tunnel experiments on single-degree-of-freedom flutter of ailerons in the high subsonic speed range

Date: June 1, 1956
Creator: Clevenson, Sherman A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Some wind-tunnel results of an investigation of the flutter of sweptback- and triangular-wing models at Mach number 1.3

Some wind-tunnel results of an investigation of the flutter of sweptback- and triangular-wing models at Mach number 1.3

Date: May 22, 1952
Creator: Tuovila, W J
Description: None
Contributing Partner: UNT Libraries Government Documents Department
A sonic-flow orifice probe for the in-flight measurements of temperature profiles of a jet engine exhaust with afterburning

A sonic-flow orifice probe for the in-flight measurements of temperature profiles of a jet engine exhaust with afterburning

Date: May 1, 1956
Creator: Havill, C Dewey & Rolls, L Stewart
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Sonic-flow-orifice temperature probe for high-gas-temperature measurements

Sonic-flow-orifice temperature probe for high-gas-temperature measurements

Date: September 1, 1950
Creator: Blackshear, Perry L , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Sound from a two-blade propeller at supersonic tip speeds

Sound from a two-blade propeller at supersonic tip speeds

Date: January 1, 1952
Creator: Hubbard, Harvey H & Lassiter, Leslie W
Description: Report presents the results of sound measurements at static conditions made for a two-blade 47-inch-diameter propeller in the tip Mach number range 0.75 to 1.30. For comparison, spectrums have been obtained at both subsonic and supersonic tip speeds. In addition, the measured data are compared with calculations by the theory of Gutin which has previously been found adequate for predicting the sound at subsonic tip speeds. Curves are presented from which the maximum over-all noise levels in free space may be estimated if the power, tip Mach number, and distance are known.
Contributing Partner: UNT Libraries Government Documents Department
Sound from a two-blade propeller at supersonic tip speeds

Sound from a two-blade propeller at supersonic tip speeds

Date: May 8, 1951
Creator: Hubbard, Harvey H & Lassiter, Leslie W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Sound measurements for five shrouded propellers at static conditions

Sound measurements for five shrouded propellers at static conditions

Date: April 1, 1950
Creator: Hubbard, Harvey H
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Sound propagation into the shadow zone in a temperature-stratified atmosphere above a plane boundary

Sound propagation into the shadow zone in a temperature-stratified atmosphere above a plane boundary

Date: October 1, 1955
Creator: Pridmore-Brown, David C & Ingard, Uno
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Source Strength Information for Shielding and Stack Effluent Calculations: a Standard Practices Guide

Source Strength Information for Shielding and Stack Effluent Calculations: a Standard Practices Guide

Date: October 3, 1958
Creator: Jones, L. H.
Description: Report presenting the curves and methods used "for determining gross fission product gamma energy in Mev/sec-watt, gross fission product beta decay in curies/sec-watt, delayed uranium fission neutrons in neutrons/sec-watt and N16 and N17 decay in photons/sec-cc of water" (p. 1).
Contributing Partner: UNT Libraries Government Documents Department
Space heating rates for some premixed turbulent propane-air flames

Space heating rates for some premixed turbulent propane-air flames

Date: June 1, 1956
Creator: Fine, Burton D & Wagner, Paul
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Spallation-Fission Competition in Heaviest Elements; Helium IonInduced Reactions in Plutonium Isotopes

Spallation-Fission Competition in Heaviest Elements; Helium IonInduced Reactions in Plutonium Isotopes

Date: June 1, 1956
Creator: Glass, Richard A.; Carr, Robert J.; Cobble, James W. & Seaborg,Glenn T.
Description: Excitation functions have been determined for the spallation and fission reactions induced in plutonium isotopes by 20 to 50 Mev helium ions. The method employed consisted of cyclotron bombardments of plutonium oxide followed by the chemical isolation and alpha or beta counting of radioactive reaction products. Formation cross sections are given where possible for the curium and americium spallation products corresponding to ({alpha},n), ({alpha},2n), ({alpha},3n), ({alpha},4n), ({alpha}5n), ({alpha},p), ({alpha},pn or d), ({alpha},p2n or t), and ({alpha},p3n) reactions in Pu{sup 238} , Pu{sup 239}, and Pu{sup 242}. Fission yield curves and fission cross sections for Pu{sup 238} and Pu{sup 239} serve to define the characteristics of the ({alpha},f) reaction for plutonium isotopes. Chemical procedures are outlined for the separation of both spallation and fission product elements in a sequence of operations performed on the entire dissolved target.
Contributing Partner: UNT Libraries Government Documents Department
Spallation-Fission Competition in Heaviest Elements; HeliumIon-Induced Reactions in Uranium Isotopes

Spallation-Fission Competition in Heaviest Elements; HeliumIon-Induced Reactions in Uranium Isotopes

