You limited your search to:

 Collection: National Advisory Committee for Aeronautics Collection
The Minimum Induced Drag of Aerofoils

The Minimum Induced Drag of Aerofoils

Date: December 1, 1979
Creator: Munk, M. M.
Description: Equations are derived to demonstrate which distribution of lifting elements result in a minimum amount of aerodynamic drag. The lifting elements were arranged (1) in one line, (2) parallel lying in a transverse plane, and (3) in any direction in a transverse plane. It was shown that the distribution of lift which causes the least drag is reduced to the solution of the problem for systems of airfoils which are situated in a plane perpendicular to the direction of flight.
Contributing Partner: UNT Libraries Government Documents Department
Pressure Distribution on Joukowski Wings

Pressure Distribution on Joukowski Wings

Date: December 1, 1979
Creator: Blumenthal, O.
Description: The hydrodynamics and mathematical models as applied to the potential flow about a Joukowski wing are presented.
Contributing Partner: UNT Libraries Government Documents Department
Remarks on the Pressure Distribution over the Surface of an Ellipsoid, Moving Translationally Through a Perfect Fluid

Remarks on the Pressure Distribution over the Surface of an Ellipsoid, Moving Translationally Through a Perfect Fluid

Date: December 1, 1979
Creator: Munk, Max M.
Description: The pressure distribution over ellipsoids when in translatory motion through a perfect fluid is calculated. A method to determine the magnitude of the velocity and of the pressure at each point of the surface of an ellipsoid of rotation is described.
Contributing Partner: UNT Libraries Government Documents Department
An approximate spin design criterion for monoplanes, 1 May 1939

An approximate spin design criterion for monoplanes, 1 May 1939

Date: January 1, 1976
Creator: Seidman, O. & Donlan, C. J.
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.
Contributing Partner: UNT Libraries Government Documents Department
Methods of analyzing wind-tunnel data for dynamic flight conditions

Methods of analyzing wind-tunnel data for dynamic flight conditions

Date: January 1, 1976
Creator: Donlan, C. J. & Recant, I. G.
Description: The effects of power on the stability and the control characteristics of an airplane are discussed and methods of analysis are given for evaluating certain dynamic characteristics of the airplane that are not directly discernible from wind tunnel tests alone. Data are presented to show how the characteristics of a model tested in a wind tunnel are affected by power. The response of an airplane to a rolling and a yawing disturbance is discussed, particularly in regard to changes in wing dihedral and fin area. Solutions of the lateral equations of motion are given in a form suitable for direct computations. An approximate formula is developed that permits the rapid estimation of the accelerations produced during pull-up maneuvers involving abrupt elevator deflections.
Contributing Partner: UNT Libraries Government Documents Department
Spin tests of a low-wing monoplane to investigate scale effect in the model test range, May 1941

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

Date: January 1, 1976
Creator: Donlan, C. J.
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.
Contributing Partner: UNT Libraries Government Documents Department
Spin-Tunnel Investigation of a 1/28-Scale Model of a Subsonic Attack Airplane

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

Date: July 1, 1964
Creator: Lee, Henry A. & Healy, Frederick M.
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.
Contributing Partner: UNT Libraries Government Documents Department
Spin Tunnel Investigation of a 1/30 Scale Model of the North American A-5A Airplane

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

Date: June 1, 1964
Creator: Lee, Henry A.
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.
Contributing Partner: UNT Libraries Government Documents Department
Performance of a Single Fuel-vaporizing Combustor With Six Injectors Adapted for Gaseous Hydrogen

Performance of a Single Fuel-vaporizing Combustor With Six Injectors Adapted for Gaseous Hydrogen

Date: November 30, 1959
Creator: Smith, A. L. & Wear, J. D.
Description: Single fuel-vaporizing combustor with injectors adapted for gaseous hydrogen.
Contributing Partner: UNT Libraries Government Documents Department
Some Research on the Lift and Stability of Wing-Body Combinations

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

Date: July 2, 1959
Creator: Purser, Paul E. & Fields, E. M.
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.
Contributing Partner: UNT Libraries Government Documents Department
Preliminary analysis of hydrogen-rich hypersonic ramjet operation

Preliminary analysis of hydrogen-rich hypersonic ramjet operation

Date: May 29, 1959
Creator: Breitwieser, R. & Morris, J. F.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
An analytical evaluation of the effects of an aerodynamic modification and of stability augmenters on the pitch behavior and probable pilot opinion of two current fighter airplanes

An analytical evaluation of the effects of an aerodynamic modification and of stability augmenters on the pitch behavior and probable pilot opinion of two current fighter airplanes

Date: April 21, 1959
Creator: Sadoff, Melvin & Stewart, John D
Description: None
Contributing 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

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

Date: April 15, 1959
Creator: Church, J. D.
Description: Wind tunnel testing of swept wing fighter aircraft model for determining drag and static longitudinal and lateral stability and control characteristics.
Contributing Partner: UNT Libraries Government Documents Department
Boundary-layer Displacement Effects in Air at Mach Numbers of 6.8 and 9.6

Boundary-layer Displacement Effects in Air at Mach Numbers of 6.8 and 9.6

Date: January 1, 1959
Creator: Bertram, M. H.
Description: Boundary layer displacement effects in air at mach 6.8 and 9.6.
Contributing 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

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

Date: January 1, 1959
Creator: unknown
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.
Contributing Partner: UNT Libraries Government Documents Department
One-dimensional flows of an imperfect diatomic gas

One-dimensional flows of an imperfect diatomic gas

Date: January 1, 1959
Creator: unknown
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).
Contributing Partner: UNT Libraries Government Documents Department
Combustor performance with various hydrogen-oxygen injection methods in a 200-pound-thrust rocket engine

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

Date: September 30, 1958
Creator: Heidmann, M F & Baker, Louis, Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Off-Design Performance of Divergent Ejectors

Off-Design Performance of Divergent Ejectors

Date: September 30, 1958
Creator: Beheim, M. A.
Description: Off-design performance of divergent ejectors.
Contributing Partner: UNT Libraries Government Documents Department
Off-design performance of divergent ejectors

Off-design performance of divergent ejectors

Date: September 30, 1958
Creator: Beheim, Milton A
Description: None
Contributing 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

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

Date: September 30, 1958
Creator: Martz, C William
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Screaming tendency of the gaseous-hydrogen - liquid-oxygen propellant combination

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

Date: September 30, 1958
Creator: Baker, Louis, Jr & Steffen, Fred W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Use of highly reactive chemical additives to improve afterburner performance at altitude

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

Date: September 30, 1958
Creator: Wanhainen, John P & Sivo, Joseph N
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Use of highly reactive chemical additives to improve afterburner performance at altitude

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

Date: September 30, 1958
Creator: Sivo, J. N. & Wanhainen, J. P.
Description: Liquid hydrogen and aluminum trimethyl as highly reactive chemical additives in turbojet afterburner to promote fuel combustion process.
Contributing Partner: UNT Libraries Government Documents Department
Some notes on the probable damage to an intercontinental-ballistic-missile warhead following puncture of the heat shield

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

Date: September 28, 1958
Creator: Strass, H. K. & Goodman, V. M.
Description: None
Contributing Partner: UNT Libraries Government Documents Department