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A Procedure for the Design of Air-Heated Ice-Prevention Systems

Description: A procedure proposed for use in the design of air-heated systems for the continuous prevention of ice formation on airplane components is set forth. Required heat-transfer and air-pressure-loss equations are presented, and methods of selecting appropriate meteorological conditions for flight over specified geographical areas and for the calculation of water-drop-impingement characteristics are suggested. In order to facilitate the design, a simple electrical analogue was devised which solves th… more
Date: June 1954
Creator: Neel, Carr B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effects of Ice Formations on Airplane Performance in Level Cruising Flight

Description: "A flight investigation in natural icing conditions was conducted by the NACA to determine the effect of ice accretion on airplane performance. The maximum loss in propeller efficiency encountered due to ice formation on the propeller blades was 19 percent. During 87 percent of the propeller icing encounters, losses of 10 percent or less were observed" (p. 1).
Date: May 1948
Creator: Preston, G. Merritt & Blackman, Calvin C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Icing Protection for a Turbojet Transport Airplane: Heating Requirements, Methods of Protection, and Performance Penalties

Description: "The problems associated with providing icing protection for the critical components of a typical turbojet transport airplane operating over a range of probable icing conditions are analyzed and discussed. Heating requirements for several thermal methods of protection are evaluated and the airplane performance penalties associated with providing this protection from various energy sources are assessed. The continuous heating requirements for icing protection and the associated airplane performa… more
Date: January 1953
Creator: Gelder, Thomas F.; Lewis, James P. & Koutz, Stanley L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Improvements in Heat Transfer for Anti-Icing of Gas-Heated Airfoils with Internal Fins and Partitions

Description: "The effect of modifying the gas passage of hollow metal airfoils by the addition of internal fins and partitions was experimentally investigated and comparisons were made among a basic unfinned airfoil section and two airfoil designs having metal fins attached at the leading edge of the internal gas passage. An analysis considering the effects of heat conduction in the airfoil metal was made to determine the internal modification effectiveness that may be obtained in gas-heated components, suc… more
Date: July 1950
Creator: Gray, Vernon H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Use of Truncated Flapped Airfoils for Impingement and Icing Tests of Full-Scale Leading-Edge Sections

Description: From Summary: "In an effort to increase the operational range of existing small icing tunnels, the use of truncated airfoil sections has been suggested. With truncated airfoils, large-scale or even full-scale wing-icing-protection systems could be evaluated. Therefore, experimental studies were conducted in the NACA Lewis laboratory icing tunnel with an NACA 651-212 airfoil section to determine the effect of truncating the airfoil chord on velocity distribution and impingement characteristics. … more
Date: July 24, 1956
Creator: von Glahn, Uwe H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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An Electric Thrust Meter Suitable for Flight Investigation of Propellers

Description: A lightweight instrument that utilizes resistance-wire electric strain gases to measure propeller-shaft thrust has been developed. A wind-tunnel investigation on a propeller installed, on a single-engine pursuit airplane showed that the instrument gave a reliable indication of propeller-shaft thrust to an accuracy of +/-2 percent within its calibrated range. No attempt was made to determine the relation of indicated shaft thrust to net propeller thrust.
Date: May 9, 1949
Creator: Perkins, Porter J., Jr. & Millenson, Morton B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Göttingen Wind Tunnel for Testing Aircraft Models

Description: Given here is a brief description of the Göttingen wind tunnel for the testing of aircraft models, preceded by a history of its development. Included are a number of diagrams illustrating, among other things, a sectional elevation of the wind tunnel, the pressure regulator, the entrance cone and method of supporting a model for simple drag tests, a three-component balance, and a propeller testing device, all of which are discussed in the text.
Date: November 1920
Creator: Prandtl, L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The Dynamometer Hub for the Testing Propellers and Engines During Flight

Description: The need for a device to measure flight resistance, engine and propeller power, and efficiency during flight grew in proportion to the demand for increased flying capacity in military types of aircraft. Here, a dynamometer hub was inserted between the engine and the propeller. Taken as a whole, the tests that were conducted show that though the dynamometer is a sensitive instrument liable to numerous derangements, it is undeniably useful even in its present form, when handled with care and skil… more
Date: July 1921
Creator: Enoch, O.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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A New Method of Testing in Wind Tunnels

Description: Now, in existing wind tunnels, using a horsepower of 100 to 300, the models are generally made to a 1/10 scale and the speed is appreciably lower than the speeds currently attained by airplanes. The Reynolds number realized is thus 15 to 25 times smaller than that reached by airplanes in free flight, while the ratio of speed to the velocity of sound is between a third and three quarters of the true ratio. The necessary increases in either the diameter of the wind tunnel or the velocity of the a… more
Date: August 1921
Creator: Margoulis, W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Flight Tests of the High-Speed Performance of a P-51B Airplane (AAF No. 43-12105)

Description: Report discussing testing to check the improvement of 3 or 4 miles per hour in the maximum speed of the P-51B airplane as a result of sealing the wing-gun access doors and flap-spar lightening holes. Large variations in speed were observed during testing, so additional testing and analysis was carried out to determine the effects of various factors that were suspected of contributing to the inconsistency of the plane's performance.
Date: December 18, 1944
Creator: Voglewede, T. J. & Danforth, E. C. B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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A Preliminary Investigation of a New Method for Testing Aerofoils in Free Flight

