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  Partner: UNT Libraries Government Documents Department
 Collection: Technical Report Archive and Image Library
The drag of inflatable rubber de-icers

The drag of inflatable rubber de-icers

Date: October 1, 1938
Creator: Robinson, Russell G
Description: Force tests on rubber de-icer models of several different profiles, at approximately one-third full scale, been carried out in the NACA 8-foot high speed wind tunnel. The conventional de-icer installation, deflated, added about 15 percent to the smooth-wing drag and, inflated, added about 100 percent. An improved installation with flash attaching strips added about 10 percent, deflated. The bulging, or ballooning, of de-icers from the wing surface is described and some remedies are discussed.
Contributing Partner: UNT Libraries Government Documents Department
Drag of prestone and oil radiators on the YO-31A airplane

Drag of prestone and oil radiators on the YO-31A airplane

Date: December 1, 1935
Creator: Defrance, S J
Description: At the request of the Army Air Corps tests were conducted on a mock-up of the YO-31A airplane to determine the drag of the prestone and oil radiators. The drag of the airplane was determined with both radiators exposed on the lower surface of the fuselage; with each radiator exposed; and with no radiators. The results show that at 120 m.p.h the oil radiator accounted for 2.8 percent of the drag of the complete airplane; the prestone radiator 8.3 percent; and both radiators together, 11.8 percent.
Contributing Partner: UNT Libraries Government Documents Department
Drag of Several Gunner's Enclosures at High Speeds, Special Report

Drag of Several Gunner's Enclosures at High Speeds, Special Report

Date: July 1, 1941
Creator: Stack, John & Moberg, Richard J.
Description: The drag of several types of gunner's turrets, windshields, blisters, and other protuberances, including projecting guns, was investigated at speeds from 75 to 440 miles per hour in the NACA 8-foot high-speed wind tunnel. The various gunner's enclosures were represented by 1/10 and 1/7 full-size models on a midwing-fuselage combination representative of bomber types. Most of the usual types of retractable turrets are very poor aerodynamically; they caused wind drag increments, dependent upon the size of the turret relative to the fuselage and upon the speed, up to twice the drag of the fuselage alone. A large streamline blister sufficient to enclose completely one type of rotating cylindrical turret caused a drag increment of approximately one-half that of the turret and at the same time provided space adequate for two gunners rather than for one gunner. A large portion of the drag increments for some types of turret appeared to be due to adverse effects on the fuselage flow caused by the turret rather than by the direct drag of the turret.
Contributing Partner: UNT Libraries Government Documents Department
The drag of streamline wires

The drag of streamline wires

Date: December 1, 1933
Creator: Jacobs, Eastman N
Description: Preliminary results are given of drag tests of streamline wires. Full-size wires were tested over a wide range of speeds in the N.A.C.A. high speed tunnel. The results are thus directly applicable to full-scale problems and include any compressibility effects encountered at the higher speeds. The results show how protuberances may be employed on conventional streamline wires to reduce the drag, and also show how the conventional wires compare with others having sections more like strut or symmetrical airfoil sections. Because the new wire sections developed are markedly superior aerodynamically to conventional wires, it is recommended that some of them be tested in service in order to investigate their relative susceptibility to vibration and to fatigue failure.
Contributing Partner: UNT Libraries Government Documents Department
The drag of two streamline bodies as affected by protuberances and appendages

The drag of two streamline bodies as affected by protuberances and appendages

Date: January 1, 1934
Creator: Abbott, Ira H
Description: This report presents the results of wind tunnel tests of two airship models conducted to determine the drag coefficients at zero pitch, and the effect of fins and cars and of flat and streamlined protuberances located at various positions along the hull. During the investigation the stern of one model was rounded off to produce a blunter shape. The extreme range of the Reynolds number based on the over-all length of the models was from 1,300,000 to 33,000,000. At large values of the Reynolds number the streamlined protuberance affected the drag very little, and the additional drag caused by the flat protuberance was less than the calculated drag by the protuberance alone. The fins and cars together increased the bare-hull drag about 20 per cent.
Contributing Partner: UNT Libraries Government Documents Department
Drag of wings with end plates

Drag of wings with end plates

Date: January 1, 1928
Creator: Hemke, Paul E
Description: In this report a formula for calculating the induced drag of multiplanes with end plates is derived. The frictional drag of the end plates are used, is sufficiently large to increase the efficiency of the wing. Curves showing the reduction of drag for monoplanes and biplanes are constructed; the influence of gap-chord ratio, aspect ratio, and height of end plate are determined for typical cases. The method of obtaining the reduction of drag for a multiplane is described. Comparisons are made of calculated and experimental results obtained in wind tunnel tests with airfoils of various aspect ratios and end plates of various sizes. The agreement between calculated and experimental results is good. Analysis of the experimental results shows that the shape and section of the end plates are important.
Contributing Partner: UNT Libraries Government Documents Department
Drag tests of 4/9-scale model engine nacelles with various cowlings

Drag tests of 4/9-scale model engine nacelles with various cowlings

Date: October 1, 1932
Creator: Windler, Ray
Description: Results are given of drag tests of 4/9-scale model radial air-cooled engine nacelles made as a part of a general investigation of wing-nacelle-propeller interference. A small nacelle of the type commonly used with exposed engine cylinders was tested with various forms of cowling over the cylinders. The effects of cowling-ring position and of angle of ring chord to the thrust line were investigated. An N.A.C.A. cowled nacelle and a smooth body were also tested. The results are given at 50, 75, and 100 miles per hour for -5 degrees, 0 degrees, 5 degrees, 10 degrees, 15 degrees angle of pitch.
Contributing Partner: UNT Libraries Government Documents Department
The drawing of experimental curves

The drawing of experimental curves

Date: July 1, 1921
Creator: Norton, F H
Description: This report presents a discussion of how to determine the location of a line or surface from experimental data. What we desire to know practically is the number of ordinates required to obtain a certain probable precision in drawing a line or surface.
Contributing Partner: UNT Libraries Government Documents Department
Drag tests of an NACA 65(215)-114, a = 1.0 practical-construction airfoil section equipped with a 0.295-airfoil-chord slotted flap

Drag tests of an NACA 65(215)-114, a = 1.0 practical-construction airfoil section equipped with a 0.295-airfoil-chord slotted flap

Date: April 1, 1947
Creator: Quinn, John H , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Drop and flight tests on NY-2 landing gears including measurements of vertical velocities at landing

Drop and flight tests on NY-2 landing gears including measurements of vertical velocities at landing

Date: January 1, 1933
Creator: Peck, W D & Beard, A P
Description: This investigation was conducted to obtain quantitative information on the effectiveness of three landing gears for the NY-2 (consolidated training) airplane. The investigation consisted of static, drop, and flight tests on landing gears of the oleo-rubber-disk and the mercury rubber-chord types, and flight tests only on a landing gear of the conventional split-axle rubber-cord type. The results show that the oleo gear is the most effective of the three landing gears in minimizing impact forces and in dissipating the energy taken.
Contributing Partner: UNT Libraries Government Documents Department