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  Partner: UNT Libraries Government Documents Department
 Collection: Technical Report Archive and Image Library
Results of the flight test of a 0.13-scale rocket-boosted model of the McDonnell F4H-1 airplane between Mach numbers of 0.20 and 1.90 : TED No. NACA AD 3115

Results of the flight test of a 0.13-scale rocket-boosted model of the McDonnell F4H-1 airplane between Mach numbers of 0.20 and 1.90 : TED No. NACA AD 3115

Date: November 8, 1957
Creator: Hastings, Earl C , Jr & Dickens, Waldo L
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Results of the Flight Test of a Dummy of the MX-656 Rocket-Propelled Models

Results of the Flight Test of a Dummy of the MX-656 Rocket-Propelled Models

Date: January 7, 1950
Creator: Mitchell, Jesse L. & Peck, Robert F.
Description: The data obtained from the flight of a simplified (dummy) rocket-propelled model of the MX-656 have been analyzed to determine the booster-model characteristics and the model-alone characteristics up to a Mach number of 1.3. The data indicate that the model-booster combination is satisfactory. The model alone is longitudinally stable i n the Mach number range covered by the test (0.9 to 1.3) with the center of gravity at -15 percent of the mean aerodynamic chord. With the stabilizer setting at 0 deg. the variation of normal-force coefficient with Mach number is not large. The total-drag-coefficient variation with Mach number is not unusual. About 12 percent of the total drag at a Mach number of 1.3 can be attributed to body base drag.
Contributing Partner: UNT Libraries Government Documents Department
Results of two free-fall experiments on flutter of thin unswept wings in the transonic speed range

Results of two free-fall experiments on flutter of thin unswept wings in the transonic speed range

Date: January 1, 1957
Creator: Lauten, William T , Jr & Nelson, Herbert C
Description: Results of four thin, unswept, flutter airfoils attached to two freely falling bodies are reported. Two airfoils fluttered at a Mach number of 0.85, a third airfoil fluttered at a Mach number of 1.03, and a fourth fluttered at a Mach number of 1.07. Results of calculations of flutter speed using incompressible and compressible air-force coefficients, including a Mach number of 1.0, are presented.
Contributing Partner: UNT Libraries Government Documents Department
Results of UO₂ Diagnositic Tests for Run Beyond Cladding Breach in EBR-2

Results of UO₂ Diagnositic Tests for Run Beyond Cladding Breach in EBR-2

Date: 1979
Creator: Strain, R. V. & Lambert, J. D. B.
Description: Pre-defected uranium dioxide fuel elements were irradiated in EBR-II to determine the response of the fission-product-monitoring systems. In particular, the tests were performed to indicate whether the amount of oxide fuel exposed to the primary sodium could be estimated by monitoring, with the fuel-element-rupture detector (FERD), delayed neutrons (DN's) emitted from bromine and iodine isotopes in the sodium. Elements with defect areas of 0.005 and 0.20 cm sq. were irradiated consecutively in April and June 1977. Post-irradiation examination of the elements showed that an unexpectedly large amount of uranium dioxide/sodium chemical reaction occurred in the element with the 0.20-cm sq. defect.
Contributing Partner: UNT Libraries Government Documents Department
The results of wind-tunnel tests at low speeds of a four-engine propeller-driven airplane configuration having a wing with 40 degrees of sweepback and an aspect ratio of 10

The results of wind-tunnel tests at low speeds of a four-engine propeller-driven airplane configuration having a wing with 40 degrees of sweepback and an aspect ratio of 10

Date: December 21, 1953
Creator: Edwards, George G; Buell, Donald A & Dickson, Jerald K
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The results of wind-tunnel tests to a Mach number of 0.90 of a four-engine, propeller-driven airplane configuration having a wing with 40 degrees of sweepback and an aspect ratio of 10

The results of wind-tunnel tests to a Mach number of 0.90 of a four-engine, propeller-driven airplane configuration having a wing with 40 degrees of sweepback and an aspect ratio of 10

Date: September 1, 1956
Creator: Edwards, George G; Dickson, Jerald K; Sutton, Fred B & Demele, Frank A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Resume and analysis of NACA lateral control research

Resume and analysis of NACA lateral control research

Date: January 1, 1937
Creator: Weick, Fred E & Jones, Robert T
Description: An analysis of the principal results of recent NACA lateral control research is made by utilizing the experience and progress gained during the course of the investigation. Two things are considered of primary importance in judging the effectiveness of different control devices: the (calculated) banking and yawing motion of a typical small airplane caused by a deflection of the control, and the stick force required to produce this deflection. The report includes a table in which a number of different lateral control devices are compared on these bases.
Contributing Partner: UNT Libraries Government Documents Department
Resume of air-load data on slats and flaps