Date: November 1, 1957
Creator: Vandenbosch, R.; Thomas, T.D.; Vandenbosch, S.E.; Glass, R.A. & Seaborg, G.T.
Description: A radiochemical study of fission and spallation products produced by bombardment of U{sup 233}, U{sup 235}, and U{sup 238} with 18-46 Mev helium ions has been made. As in the case of similar studies using isotopes of plutonium as targets, most of the reaction cross section is taken up by fission. Also, the pronounced increase of the total cross section for ({alpha},xn) reactions with increasing mass number of the target that was observed for plutonium targets is observed for uranium targets.
Contributing Partner: UNT Libraries Government Documents Department
Spallation-Fission Competition in Heaviest Elements; HeliumIon-Induced Reactions in Uranium Isotopes

Spallation-Fission Competition in Heaviest Elements; HeliumIon-Induced Reactions in Uranium Isotopes

Date: January 1, 1958
Creator: Vandenbosch, R.; Thomas, T.D.; Vandenbosch, S.E.; Glass, R.A. & Seaborg, G.T.
Description: A radiochemical study of fission and spallation products produced by bombardment of U{sup 233}, U{sup 235}, and U{sup 238} with 18-46 Mev helium ions has been made. As in the case of similar studies using isotopes of plutonium as targets, most of the reaction cross section is taken up by fission. Also, the pronounced increase of the total cross section for ({alpha},xn) reactions with increasing mass number of the target that was observed for plutonium targets is observed for uranium targets.
Contributing Partner: UNT Libraries Government Documents Department
Spallation-Fission Competition in Heaviest Elements; TritonProduction

Spallation-Fission Competition in Heaviest Elements; TritonProduction

Date: March 1, 1957
Creator: Wade, William H.; Gonzalez-Vidal, Jose; Glass, Richard A. & Seaborg, Glenn T.
Description: Stacked f o i l s of Au{sup 197}, Th{sup 232}, and U{sup 238} were bombarded, i n a series of experiments, with 48-Mev helium ions, 24-Mev deuterons, and 32-Mev protons. Tritium from each f o i l was collected and then measured by a gas-counting technique. The qualitative r e s u l t s indicate t h a t high-energy t r i t o n s are emitted i n r e l a t i v e l y large abundance from a l l targets and with each of the bombarding p a r t i c l e s . Cross sections f o r t r i t o n production from fissionable U 238 and Th{sup 232} and from non-f i s s ionable Au{sup 197} are comparable. The integrated (ci,t) cross sections thus determined for and 9lk-1' are nearly the same a s the integrated cross sections f o r the '(,pZn)' reactions as determined by measuring the yield of t h e product heavy isotopes i n radiochemical experiments. A l l of the f a c t s axe consistent with a picture of emission of high-energy t r ...
Contributing Partner: UNT Libraries Government Documents Department
Span load distribution resulting from constant vertical acceleration for thin sweptback tapered wings with streamwise tips

Span load distribution resulting from constant vertical acceleration for thin sweptback tapered wings with streamwise tips

Date: January 1, 1954
Creator: Cole, Isabella J & Margolis, Kenneth
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Span load distributions resulting from angle of attack, rolling, and pitching for tapered sweptback wings with streamwise tips

Span load distributions resulting from angle of attack, rolling, and pitching for tapered sweptback wings with streamwise tips

Date: July 1, 1952
Creator: Martin, John C & Jeffreys, Isabella
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Span load distributions resulting from constant angle of attack, steady rolling velocity, steady pitching velocity, and constant vertical acceleration for tapered sweptback wings with streamwise tips subsonic leading edges and supersonic trailing edg

Span load distributions resulting from constant angle of attack, steady rolling velocity, steady pitching velocity, and constant vertical acceleration for tapered sweptback wings with streamwise tips subsonic leading edges and supersonic trailing edg

Date: December 1, 1952
Creator: Hannah, Margery E & Margolis, Kenneth
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The spanwise distribution of lift for minimum induced drag of wings having a given lift and a given bending moment

The spanwise distribution of lift for minimum induced drag of wings having a given lift and a given bending moment

Date: December 1, 1950
Creator: Jones, R. T.
Description: The problem of the minimum induced drag of wings having a given lift and a given span is extended to include cases in which the bending moment to be supported by the wing is also given. The theory is limited to lifting surfaces traveling at subsonic speeds. It is found that the required shape of the downwash distribution can be obtained in an elementary way which is applicable to a variety of such problems. Expressions for the minimum drag and the corresponding spanwise load distributions are also given for the case in which the lift and the bending moment about the wing root are fixed while the span is allowed to vary. The results show a 15-percent reduction of the induced drag with a 15-percent increase in span as compared with results for an elliptically loaded wing having the same total lift and bending moment.
Contributing Partner: UNT Libraries Government Documents Department
The spanwise distribution of lift for minimum induced drag of wings having a given lift and a given bending moment

The spanwise distribution of lift for minimum induced drag of wings having a given lift and a given bending moment

Date: December 1, 1950
Creator: Jones, Robert Thomas
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Spanwise loading for wings and control surfaces of low aspect ratio

Spanwise loading for wings and control surfaces of low aspect ratio

Date: January 1, 1950
Creator: Deyoung, John
Description: None
Contributing Partner: UNT Libraries Government Documents Department