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Applications of Modern Hydrodynamics to Aeronautics. Part 1: Fundamental Concepts and the Most Important Theorems. Part 2: Applications

Description: A discussion of the principles of hydrodynamics of nonviscous fluids in the case of motion of solid bodies in a fluid is presented. Formulae are derived to demonstrate the transition from the fluid surface to a corresponding 'control surface'. The external forces are compounded of the fluid pressures on the control surface and the forces which are exercised on the fluid by any solid bodies which may be inside of the control surfaces. Illustrations of these formulae as applied to the acquisition of transformations from a known simple flow to new types of flow for other boundaries are given. Theoretical and experimental investigations of models of airship bodies are presented.
Date: 1979?~
Creator: Prandtl, L.
Partner: UNT Libraries Government Documents Department

An approximate spin design criterion for monoplanes, 1 May 1939

Description: An approximate empirical criterion, based on the projected side area and the mass distribution of the airplane, was formulated. The British results were analyzed and applied to American designs. A simpler design criterion, based solely on the type and the dimensions of the tail, was developed; it is useful in a rapid estimation of whether a new design is likely to comply with the minimum requirements for safety in spinning.
Date: January 1, 1976
Creator: Seidman, O. & Donlan, C. J.
Partner: UNT Libraries Government Documents Department

Spin tests of a low-wing monoplane to investigate scale effect in the model test range, May 1941

Description: Concurrent tests were performed on a 1/16 and a 1/20 scale model (wing spans of 2.64 and 2.11 ft. respectively) of a modern low wing monoplane in the NACA 15 foot free-spinning wind tunnel. Results are presented in the form of charts that afford a direct comparison between the spins of the two models for a number of different conditions. Qualitatively, the same characteristic effects of control disposition, mass distribution, and dimensional modifications were indicated by both models. Quantitatively, the number of turns for recover and the steady spin parameters, with the exception of the inclination of the wing to the horizontal, were usually in good agreement.
Date: January 1, 1976
Creator: Donlan, C. J.
Partner: UNT Libraries Government Documents Department

Smoking characteristics of various fuels as determined by open-cup and laboratory-burner smoke tests

Description: Report discussing tests in a combustion chamber to obtain smoking characteristics data on a variety of hydrocarbon fuels. Details about the smoking tendencies and burning rates of the fuels in uncontrolled and controlled tests are provided.
Date: {1945-06, 1945-09}
Creator: Ebersole, Earl R. & Barnett, Henry C.
Partner: UNT Libraries Government Documents Department

Spin-Tunnel Investigation of a 1/28-Scale Model of a Subsonic Attack Airplane

Description: An investigation has been made of a 1/28-scale model of the Grumman A-6A airplane in the Langley spin tunnel. The erect spin and recovery characteristics of the model were determined for the flight design gross weight loading and for a loading with full internal fuel and empty external wing fuel tanks. The effects of extending slats and deflecting flaps were investigated. Inverted-spin and recovery characteristics of the model were determined for the flight design gross weight loading. The size of the spin-recovery tail parachute necessary to insure satisfactory spin-recovery was determined, and the effect of firing wing-mounded rockets during spins was investigated.
Date: July 1964
Creator: Lee, Henry A. & Healy, Frederick M.
Partner: UNT Libraries Government Documents Department

Spin Tunnel Investigation of a 1/30 Scale Model of the North American A-5A Airplane

Description: An investigation has been made in the Langley spin tunnel to determine the erect and inverted spin and recovery characteristics of a 1/30-scale dynamic model of the North American A-5A airplane. Tests were made for the basic flight design loading with the center of gravity at 30-percent mean aerodynamic chord and also for a forward position and a rearward position with the center of gravity at 26-percent and 40-percent mean aerodynamic chord, respectively. Tests were also made to determine the effect of full external wing tanks on both wings, and of an asymmetrical condition when only one full tank is carried.
Date: June 1964
Creator: Lee, Henry A.
Partner: UNT Libraries Government Documents Department

Some Research on the Lift and Stability of Wing-Body Combinations

Description: The present paper summarizes and correlates broadly some of the research results applicable to fin-stabilized ammunition. The discussion and correlation are intended to be comprehensive, rather than detailed, in order to show general trends over the Mach number range up to 7.0. Some discussion of wings, bodies, and wing-body interference is presented, and a list of 179 papers containing further information is included. The present paper is intended to serve more as a bibliography and source of reference material than as a direct source of design information.
Date: July 2, 1959
Creator: Purser, Paul E. & Fields, E. M.
Partner: UNT Libraries Government Documents Department