Resume of air-load data on slats and flaps

Date: March 1, 1939
Creator: Wenzinger, Carl J & Rogallo, Francis M
Description: A resume of the generally available test data regarding air loads on slats and flaps is presented and data attained up to the fall of 1938 are included. The data are given in the form of N.A.C.A. standard coefficients of air forces and moments on the lift-increasing device and, when available, the aerodynamic characteristics of the combined wing and high-lift device are included. Slats of the Handley Page type, fixed auxiliary airfoils, and flaps of several different types are covered.
Contributing Partner: UNT Libraries Government Documents Department
Resume of hinge-moment data for unshielded horn- balanced control surfaces

Resume of hinge-moment data for unshielded horn- balanced control surfaces

Date: June 1, 1943
Creator: Lowry, John G
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Resume of NACA stability and control tests of the Bell P-63 series airplane

Resume of NACA stability and control tests of the Bell P-63 series airplane

Date: October 1, 1944
Creator: Johnson, Harold I
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Resume of Present Data on Load Distribution on Slots and Flaps, Special Report

Resume of Present Data on Load Distribution on Slots and Flaps, Special Report

Date: April 1, 1934
Creator: Wenzinger, Carl J.
Description: This report covers a study of the generally available data on load distribution on slots and flaps. The study was made by the National Advisory Committee for Aeronautics at the request of the Material Division, Army Air Corps to furnish information applicable to design criteria for slots and flaps of various types. The data are presented in three main sections: slots (Handley page type), auxiliary airfoils (fixed), and flaps.
Contributing Partner: UNT Libraries Government Documents Department
Resume of Producer-Gas Investigations: October 1, 1904-June 30, 1910

Resume of Producer-Gas Investigations: October 1, 1904-June 30, 1910

Date: 1911
Creator: Fernarld, R. H. & Smith, C. D.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Resume of the activities of the Aeronautical Experimental Institute, Rome, during the months of May, June, July and August 1921

Resume of the activities of the Aeronautical Experimental Institute, Rome, during the months of May, June, July and August 1921

Date: July 1, 1922
Creator: unknown
Description: This report is a listing of the different studies conducted by the Institute in May thru August of 1921. The aerodynamical section studied: the aerodynamical characteristics of a very thick concave-convex wing; the disturbance caused in a tunnel by the presence of a disk, placed in relation with a transversely infinite barrier; vertical pressure in a wing of low head resistance; the drag caused by two small doors in the sides of the fuselage. Some other studies conducted by the Institute included: depressions in the interior of the model of a wing; the influence of a conical casing fitted with helicoidal flanges centered on the hub of the propeller; the influence of the velocity of translation on the aerodynamical effects of the propeller; and the influence of a honeycomb placed in the tunnel.
Contributing Partner: UNT Libraries Government Documents Department
A resume of the advances in theoretical aeronautics made by Max M. Munk

A resume of the advances in theoretical aeronautics made by Max M. Munk

Date: January 1, 1926
Creator: Ames, Joseph S
Description: In order to apply profitably the mathematical methods of hydrodynamics to aeronautical problems, it is necessary to make simplifications in the physical conditions of the latter. To begin with, it is allowable in many problems, as Prandtl has so successfully shown, to treat the air as having constant density and as free of viscosity. But this is not sufficient. It is also necessary to specify certain shapes for the solid bodies whose motion through the air is discussed, shapes suggested by the actual solids - airships or airfoils - it is true, but so chosen that they lead to solvable problems. In a valuable paper presented by Dr. Max M. Munk, of the National Advisory Committee for Aeronautics, Washington, to the Delft Conference in April, 1924, these necessary simplifying assumptions are discussed in detail. It is the purpose of the present paper to present in as simple a manner as possible some of the interesting results obtained by Dr. Munk's methods.
Contributing Partner: UNT Libraries Government Documents Department
Resume of the theory of naval and aerial propulsive propellers and of airplanes in the rectilinear flight

Resume of the theory of naval and aerial propulsive propellers and of airplanes in the rectilinear flight

Date: April 1, 1921
Creator: Rateau, A
Description: Though dissimilar, these two subjects have been united because they have some points in common. The computation of the movement of an airplane can only be correctly established if we are in a position to know exactly the thrust and resisting torque of the propeller for the various values of slip, which may vary greatly according to circumstance. The first part of the work concerns propellers and introduces as a fundamental variable, the true slip (delta) with respect to the effective pitch, which is the advance per revolution of the propeller corresponding to no thrust. The second part deals with characteristic curves of an airplane.
Contributing Partner: UNT Libraries Government Documents Department
Resume of wind-tunnel data on the effect of external stores on stability of models of military airplanes

Resume of wind-tunnel data on the effect of external stores on stability of models of military airplanes

Date: December 19, 1946
Creator: Silvers, H Norman & Vogler, Raymond D
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Retrogressive Failures in Sand Deposits of the Mississippi River, Report 1: Field Investigations, Laboratory Studies and Analysis of the Hypothesized Failure Mechanism

Retrogressive Failures in Sand Deposits of the Mississippi River, Report 1: Field Investigations, Laboratory Studies and Analysis of the Hypothesized Failure Mechanism

