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 Collection: Technical Report Archive and Image Library
Rocket-powered-model investigation of the effects of aeroelasticity on the rolling effectiveness of an 8.06-percent-scale mcdonnell f3h-1 airplane wing at mach numbers from 0.5 to 1.4

Rocket-powered-model investigation of the effects of aeroelasticity on the rolling effectiveness of an 8.06-percent-scale mcdonnell f3h-1 airplane wing at mach numbers from 0.5 to 1.4

Date: April 12, 1954
Creator: English, R. D.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Rocket-powered-model investigation of the effects of aeroelasticity on the rolling effectiveness of an 8.06-percent-scale McDonnell F3H-1 airplane wing at Mach numbers from 0.5 to 1.4 : TED No. NACA DE 351

Rocket-powered-model investigation of the effects of aeroelasticity on the rolling effectiveness of an 8.06-percent-scale McDonnell F3H-1 airplane wing at Mach numbers from 0.5 to 1.4 : TED No. NACA DE 351

Date: April 12, 1954
Creator: English, Roland D.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Rocket-powered-model investigation of the hinge-moment and normal-force characteristics of a half-diamond tip control on a 60 degree sweptback diamond wind between Mach numbers of 0.5 and 1.3

Rocket-powered-model investigation of the hinge-moment and normal-force characteristics of a half-diamond tip control on a 60 degree sweptback diamond wind between Mach numbers of 0.5 and 1.3

Date: April 26, 1954
Creator: Church, James D
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Rocket thrust variation with foamed liquid propellants

Rocket thrust variation with foamed liquid propellants

Date: February 26, 1957
Creator: Morrell, G
Description: An analysis is presented on a method for varying rocket thrust by varying the bulk density of the propellants. This density variation was accomplished by uniformly dispersing an inert, insoluble gas in the liquid propellants. Only qualitative agreement with theory was obtained from preliminary experiments with a 1000-pound-thrust ammonia - nitric acid rocket engine; the required experimental gas-flow rates were two to six times greater than those predicted by theory. It was demonstrated, however, that this method of rocket-thrust variation is feasible.
Contributing Partner: UNT Libraries Government Documents Department
Rockets using Liquid Oxygen

Rockets using Liquid Oxygen

Date: April 1, 1947
Creator: Busemann, Adolf
Description: It is my task to discuss rocket propulsion using liquid oxygen and my treatment must be highly condensed for the ideas and experiments pertaining to this classic type of rocket are so numerous that one could occupy a whole morning with a detailed presentation. First, with regard to oxygen itself as compared with competing oxygen carriers, it is known that the liquid state of oxygen, in spite of the low boiling point, is more advantageous than the gaseous form of oxygen in pressure tanks, therefore only liquid oxygen need be compared with the oxygen carriers. The advantages of liquid oxygen are absolute purity and unlimited availability at relatively small cost in energy. The disadvantages are those arising from the impossibility of absolute isolation from heat; consequently, allowance must always be made for a certain degree of vaporization and only vented vessels can be used for storage and transportation. This necessity alone eliminates many fields of application, for example, at the front lines. In addition, liquid oxygen has a lower specific weight than other oxygen carriers, therefore many accessories become relatively larger and heavier in the case of an oxygen rocket, for example, the supply tanks and the pumps. The advantages ...
Contributing Partner: UNT Libraries Government Documents Department
Rocky Mount, North Carolina

Rocky Mount, North Carolina

Date: 1980
Creator: U.S. Fish and Wildlife Service
Description: Map showing biological resources (aquatic organisms, terrestrial organisms, land use, etc.) in the Rocky Mount region of the Atlantic coast area. Scale 1:250,000.
Contributing Partner: UNT Libraries Government Documents Department
Rohrbach all metal commercial airplane RO VIII "Roland"

Rohrbach all metal commercial airplane RO VIII "Roland"

Date: December 1, 1926
Creator: unknown
Description: With three 230 HP. engines and all metal construction, the Roland, Rohrbach VIII is a passenger aircraft with seating for two pilots and 10 passengers.
Contributing Partner: UNT Libraries Government Documents Department
The Rohrbach "ROBBE" RO VII seaplane : military or commercial

