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  Partner: UNT Libraries Government Documents Department
 Decade: 1950-1959
 Serial/Series Title: NACA Technical Notes
 Collection: National Advisory Committee for Aeronautics Collection
Theoretical study of the lateral frequency response to gusts of a fighter airplane, both with controls fixed and with several types of autopilots

Theoretical study of the lateral frequency response to gusts of a fighter airplane, both with controls fixed and with several types of autopilots

Date: March 1, 1956
Creator: Adams, James J & Mathews, Charles, W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Determination of Shapes of Boattail Bodies of Revolution for Minimum Wave Drag

Determination of Shapes of Boattail Bodies of Revolution for Minimum Wave Drag

Date: November 1, 1951
Creator: Adams, Mac C.
Description: By use of an approximate equation for the wave drag of slender bodies of revolution in a supersonic flow field, the optimum shapes of certain boattail bodies are determined for minimum wave drag. The properties of three specific families of bodies are determined, the first family consisting of bodies having a given length and base area and a contour passing through a prescribed point between the nose and base, the second family having fixed length, base area, and maximum area, and the third family having given length, volume, and base area. The method presented is easily generalized to determine minimum-wave-drag profile shapes which have contours that must pass through any prescribed number of points. According to linearized theory, the optimum profiles are found to have infinite slope at the nose but zero radius of curvature so that the bodies appear to have pointed noses, a zero slope at the body base, and no variation of wave drag with Mach number. For those bodies having a specified intermediate.diameter (that is, location and magnitude given), the maximum body diameter is shown to be larger, in general, than the specified diameter. It is also shown that, for bodies having a specified maximum diameter, ...
Contributing Partner: UNT Libraries Government Documents Department
Analysis of the horizontal-tail loads measured in flight on a multiengine jet bomber

Analysis of the horizontal-tail loads measured in flight on a multiengine jet bomber

Date: September 1, 1955
Creator: Aiken, William S & Wiener, Bernard
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Analysis of horizontal-tail loads in pitching maneuvers on a flexible swept-wing jet bomber

Analysis of horizontal-tail loads in pitching maneuvers on a flexible swept-wing jet bomber

Date: December 1, 1957
Creator: Aiken, William S , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Determination of vortex paths by series expansion technique with application to cruciform wings

Determination of vortex paths by series expansion technique with application to cruciform wings

Date: April 1, 1956
Creator: Alksne, Alberta Y
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Analytical method for determining transmission and absorption of time-dependent radiation through thick absorbers III : absorber with radioactive daughter products

Analytical method for determining transmission and absorption of time-dependent radiation through thick absorbers III : absorber with radioactive daughter products

Date: June 1, 1950
Creator: Allen, G
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Tables for determining reduction of energy and intensity of X-rays and gamma-rays at various scattering angles in small thickness of matter

Tables for determining reduction of energy and intensity of X-rays and gamma-rays at various scattering angles in small thickness of matter

Date: February 1, 1950
Creator: Allen, G
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Friction and wear with reactive gases at temperatures up to 1200 F

Friction and wear with reactive gases at temperatures up to 1200 F

Date: September 1, 1958
Creator: Allen, Gordon P; Buckley, Donald H & Johnson, Robert L
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The asymmetric adjustable supersonic nozzle for wind-tunnel application

The asymmetric adjustable supersonic nozzle for wind-tunnel application

Date: March 1, 1953
Creator: Allen, H Julian
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Visualization study of secondary flows in turbine rotor tip regions

Visualization study of secondary flows in turbine rotor tip regions

Date: September 1, 1955
Creator: Allen, Hubert W & Kofskey, Milton G
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Motion of a ballistic missile angularly misaligned with the flight path upon entering the atmosphere and its effect upon aerodynamic heating, aerodynamic loads, and miss distance

Motion of a ballistic missile angularly misaligned with the flight path upon entering the atmosphere and its effect upon aerodynamic heating, aerodynamic loads, and miss distance

Date: October 1, 1957
Creator: Allen, Julian H
Description: An analysis is given of the oscillating motion of a ballistic missile which upon entering the atmosphere is angularly misaligned with respect to the flight path. The history of the motion for some example missiles is discussed from the point of view of the effect of the motion on the aerodynamic heating and loading. The miss distance at the target due to misalignment and to small accidental trim angles is treated. The stability problem is also discussed for the case where the missile is tumbling prior to atmospheric entry.
Contributing Partner: UNT Libraries Government Documents Department
A study of the motion and aerodynamic heating of missiles entering the earth's atmosphere at high supersonic speeds

