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Considerations of the Total Drag of Supersonic Airfoil Sections
The results of calculations of the viscous and pressure drags of some two-dimensional supersonic airfoils at zero lift are presented. The results indicate that inclusion of viscous drag alters many previous results regarding the desirability of certain airfoil shapes for securing low drags at supersonic speeds. At certain Reynolds and Mach numbers, for instance, a circular-arc airfoil may theoretically have less drag than the previously advocated symmetrical wedge-shape profile; although under different conditions, the circular-arc airfoil may have a higher drag.
Date:
July 1947
Creator:
Ivey, H. Reese & Klunker, E. Bernard
System:
The UNT Digital Library
Aerodynamic Investigation of a Cup Anemometer
Results of an investigation wherein the change of the normal force coefficient with Reynolds Number was obtained statically for a 15.5-centimeter hemispherical cup.
Date:
July 1934
Creator:
Hubbard, John D. & Brescoll, George P.
System:
The UNT Digital Library
Charts for the Computation of Equilibrium Composition of Chemical Reactions in the Carbon-Hydrogen-Oxygen-Nitrogen System at Temperatures From 2000° to 5000° Degrees K
Charts are provided for the estimation and progressive adjustment of two independent variables on which the calculations are based. Additional charts are provided for the graphical calculation of the composition.
Date:
July 1948
Creator:
Huff, Vearl N. & Calvert, Clyde S.
System:
The UNT Digital Library
The Amiot S.E.C.M. 110 C.1 : A Single-Seat Pursuit Monoplane
Circular presenting a description of the Amiot S.E.C.M. 110 C.1, which is a single-seat pursuit monoplane. Some of the design principles that the aircraft was built from are provided. A description of the design, components, dimensions, flight characteristics, and photographs are provided.
Date:
July 1929
Creator:
unknown
System:
The UNT Digital Library
Compressibility and Heating Effects on Pressure Loss and Cooling of a Baffled Cylinder Barrel
Report presenting testing to obtain experimental confirmation of the effect of air compressibility on cooling and pressure loss of a baffled cylinder barrel and to evaluate various methods of analysis. Testing occurred over a wide range of air flows and density altitudes.
Date:
July 1944
Creator:
Goldstein, Arthur W. & Ellerbrock, Herman H., Jr.
System:
The UNT Digital Library
The critical velocity of a body towed by a cable from an airplane
It is sufficient to consider only the equations of motion of the towed body whereas those of the cable may be left out of consideration. The result obtained makes it possible to determine which factors affect the critical velocity and what modifications of the instrument are necessary for extending the upper limit of that velocity.
Date:
July 1937
Creator:
Koning, C. & DeHaas, T. P.
System:
The UNT Digital Library
The Hanriot-Biche 110 C1 Airplane (French): An All-Metal Low-Wing Pursuit Monoplane
Circular presenting a description of the Hanriot-Biche 110 C1 airplane, which is a French all-metal low-wing pursuit monoplane. Details regarding the wing, girders and tail surfaces, pilot's cockpit, power plant, landing gear, flying qualities, and photographs are provided.
Date:
July 1933
Creator:
Rabion, René
System:
The UNT Digital Library
The "Comte A.C. 3" Military Airplane (Swiss) : A High-Wing Semicantilever Monoplane
Circular presenting a description of the Comte A.C. 3, which is a high-wing monoplane with tow tandem 600 hp Hispano-Suiza engines mounted above the fuselage. Details of the design, fuel tanks, fuselage, pilot seating, engine, wings, safety factors, and flight qualities are provided.
Date:
July 1930
Creator:
unknown
System:
The UNT Digital Library
NACA Mach number indicator for use in high-speed tunnels
Report presenting a description of a device for indicating stream Mach number in a high-speed tunnel. It consists of a mechanism for determining the pressure ratio that Mach number is a function of. The instrument is in service in the 8-foot high-speed tunnel and its accuracy has been found adequate for wind-tunnel requirements.
Date:
July 1943
Creator:
Smith, Norman F.
System:
The UNT Digital Library
On a New Method for Calculating the Potential Flow Past a Body of Revolution
Report presenting a new method for obtaining the velocity potential of the flow about a solid of revolution moving uniformly in the direction of its axis of symmetry in a fluid otherwise at rest. The method is based essentially on the fact that the form of the differential equation for the velocity potential is invariant with regard to conformal transformations in a meridian plane. The general results are applied to a body of revolution obtained by revolving a symmetrical Joukowski profile about its axis of symmetry.
Date:
July 1942
Creator:
Kaplan, Carl
System:
The UNT Digital Library
Wind-Tunnel Investigation to Determine the Horizontal- and Vertical-Tail Contributions to the Static Lateral Stability Characteristics of a Complete-Model Swept-Wing Configuration at High Subsonic Speeds
Results regarding an investigation to determine the horizontal- and vertical-tail contributions to the static lateral stability of a complete-model swept-wing configuration at high subsonic speeds. Generally, Mach number effects within the range studied and wing effects on the tail contribution were small and the overall trends of the data of the present investigation agreed with those which have been established at low speeds.
Date:
July 10, 1953
Creator:
Wiggins, James W.; Kuhn, Richard E. & Fournier, Paul G.
System:
The UNT Digital Library
The development and application of high-critical-speed nose inlets
From Summary: "An analysis of the nose-inlet shapes developed in previous investigations to represent the optimum from the standpoint of critical speed has shown that marked similarity exists between the nondimensional profiles of inlets which have widely different proportions and critical speeds. With the nondimensional similarity of such profiles established, the large differences in the critical speeds of these nose inlets must be a function of their proportions. An investigation was undertaken in the Langley 8-foot high-speed tunnel to establish the effects of nose-inlet proportions on critical Mach number and to develop a rational method for the design of high-critical-speed nose inlets to meet desired requirements."
