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Results of Preliminary Flight Tests of the XS-1 Airplane (8-Percent Wing) to a Mach Number of 1.25

Description: Presents results of the U. S. Air Forces' accelerated transonic flight tests of the XS-1 No. 1 airplane for the Mach number range from 0.70 to 1.25 at altitudes from 30,000 to 49,000 feet. Data are included on horizontal-tail loads and buffeting, longitudinal trim changes, elevator effectiveness and control forces, and lateral trim characteristics.
Date: April 6, 1948
Creator: Williams, W C & Beeler, De E
Item Type: Report
Partner: UNT Libraries Government Documents Department

Results of recent experiments with slotted wings

Description: This report gives the results of a recent series of experiments performed on a wing designed for a cantilever monoplane. Both wings were trapezial in their ground plan, with their tips rounded elliptically. These wing sections combine all known devices for increasing the lift, namely, the slot, the increased camber and angle of attack by means of an aileron running the whole length of the span. The last advance included in the wing section was an increase in wing area by means of an auxiliary wing adjusted by a sort of rectangular joint.
Date: January 1, 1925
Creator: Lachmann, G
Item Type: Report
Partner: UNT Libraries Government Documents Department

Results of tests on radiators for aircraft engines

Description: Part 1 is to present the results of tests on 56 types of core in a form convenient for use in the study of the performance of and possible improvements in existing designs. Working rules are given by which the data contained in the report may be used, and the most obvious conclusions as to the behavior of cores are summarized. Part 2 presents the results of tests made to determine the pressure necessary to produce water flows up to 50 gallons per minute through an 8-inch square section of radiator core. These data are of special value in evaluating the hydraulic head against which the circulating pump is required to operate.
Date: January 1, 1920
Creator: Dickinson, H C; James, W S & Kleinschmidt, R V
Item Type: Report
Partner: UNT Libraries Government Documents Department

Results of Tests to Determine the Effect of a Conical Windshield on the Drag of a Bluff Body at Supersonic Speeds

Description: Tests to evaluate the effect of a conical windshield on the drag of a bluff body at supersonic speeds were performed for the following configurations: a sharp nose fuselage with stabilizing fins,a blunt nose fuselage with a hemispherical shape, and a blunt nose fuselage with a conical point. Results of the drag coeeficient are described at Mach 1.0 and the greatest Mach number of 1.37.
Date: January 14, 1947
Creator: Alexander, Sidney R.
Item Type: Report
Partner: UNT Libraries Government Documents Department

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

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.
Date: January 7, 1950
Creator: Mitchell, Jesse L. & Peck, Robert F.
Item Type: Report
Partner: UNT Libraries Government Documents Department

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

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.
Date: January 1, 1957
Creator: Lauten, William T., Jr. & Nelson, Herbert C.
Item Type: Report
Partner: UNT Libraries Government Documents Department

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

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.
Date: 1979
Creator: Strain, R. V. & Lambert, J. D. B.
Item Type: Report
Partner: UNT Libraries Government Documents Department

Resume and analysis of NACA lateral control research

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.
Date: January 1, 1937
Creator: Weick, Fred E. & Jones, Robert T.
Item Type: Report
Partner: UNT Libraries Government Documents Department

Resume of air-load data on slats and flaps

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.
Date: March 1, 1939
Creator: Wenzinger, Carl J. & Rogallo, Francis M.
Item Type: Report
Partner: UNT Libraries Government Documents Department

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

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.
Date: April 1, 1934
Creator: Wenzinger, Carl J.
Item Type: Report
Partner: UNT Libraries Government Documents Department

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

Description: From Scope of Report: "The purpose of this report is, therefore, to present in convenient form all the more important data accumulated in the course of the tests described, in order that the results may be readily accessible both to the Government officials having charge of the design, purchase, or care of power plants and to all persons interested in the development of the internal-combustion engine and the gas producer as means for utilizing the energy of fuels."
Date: 1911
Creator: Fernarld, R. H. & Smith, C. D.
Item Type: Report
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

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.
Date: July 1, 1922
Item Type: Report
Partner: UNT Libraries Government Documents Department

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

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.
Date: January 1, 1926
Creator: Ames, Joseph S
Item Type: Report
Partner: UNT Libraries Government Documents Department

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

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.
Date: April 1, 1921
Creator: Rateau, A
Item Type: Report
Partner: UNT Libraries Government Documents Department