A study of the motion and aerodynamic heating of missiles entering the earth's atmosphere at high supersonic speeds

Date: October 1, 1957
Creator: Allen, Julian H & Eggers, A J , Jr
Description: A simplified analysis of the velocity and deceleration history of missiles entering the earth's atmosphere at high supersonic speeds is presented. The results of this motion analysis are employed to indicate means available to the designer for minimizing aerodynamic heating. The heating problem considered involves not only the total heat transferred to a missile by convection, but also the maximum average and local time rates of convective heat transfer.
Contributing Partner: UNT Libraries Government Documents Department
Construction and use of charts in design studies of gas turbines

Construction and use of charts in design studies of gas turbines

Date: July 1, 1951
Creator: Alpert, Sumner & Litrenta, Rose M
Description: None
Contributing Partner: UNT Libraries Government Documents Department
A comparison of the turbulent boundary-layer growth on an unswept and a swept wing

A comparison of the turbulent boundary-layer growth on an unswept and a swept wing

Date: September 1, 1951
Creator: Altman, John M & Hayter, Nora-Lee F
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Theory of helicopter damping in pitch or roll and a comparison with flight measurements

Theory of helicopter damping in pitch or roll and a comparison with flight measurements

Date: October 1, 1950
Creator: Amer, Kenneth B
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Charts for estimation of longitudinal-stability derivatives for a helicopter rotor in forward flight

Charts for estimation of longitudinal-stability derivatives for a helicopter rotor in forward flight

Date: March 1, 1951
Creator: Amer, Kenneth B & Gustafson, Frederic Bowen
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Comparison of the experimental pressure distribution on an NACA 0012 profile at high speeds with that calculated by the relaxation method

Comparison of the experimental pressure distribution on an NACA 0012 profile at high speeds with that calculated by the relaxation method

Date: August 1, 1950
Creator: Amick, James L
Description: None
Contributing Partner: UNT Libraries Government Documents Department
A method of selecting the thickness, hollowness, and size of a supersonic wing for least drag and sufficient bending strength at specified flight conditions

A method of selecting the thickness, hollowness, and size of a supersonic wing for least drag and sufficient bending strength at specified flight conditions

Date: July 1, 1952
Creator: Amick, James L
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effect of concentration on ignition delays for various fuel-oxygen-nitrogen mixtures at elevated temperatures

Effect of concentration on ignition delays for various fuel-oxygen-nitrogen mixtures at elevated temperatures

Date: December 1, 1956
Creator: Anagnostou, E; Brokaw, R S & Butler, J N
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Compressive crippling of structural sections

Compressive crippling of structural sections

Date: January 1, 1956
Creator: Anderson, Melvin S
Description: A method is presented for calculating crippling stresses of structural sections as a function of material properties and the proportions of the section. The presence of formed or anisotropic material is accounted for by the use of an effective stress-strain curve. The method of analysis applies to many sections for which a procedure for calculating crippling was not previously available.
Contributing Partner: UNT Libraries Government Documents Department
Local instability of the elements of a truss-core sandwich plate

Local instability of the elements of a truss-core sandwich plate

Date: July 1, 1958
Creator: Anderson, Melvin S
Description: The charts presented give the compressive buckling coefficients for a single-truss-core and a double-truss-core sandwich plate. These charts cover a wide range of sandwich proportions and may be used for sandwiches with unequal faces. They apply to inplane compressive loads acting parallel or perpendicular to the core direction or for various combinations of these loads. (author).
Contributing Partner: UNT Libraries Government Documents Department
Some research results on sandwich structures

Some research results on sandwich structures

Date: June 1, 1957
Creator: Anderson, Melvin S & Updegraff, Richard G
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Charts giving critical compressive stress of continuous flat sheet divided into parallelogram-shaped panels

Charts giving critical compressive stress of continuous flat sheet divided into parallelogram-shaped panels

Date: July 1, 1951
Creator: Anderson, Roger A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Correlation of crippling strength of plate structures with material properties

Correlation of crippling strength of plate structures with material properties

Date: January 1, 1956
Creator: Anderson, Roger A & Anderson, Melvin S
Description: None
Contributing Partner: UNT Libraries Government Documents Department
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