Date: June 1988
Creator: Torrey, Victor H., III; Dunbar, Joseph B. & Peterson, Richard W.
Description: First report regarding geotechnical field investigations meant to apply current state-of-the-art knowledge and methods to assessing the in situ characteristics of susceptible point bar deposits below Baton Rouge.
Contributing Partner: UNT Libraries Government Documents Department
Retrogressive Failures in Sand Deposits of the Mississippi River, Report 2: Empirical Evidence in Support of the Hypothesized Failure Mechanism and Development of the Levee Safety Flow Slide Monitoring System

Retrogressive Failures in Sand Deposits of the Mississippi River, Report 2: Empirical Evidence in Support of the Hypothesized Failure Mechanism and Development of the Levee Safety Flow Slide Monitoring System

Date: June 1988
Creator: Torrey, Victor H., III
Description: This report represents a continuation of efforts by the Lower Mississippi Valley Division (LMVD), US Army Corps of Engineers, to develop an effective plan for and means of protecting the integrity of main line Mississippi River levees from the threat of flow slides in sand deposits.
Contributing Partner: UNT Libraries Government Documents Department
Reuse and Subsurface Injection of Municipal Sewage Effluent: Two Case Histories

Reuse and Subsurface Injection of Municipal Sewage Effluent: Two Case Histories

Date: 1971
Creator: Donaldson, Erle C. & Bayazeed, Abdo F.
Description: Report issued by the U.S. Bureau of Mines discussing sewage disposal and reuse. As stated in the introduction, "this paper describes the renovation of municipal sewage water for industrial use, and the use of subsurface waste disposal by an industrial complex and by a city" (p. 1). This report includes tables, and illustrations.
Contributing Partner: UNT Libraries Government Documents Department
Reverse Osmosis for Water Desalination

Reverse Osmosis for Water Desalination

Date: May 22, 1964
Creator: Lonsdale, H. K.; Merten, U.; Riley, R. L.; Vos, K. D. & Westmoreland, J. C.
Description: Report issued by the Office of Saline Water over studies conducted on the reverse-osmosis program. The methods of desalination through osmosis are discussed. This report includes tables, illustrations, and photographs.
Contributing Partner: UNT Libraries Government Documents Department
The reversibility theorem for thin airfoils in subsonic and supersonic flow

The reversibility theorem for thin airfoils in subsonic and supersonic flow

Date: January 1, 1950
Creator: Brown, Clinton E
Description: A method introduced by Munk is extended to prove that the light-curve slope of thin wings in either subsonic flow or supersonic flow is the same when the direction of flight of the wing is reversed. It is also shown that the wing reversal does not change the thickness drag, damping-in-roll parameter or the damping-in-pitch parameter.
Contributing Partner: UNT Libraries Government Documents Department
A Review and Analysis of Fortran 8x

A Review and Analysis of Fortran 8x

Date: October 1987
Creator: Smith, Brian T.
Description: The ANSI Standards Subcommittee X3J3 on Fortran has recently completed a draft proposed standard for the Fortran programming language. The draft proposed standard, known informally as Fortran 8x, is a revision of the current standard X3.9-1978, known informally as Fortran 77. This report is a review of Fortran 8x and consists of a series of six articles. The first article gives a general overview of Fortran 8x. The next three articles give brief discussions of the array facilities; the enhanced numeric facilities; and user-defined data types, procedure interfaces, and the new program unit called a module. The fifth article provides a brief analysis of the controversial issues discussed by X3J3 (including both the accepted and rejected facilities for Fortran 8x). The sixth article gives a brief comparison with Ada. The report concludes with a summary giving information on how and where to express opinions of the draft proposed standard.
Contributing Partner: UNT Libraries Government Documents Department
Review and Analysis of Spray Combustion as Related to Alternative Fuels

Review and Analysis of Spray Combustion as Related to Alternative Fuels

Date: September 1979
Creator: Black, C. H.; Chiu, H. H.; Fischer, J. & Clinch, J. M.
Description: A review was conducted during the period of mid-June to mid-August 1979, of the literature on spray combustion. Particular attention has been paid to theoretical and experimental work on droplet and spray combustion applicable to the use of alternate fuels, mainly liquid fuels derived from coal and shale.
Contributing Partner: UNT Libraries Government Documents Department
Review and Evaluation of Extractants for Strontium Removal Using Magnetically Assisted Chemical Separation

Review and Evaluation of Extractants for Strontium Removal Using Magnetically Assisted Chemical Separation

Date: November 1995
Creator: Bauer, C. B.; Rogers, R. D.; Nuñez, Luis; Ziemer, M. D.; Pleune, T. T. & Vandegrift, G. F.
Description: A literature review on extractants for strontium removal was initially performed at Northern Illinois University to assess their potential in magnetically assisted chemical separation. A series of potential strontium extractants was systematically evaluated there using radioanalytical methods. Initial experiments were designed to test the uptake of strontium from nitric acid using several samples of magnetic extractant particles that were coated with various crown ether ligands. High partition coefficient (K(sub d)) values for stimulant tank waste were obtained. Further studies demonstrated that the large partitioning was due to uncoated particles.
Contributing Partner: UNT Libraries Government Documents Department