Effects of components and various modifications on the drag and the static stability and control characteristics of a 42 deg swept-wing fighter-airplane model at Mach numbers of 1.60 to 2.50

Description: Wind tunnel testing of swept wing fighter aircraft model for determining drag and static longitudinal and lateral stability and control characteristics.
Date: April 15, 1959
Creator: Church, J. D.
Partner: UNT Libraries Government Documents Department

Forty-Fourth Annual Report of the National Advisory Committee for Aeronautics Administrative Report Including Technical Reports Nos. 1342 to 1392

Description: In accordance with act of Congress, approved March 3, 1915, as amended (U.S.C., title 50, .sw 151), which established the National Advisory Committee for Aeronautics, the Committee submits its Forty-fourth Annual Report for the fiscal year 1958. This is the Committee's final report to the Congress. The National Aeronautics and Space Act of 1958 (Public Law 85-568) provides in section 301 that the NACA "shall cease to exist" and "all functions, powers, duties, and obligations, and all real and personal property, personnel (other than members of the Committee), funds, and records of the NACA shall be transferred to the National Aeronautics and Space Administration. The aforesaid act provides that "this section shall take effect 90 days after the date of the enactment of this act, or on any earlier date on which the Administrator shall determining and announce by proclamation published in the Federal Register, that the Administration has been organized and is prepared to discharge the duties and exercise the power conferred upon it by this act." The Administrator, Hon. T. Keith Glennan has advised the Committee of his intention to issue such proclamation, effective October 1,1958.
Date: 1959
Partner: UNT Libraries Government Documents Department

One-dimensional flows of an imperfect diatomic gas

Description: With the assumptions that Berthelot's equation of state accounts for molecular size and intermolecular force effects, and that changes in the vibrational heat capacities are given by a Planck term, expressions are developed for analyzing one-dimensional flows of a diatomic gas. The special cases of flow through normal and oblique shocks in free air at sea level are investigated. It is found that up to a Mach number 10 pressure ratio across a normal shock differs by less than 6 percent from its ideal gas value; whereas at Mach numbers above 4 the temperature rise is considerable below and hence the density rise is well above that predicted assuming ideal gas behavior. It is further shown that only the caloric imperfection in air has an appreciable effect on the pressures developed in the shock process considered. The effects of gaseous imperfections on oblique shock-flows are studied from the standpoint of their influence on the life and pressure drag of a flat plate operating at Mach numbers of 10 and 20. The influence is found to be small. (author).
Date: January 1, 1959
Partner: UNT Libraries Government Documents Department

Combustor performance with various hydrogen-oxygen injection methods in a 200-pound-thrust rocket engine

Description: Report presenting a determination of the characteristics velocity of liquid oxygen and gaseous hydrogen as a function of mixture ratio in a nominal 200-pound-thrust variable-length rocket engine. Fourteen injectors, which varied mixing and oxygen atomization, were investigated. The four types of injector designs included triplets of two hydrogen jets impinging on one oxygen jet, concentric injection with hydrogen surrounding a jet of oxygen, radial injection of oxygen with variations in hydrogen injection, and oxygen atomization by two impinging jets with variations in hydrogen injection.
Date: September 30, 1958
Creator: Heidmann, M. F. & Baker, Louis, Jr.
Partner: UNT Libraries Government Documents Department

Off-design performance of divergent ejectors

Description: Report presenting an investigation of the off-design performance of fixed- and variable-geometry divergent ejectors. Results regarding fixed geometry and low secondary flow, fixed geometry and high secondary flow, variable geometry and low secondary flow, variable geometry and high secondary flow, and ejectors with full afterburning are provided.
Date: September 30, 1958
Creator: Beheim, Milton A.
Partner: UNT Libraries Government Documents Department

Off-design performance of divergent ejectors

Description: From Summary: "The off-design performance of fixed- and of variable-geometry divergent ejectors was investigated. The ejectors, which were designed for turbojet operation at Mach 3, were investigated in the Mach number range of 0.8 to 2. The performance of a fixed-geometry ejector with high secondary-flow rates was competitive with that of more complex variable-geometry ejectors. Variable-geometry ejectors with compromises to reduce mechanical complexity produced performance reasonably close to that of an ideal variable ejector."
Date: September 30, 1958
Creator: Beheim, Milton A.
Partner: UNT Libraries Government Documents Department