The Rohrbach "ROBBE" RO VII seaplane : military or commercial

Date: April 1, 1927
Creator: unknown
Description: The RO VII is a monoplane with two 230 BMW engines mounted on top of the wing. It seats 4 passengers with room for a pilot and a mechanic in the cockpit.
Contributing Partner: UNT Libraries Government Documents Department
The Rohrbach "ROCCO:" seaplane : new German commercial seaplane with two Rolls-Royce "Condor" engines

The Rohrbach "ROCCO:" seaplane : new German commercial seaplane with two Rolls-Royce "Condor" engines

Date: June 1, 1927
Creator: unknown
Description: The Rocco is a has a monoplane wing surmounted by two engines. It's flat sided narrow beam hull is steadied when on the water by 2 outboard wing floats.
Contributing Partner: UNT Libraries Government Documents Department
The Role of Bubble-Size Equilibration in the Transient Behavior of Fission Gas

The Role of Bubble-Size Equilibration in the Transient Behavior of Fission Gas

Date: 1978?
Creator: Gruber, E. E.
Description: An explicit analysis of bubble-size equilibration by volume diffusion has been derived and incorporated into the FRAS2 code. This code was developed for mechanistic analysis of transient fission-gas behavior in LMFBR fuel, but had been limited by the approximation that the time required for bubble-size adjustment, following coalescence or changes in temperature or pressure, was negligible. The equilibration phenomenon is illustrated by several idealized examples. If the fuel temperature rises linearly with time, an isolated bubble will expand rapidly toward its equilibrium size only after the temperature reaches a critical value that depends on both bubble size and heating rate. Conversely, if the temperature is reduced uniformly, an isolated bubble will shrink only until diffusion becomes too slow for further size change. The final size that is ''frozen in'' may be significantly larger than the final equilibrium size. Finally, isothermal equilibration following coalescence of two equal bubbles can be described conveniently in terms of relaxation times, which depend on bubble size and temperature. However, a complete picture of the role of equilibration in transient fission-gas behavior can only be gained through an investigation of the bubble-size distribution and its evolution. Such an investigation is carried out with the FRAS2 code, ...
Contributing Partner: UNT Libraries Government Documents Department
Role of nickel dip in enameling of sheet steel

Role of nickel dip in enameling of sheet steel

Date: June 1, 1954
Creator: Moore, D G; Pitts, J W & Harrison, W N
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The Role of Standard Reference Materials in Measurement Systems

The Role of Standard Reference Materials in Measurement Systems

Date: January 1975
Creator: Cali, J. P.; Mears, T. W.; Michaelis, R. E.; Reed, W. P.; Seward, R. W.; Stanley, C., L. et al.
Description: Report is a guide to Standard Reference Materials (SRM's) and should be useful to all users of SRM's particularly those in countries developing national measurement systems. It is not intended to be an exhaustive description of the NBS-SRM program, but rather a review of the role SRM's play in the measurement system, how SRM's are certified, and what the certification means. To illustrate the use of SRM's, several selected industries are described in which SRM's have made significant contributions.
Contributing Partner: UNT Libraries Government Documents Department
The role of triple collisions in excitation of molecular vibrations in nitrous oxide

The role of triple collisions in excitation of molecular vibrations in nitrous oxide

Date: May 1, 1954
Creator: Walker, Richard A; Rossing, Thomas D & Legvold, Sam
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Roll Cladding Uranium-Zirconium and Uranium-Zirconium-Niobium Alloys with Zircaloy-2 for Plate-Type Fuel Elements

Roll Cladding Uranium-Zirconium and Uranium-Zirconium-Niobium Alloys with Zircaloy-2 for Plate-Type Fuel Elements

Date: February 1958
Creator: Bean, C. H.; Macherey, R. E. & Lindgren, J. R.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Rolling effectiveness and aileron reversal of rectangular wings at supersonic speeds

Rolling effectiveness and aileron reversal of rectangular wings at supersonic speeds

Date: April 1, 1954
Creator: Hedgepeth, John M & Kell, Robert J
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Rolling effectiveness of a thin tapered wing having partial-span ailerons as determined by rocket-powered test vehicles

