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An investigation of the drag of windshields in the 8-foot high-speed wind tunnel

Description: Report presents the results of tests made to determine the drag of closed-cockpit and transport-type windshields. The tests were made at speeds corresponding to a Mach number range of approximately 0.25 to 0.58 in the NACA 8-foot high-speed wind tunnel. This speed range corresponds to a test Reynolds number range of 2,510,000 to 4,830,000 based on the mean aerodynamic chord of the full-span model (17.29 in.). The shapes of the windshield proper, the hood, and the tail fairing were systematically varied to include common types and refined design.
Date: May 22, 1939
Creator: Robinson, Russell G. & Delano, James B.
Partner: UNT Libraries Government Documents Department
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The Drag of Airplane Radiators With Special Reference to Air Heating (Comparison of Theory and Experiment)

Description: This report contains a survey of past radiator research. This report also is intended as a systematic comparison of theoretical and experimental radiator drag, with the object of ascertaining the most important loss sources and their interaction in different cases of installation, and to separate the radiator systems which are amenable to calculation, both as regards axial flow and drag. The sources of loss due to the diffuser are to be looked into closely as in many cases they can be of preeminent magnitude and their customary appraisal, according to Fliegner's formula, does not meet actual conditions.
Date: May 1939
Creator: Göthert, B.
Partner: UNT Libraries Government Documents Department
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An Experimental Investigation of the Normal Acceleration of an Airplane Model in a Gust

Description: Note presenting an investigation in the gust tunnel to determine the influence of airplane wing loading, forward velocity, wing plan form, and the fuselage on the reaction of the airplane to a known gust. Tests were made for four values of gust velocity and for two gust gradients, specifically the sharp-edge gust and a gust rising linearly to full strength in a distance of several chord lengths.
Date: May 1939
Creator: Donely, Philip
Partner: UNT Libraries Government Documents Department
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Experiments on the Recovery of Waste Heat in Cooling Ducts, Special Report

Description: Tests have been conducted in the N.A.C.A. full-scale wind tunnel to investigate the partial recovery of the heat energy which is apparently wasted in the cooling of aircraft engines. The results indicate that if the radiator is located in an expanded duct, a part of the energy lost in cooling is recovered; however, the energy recovery is not of practical importance up to airplane speeds of 400 miles per hour. Throttling of the duct flow occurs with heated radiators and must be considered in designing the duct outlets from data obtained with cold radiators in the ducts.
Date: May 1939
Creator: Silverstein, Abe
Partner: UNT Libraries Government Documents Department
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Greenhouse tomatoes.

Description: Describes the benefits of growing tomatoes in greenhouses for improved quality and marketability. Discusses requirements and methods for successfully growing greenhouse tomatoes.
Date: May 1939
Creator: Beattie, James H. (James Herbert), b. 1882
Partner: UNT Libraries Government Documents Department
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The Power of Aircraft Engines at Altitude

Description: The subject of the present paper is confined to the investigations and methods employed by the Fiat company in their studies on the altitude performance of an air-cooled engine of the production type. The experimental set-up as well as test engine data are provided.
Date: May 1939
Creator: Ragazzi, Paolo
Partner: UNT Libraries Government Documents Department
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Radiator Design and Installation

Description: "The fundamental principles of fluid flow, pressure losses, and heat transfer have been presented and analyzed for the case of a smooth tube with fully developed turbulent flow. These equations apply to tubes with large length-diameter ratios where the flow is at a high Reynolds Number. The error introduced by using these equations increases as the magnitude of the tube length and the air-flow Reynolds Number approaches the values encountered in modern radiator designs" (p. 1).
Date: May 1939
Creator: Brevoort, M. J. & Leifer, M.
Partner: UNT Libraries Government Documents Department
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A semi-graphical method for analyzing strains measured on three or four gage lines intersecting at 45 degrees

Description: Report presenting a method for analyzing strains measured on three or four gage lines intersecting at 45 degrees, which helps determine the state of stress at a point on a plane. An equation for adjustment factor and a master curve is provided, which can be memorized and easily used in the future.
Date: May 1939
Creator: Hill, H. N.
Partner: UNT Libraries Government Documents Department
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A simplified method for the calculation of airfoil pressure distribution

Description: From Summary: "A method is presented for the rapid calculation of the pressure distribution over an airfoil section when the normal-force distribution and the pressure distribution over the "base profile" (i.e., the profile of the same airfoil were the camber line straight and the resulting airfoil at zero angle of attack) are known. This note is intended as a supplement to N.A.C.A. Report Nos. 631 and 634 wherein methods are presented for the calculation of the normal-force distribution over plain and flapped airfoils, respectively, but not of the pressures on the individual surfaces. Base-profile pressure-coefficient distributions for the usual N.A.C.A. family of airfoils, which are also suitable for several other commonly employed airfoils, are included in tabular form. With these tabulated base-profile pressures and the computed normal-force distributions, pressure distributions adequate for most engineering purposes can be obtained."
Date: May 1939
Creator: Allen, H. Julian
Partner: UNT Libraries Government Documents Department
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