Date:
July 1945
Creator:
Baals, Donald D.; Smith, Norman F. & Wright, John B.
System:
The UNT Digital Library
Wind-Tunnel Investigation of the Effects of Spoilers on the Characteristics of a Low-Drag Airfoil Equipped With a 0.25-Chord Slotted Flap
Report discussing the effects of circular-arc spoilers on the section characteristics of an NACA 66,2-216 airfoil with a 0.25-chord slotted flap. Spoilers were tested on the upper surface of the airfoil, on the lower surface, and on both simultaneously. Only the simultaneous placement of spoilers was found to provide satisfactory results as a lateral control device.
Date:
July 23, 1945
Creator:
Holtzclaw, Ralph W.
System:
The UNT Digital Library
The Bernard 80 G.R. Long-Distance Airplane (French) : A Two-Place Cantilever Monoplane
Circular presenting a description of the Bernard 80 aircraft. Details are provided on the body shape, wings, ribs, fuel requirements, and flight characteristics.
Date:
July 1931
Creator:
unknown
System:
The UNT Digital Library
The Comper "Streak" Single Seat Airplane (British): A Low-Wing Cantilever Monoplane
Circular describing the Comper Streak single-seat low-wing cantilever monoplane. Details of the fuselage, construction, wing, stabilizer, engine, landing gear, characteristics, drawings, and photographs are provided.
Date:
July 1934
Creator:
unknown
System:
The UNT Digital Library
Determination of General Relations for the Behavior of Turbulent Boundary Layers
Report presenting an analysis of data for turbulent boundary layers along wings and bodies of various shapes in order to determine the fundamental variables that control the development of turbulent boundary layers. Results indicate that the type of velocity distribution in the boundary layer could be expressed in terms of a single parameter.
Date:
July 1943
Creator:
von Doenhoff, Albert E. & Tetervin, Neal
System:
The UNT Digital Library
The Avro "Gosport," 504 R: A New Training Airplane
Circular describing the Avro Gosport 504 R, which is a new training airplane that is lighter than other Avro training airplanes but is strong enough to withstand rough handling that may be encountered in training. Details of the fuselage, construction, ailerons, tail, struts, landing gear, fuel tanks, performance, characteristics, and photographs are provided.
Date:
July 1927
Creator:
unknown
System:
The UNT Digital Library
The Gloster "Gambet" Airplane: A Deck-Landing Ship's Fighter Fitted With a 420 HP. Bristol Jupiter VI Engine
Circular detailing the Glouster "Gambet", which is a new single-seat fighter for use from aircraft carriers. A description of the design, components, characteristics, photographs, and drawings are provided.
Date:
July 1927
Creator:
unknown
System:
The UNT Digital Library
The Bernard 20 C.1 (French): A Single-Seat Pursuit Monoplane
Circular presenting a description of the Bernard 20 C.1, which is made of wood and has four main parts: a one-piece wing with a fuselage in the middle, a rear section with the tail surfaces, an engine mount, and a landing gear.
Date:
July 1929
Creator:
unknown
System:
The UNT Digital Library
Comparison of Vee-Type and Conventional Tail Surfaces in Combination with Fuselage and Wing in the Variable-Density Tunnel
"The pitching and the yawing moments of a vee-type and a conventional type of tail surface were measured. The tests were made in the presence of a fuselage and a wing-fuselage combination in such a way as to determine the moments contributed by the tail surfaces" (p. 1).
Date:
July 1941
Creator:
Greenberg, Harry
System:
The UNT Digital Library
The Farman Night Bombers 211 and 212 (French): Four-Engine High-Wing Monoplanes
Circular presenting a description of the Farman night bombers 211 and 212, which are four-engine high-wing monoplanes that are equipped with different engines. Details of the wing structure, fuselage, tail surface and controls, landing gear, power plant, characteristics, performance, drawings, and photographs are provided.
Date:
July 1932
Creator:
unknown
System:
The UNT Digital Library
The Caproni "90 P.B." Military Airplane (Italian): A Giant Biplane of 6000 Horsepower
Circular presenting a description of the Caproni 90 P.B., which is the largest airplane in existence at the time of the report. Details of the weight, construction, wings, controls, fuselage, tail, landing gear, flying qualities, and photographs are provided.
Date:
July 1930
Creator:
unknown
System:
The UNT Digital Library
The Mono-Spar Light Airplane (British): A Twin-Engined Low-Wing Cabin Monoplane
Circular presenting a description of the Mono-Spar light airplane, which is a small twin-engined low-wing cabin monoplane. A description of the design, structural features, characteristics, flying qualities, photographs, and drawings are provided.
Date:
July 1931
Creator:
unknown
System:
The UNT Digital Library
The Effect of Increased Cooling Surface on Performance of Aircraft-Engine Cylinders as Shown by Tests of the NACA Cylinder
Report presenting a method of constructing fins of nearly optimum proportions to the point where a cylinder has been manufactured and tested. Data were obtained on cylinder temperature for a wide range of inlet-manifold pressures, engine speeds, and cooling-pressure differences. Results regarding cooling equations, cylinder-temperature relationships, and a comparison of three cylinder cooling performances are provided.
Date:
July 1944
Creator:
Schey, Oscar W.; Rollin, Vern G. & Ellerbrock, Herman H., Jr.
System:
The UNT Digital Library