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  Partner: UNT Libraries Government Documents Department
 Collection: Technical Report Archive and Image Library
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
Drag measurements at high Reynolds numbers of a 100-inch-chord NACA 23016 practical construction wing section submitted by Chance Vought Aircraft Company

Drag measurements at high Reynolds numbers of a 100-inch-chord NACA 23016 practical construction wing section submitted by Chance Vought Aircraft Company

Date: June 1, 1944
Creator: Nuber, Robert J
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Drag investigation of a swept-wing fighter-airplane model incorporating two drag-rise-reducing fuselage revisions

Drag investigation of a swept-wing fighter-airplane model incorporating two drag-rise-reducing fuselage revisions

Date: July 19, 1955
Creator: Whitcomb, Charles F & Lee, Edwin E , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Drag measurements at low lift of a four-nacelle airplane configuration having a longitudinal distribution of cross-sectional area conducive to low transonic drag rise

Drag measurements at low lift of a four-nacelle airplane configuration having a longitudinal distribution of cross-sectional area conducive to low transonic drag rise

Date: November 18, 1953
Creator: Hopko, Russell N; Piland, Robert O & Hall, James R
Description: None
Contributing Partner: UNT Libraries Government Documents Department