Description: "This report is a description of a new method of testing aerofoils in free flight devised by the National Advisory Committee for Aeronautics. The method consists in lowering below a flying airplane a large inverted aerofoil on three small steel wires in such a way that the lift on the aerofoil always keeps the wires tight. The resultant force is measured by the tension in the wires, and the direction of the resultant by the amount the wing trails backwards" (p. 1).
Date: January 1922
Creator: Norton, F. H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Extract From a Report on the Resistance of Spheres of Small Diameter in an Airstream of High Velocity

Description: Much attention is given here to the design of the wind tunnel and the experimental set-up. In comparing their results on the wind resistance of spheres to the results of other researchers, the authors find wide discrepancies. They are unable to explain the cause of the discrepancies, concluding, as they do, that the differing results could not be explained by the action of the wind tunnel walls.
Date: March 1921
Creator: Toussaint & Hayer
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Standardization and Aerodynamics

Description: Report presenting suggestions for the standardization of the study of aerodynamics in laboratories in the United States and Europe. A report by each of the different scientists, all of whom are working in a variety of different labs and countries, is provided, and each discusses the progress made in their respective labs and their suggestions for standardization and progress in the field.
Date: March 1923
Creator: Knight, William; Prandtl, L.; von Karman; Costanzi, G.; Margoulis, W.; Verduzio, R. et al.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

The Testing of Aviation Engines Under Approximate Altitude Conditions

Description: Note presenting a description of the aviation testing laboratory that has been built at the Bureau of Standards in order to test aviation engines under approximate engine conditions. A description of some of the calculations that are used to compare experimental and theoretical results are provided.
Date: December 1924
Creator: DuBois, R. N.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Experiments with a model water tunnel

Description: This report describes a model water tunnel built in 1928 by the NACA to investigate the possibility of using water tunnels for aerodynamic investigations at large scales. The model tunnel is similar to an open-throat wind tunnel, but uses water for the working fluid.
Date: December 1930
Creator: Jacobs, Eastman N. & Abbott, Ira H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Dynamic Similitude Between a Model and a Full-Scale Body for Model Investigation at Full-Scale Mach Number

Description: Note presenting an analysis for interpreting results of dynamic tests of a model investigated at full-scale Mach number in terms of the corresponding full-scale body. The analysis indicates that dynamic similarity for such a condition can be closely approximated although the effect of gravity is not to scale.
Date: March 1950
Creator: Neihouse, Anshal I. & Pepoon, Philip W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

An Investigation of Aircraft Heaters 34: Experimental Determination of Thermal and Hydrodynamical Behavior of Air Flowing Between a Flat and a Wave-Shaped Plate

Description: Report presenting an investigation of the thermal and hydrodynamical behavior of air flowing along a passage with one flat side, which was steam-heated, and one wave-shaped side, which was unheated. Two series of tests were conducted, one with the plates in direct opposition and one with the plates slightly separated, which induced turbulence upstream of the thermal boundary layer. Results regarding heat transfer and static-pressure drop are provided.
Date: August 1951
Creator: Boelter, L. M. K.; Sanders, V. D.; Young, G.; Morgan, M. & Morrin, E. H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

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 includ… more
Date: July 1922
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Method Rendering It Possible, in Testing Airplane Wing Models at the Eiffel Laboratory, to Obtain Comparable Polars, Whether the Supports Are Attached to the Upper or Lower Side of Model

Description: Report presenting an examination of the errors that result from testing an aircraft model and applying the results to full-sized airplanes. An investigation is carried out to determine how to obtain comparable polars regardless of whether the supports are attached to the upper or lower side of the model.
Date: November 1922
Creator: Eiffel, G.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Influence of refraction on the applicability of the Zehnder-Mach interferometer to studies of cooled boundary layers

Description: Report presenting an analytical investigation to determine the applicability of the Zehnder-Mach interferometer to two-dimensional cooled-boundary-layer studies. The main factor governing a test section design other than flow characteristics is the estimate of how close to the wall the boundary layer need be studied.
Date: September 1951
Creator: Kinsler, Martin R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Testing Airplanes in Flight: Determining Position of Resultant of Action of Air and Longitudinal Stability of an Airplane at Different Angles of Attack

Description: "Measurements made during flight with the triple recording device which gives the horizontal and vertical speeds of an airplane and the angle it makes with the horizon, render it possible to calculate its lift, its drag, and R the resultant of the action of the air both in magnitude and direction, but with these data alone, it is impossible to determine the position of this resultant in the plane of symmetry of the airplane. We will also see how we may determine the position of R during flight … more
Date: April 1922
Creator: Senouque, A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Note on similarity conditions for flows with heat transfer

Description: Report presenting an examination of the conditions for similarity of flow for a compressible fluid with heat transfer with particular reference to variation of stagnation temperature and scale of the model. Important simplification of the experimental procedure for tests simulating flight at high Mach number is possible by using the similarity relations developed in the report.
Date: April 1948
Creator: von Doenhoff, Albert E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Supersonic Nozzle Design

Description: "The theory of supersonic flow in nozzles is discussed, emphasis being placed on the physical rather than the mathematical point of view. Methods, both graphic and analytic, for designed nozzles are described together with a discussion of design factors. In addition, the analysis of given nozzle shapes to determine velocity distribution and possible existence of shock waves is considered" (p. 1).
Date: June 1948
Creator: Crown, J. Conrad
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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