Rocket-model investigation to determine the lift and pitching effectiveness of small pulse rockets exhausted from the fuselage over the surface of an adjacent wing at Mach numbers from 0.9 to 1.8

Description: Report presenting some experimental free-flight data at a range of Mach numbers regarding the normal force and pitching effectiveness of several small pulse rockets in the fuselage of a rocket propelled model. Wing-damping data was also obtained from the wing bending response to the pulse-rocket excitations, and longitudinal stability data was determined from the model response. Results regarding pulse-rocket effectiveness, wing damping, and model stability data are provided.
Date: September 30, 1958
Creator: Martz, C. William
Partner: UNT Libraries Government Documents Department

Screaming tendency of the gaseous-hydrogen - liquid-oxygen propellant combination

Description: Report presenting an exploratory study of the screaming tendency of the gaseous-hydrogen-liquid-oxygen propellant combination in 200-pound-thrust rocket engines. Four injector classes in a total of 12 different configurations were tested in a variety of chamber lengths over the usable mixture-ratio range. Results regarding acoustic oscillations, unclassified oscillations, driving and damping mechanisms, and effects of screaming on heat transfer are provided.
Date: September 30, 1958
Creator: Baker, Louis, Jr. & Steffen, Fred W.
Partner: UNT Libraries Government Documents Department

Use of highly reactive chemical additives to improve afterburner performance at altitude

Description: Report presenting an investigation in an altitude test chamber to evaluate the use of highly reactive chemicals injected into a turbojet afterburner to promote the combustion process. The chemicals evaluated were commercial hydrogen and aluminum trimethyl. Results regarding the afterburner efficiency, afterburner stability limits, afterburner-outlet total temperature, and an application of the results to other systems are provided.
Date: September 30, 1958
Creator: Wanhainen, John P. & Sivo, Joseph N.
Partner: UNT Libraries Government Documents Department

Some notes on the probable damage to an intercontinental-ballistic-missile warhead following puncture of the heat shield

Description: Report discussing a study of the effects of puncturing the heat shield of an intercontinental-ballistic-missile warhead by small projectiles. Calculations were created for both rod and sphere projectiles and experimental testing was performed on a missile model with holes drilled in the heat shield. The possibility that a projectile could have enough energy to cause mechanical damage to the interior of the warhead is also presented.
Date: September 29, 1958
Creator: Strass, H. K. & Goodman, V. M.
Partner: UNT Libraries Government Documents Department

Analysis of pressure data obtained at transonic speeds on a thin low-aspect-ratio cambered delta wing-body combination

Description: From Introduction: "Wind-tunnel and flight tests have shown that conical leading-edge camber on a thin low-aspect-ratio delta wing results in increasing the lift-drag ratio at transonic and low supersonic speeds (refs. 1 and 2). References 3 and 4 present the results of two previous investigations of this general program. A more detailed analysis of the pressure distributions of reference 5 is presented herein in terms of total section loads and overall wing-body characteristics."
Date: September 26, 1958
Creator: Mugler, John P., Jr.
Partner: UNT Libraries Government Documents Department

Large-scale wind-tunnel tests of a jet-transport-type model with leading- and trailing-edge high-lift devices

Description: From Summary: "An investigation was conducted to determine the longitudinal characteristics of an airplane model with a 35 degree swept wing of aspect ratio 7 and four pylon-mounted nacelles. Several leading-edge configurations were studied in conjunction with double-slotted trailing-edge flaps. Three-component longitudinal data are presented. In general, the test Reynolds number was about 4.8 x 10(exp 6), but for selected configurations, data for Reynolds number ranges from 2.8 to 8 x 10(exp 6) are included."
Date: September 26, 1958
Creator: Hickey, David H. & Aoyagi, Kiyoshi
Partner: UNT Libraries Government Documents Department

Static and dynamic-rotary stability derivatives of an airplane model with an unswept wing and a high horizontal tail at Mach numbers of 2.5, 3.0, and 3.5

Description: Report presenting the static and dynamic-rotary stability derivatives for an airplane with an unswept wing and a high horizontal tail as determined in wind-tunnel tests at 3 Mach numbers. The tail contribution to stability was found to not be predicted by the simplified theoretical methods used in this report. Results regarding the longitudinal derivatives, sideslip derivatives, yawing derivatives, rolling derivatives, and variation of static derivatives with Mach number.
Date: September 26, 1958
Creator: Lampkin, Bedford A. & Tunnell, Phillips J.
Partner: UNT Libraries Government Documents Department