Rolling effectiveness of a thin tapered wing having partial-span ailerons as determined by rocket-powered test vehicles

Date: May 23, 1950
Creator: Sandahl, Carl A & Strass, H Kurt
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Rolling effectiveness of all-movable wings at small angles of incidence at Mach numbers from 0.6 to 1.6

Rolling effectiveness of all-movable wings at small angles of incidence at Mach numbers from 0.6 to 1.6

Date: October 9, 1951
Creator: Strass, H Kurt & Marley, Edward, T
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The rolling effectiveness of wing-tip ailerons as determined by rocket-powered test vehicles and linear supersonic theory

The rolling effectiveness of wing-tip ailerons as determined by rocket-powered test vehicles and linear supersonic theory

Date: August 29, 1950
Creator: Sandahl, Carl A; Strass, H Kurt & Piland, Robert O
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The rolling friction of several airplane wheels and tires and the effect of rolling friction on take-off

The rolling friction of several airplane wheels and tires and the effect of rolling friction on take-off

Date: January 1, 1937
Creator: Wetmore, J W
Description: This report presents the results of test made to determine the rolling friction of airplane wheels and tires under various conditions of wheel loading, tire inflation pressure, and ground surface. The effect of wheel-bearing type was also investigated. Six pairs of wheels and tires were tested including two sizes of each of the types designated as standard (high pressure), low pressure, and extra low pressure. The results of calculations intended to show the effect of variations in rolling friction on take-off are also presented.
Contributing Partner: UNT Libraries Government Documents Department
The rolling moment due to sideslip of triangular, trapezoidal, and related plan forms in supersonic flow

The rolling moment due to sideslip of triangular, trapezoidal, and related plan forms in supersonic flow

Date: October 1, 1948
Creator: Jones, Arthur L; Spreiter, John R & Alksne, Alberta
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Rolling moments due to rolling and yaw for four wing models in rotation

Rolling moments due to rolling and yaw for four wing models in rotation

Date: January 1, 1932
Creator: Knight, Montgomery & Wenzinger, Carl J
Description: This report presents the results of a series of autorotation and torque tests on four different rotating wing systems at various rates of roll and at several angles of yaw. The investigation covered an angle of attack range up to 90 degrees and angles of yaw of 0 degree, 5 degrees, 10 degrees, and 20 degrees. The tests were made in a 5-foot, closed-throat atmospheric wind tunnel. The object of the tests was primarily to determine the effects of various angles of yaw on the rolling moments of the rotating wings up to large angles of attack. It was found that at angles of attack above that of maximum lift the rolling moments on the wings due to yaw (or side slip) from 5 degrees to 20 degrees were roughly of the same magnitude as those due to rolling. There was a wide variation in magnitude of the rolling moment due to yaw angle. The rates and ranges of stable autorotation for the monoplane models were considerably increased by yaw, whereas for an unstaggered biplane they were little affected. The immediate cause of the rolling moment due to yaw is apparently the building up of large loads on the forward ...
Contributing Partner: UNT Libraries Government Documents Department
Rolling, yawing, and hinge moments produced by rectangular ailerons

Rolling, yawing, and hinge moments produced by rectangular ailerons

Date: January 1, 1933
Creator: Heald, R H
Description: Ailerons described in references 1, 2, and 3, are summarized in the form of empirical equations which relate the aileron dimensions and displacements to the rolling, yawing, and hinge moments for pitch angles of 0 and 12 degrees, corresponding to angles of attack of the wings of 4 and 16 degrees, respectively.
Contributing Partner: UNT Libraries Government Documents Department
Roseburg, Oregon

Roseburg, Oregon

Date: 1981
Creator: U.S. Fish and Wildlife Service
Description: Map showing biological resources (aquatic organisms, terrestrial organisms, land use, etc.) in the Roseburg region of the Pacific coast area. Scale 1:250,000.
Contributing Partner: UNT Libraries Government Documents Department
A rosette strain computer

A rosette strain computer

Date: December 1, 1942
Creator: Klemperer, W B
Description: None
Contributing Partner: UNT Libraries Government Documents Department