You limited your search to:

  Partner: UNT Libraries Government Documents Department
 Decade: 1950-1959
 Year: 1953
 Serial/Series Title: NACA Technical Notes
 Collection: National Advisory Committee for Aeronautics Collection
Accelerations and passenger harness loads measured in full-scale light-airplane crashes

Accelerations and passenger harness loads measured in full-scale light-airplane crashes

Date: August 1953
Creator: Eiband, A Martin; Simpkinson, Scott H & Black, Dugald O
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics of a two-blade NACA 10-(3)(062)-045 propeller and of a two-blade NACA 10-(3)(08)-045 propeller

Aerodynamic characteristics of a two-blade NACA 10-(3)(062)-045 propeller and of a two-blade NACA 10-(3)(08)-045 propeller

Date: January 1, 1953
Creator: Solomon, William
Description: Characteristics are given for the two-blade NACA 10-(3)(062)-045 propeller and for the two-blade NACA 10-(3)(08)-045 propeller over a range of advance ratio from 0.5 to 3.8, through a blade-angle range from 20 degrees to 55 degrees measured at the 0.75 radius. Maximum efficiencies of the order of 91.5 to 92 percent were obtained for the propellers. The propeller with the thinner airfoil sections over the outboard portion of the blades, the NACA 10-(3)(062)-045 propeller, had lower losses at high tip speeds, the difference amounting to about 5 percent at a helical tip Mach number of 1.10.
Contributing Partner: UNT Libraries Government Documents Department
The aerodynamic characteristics of an aspect-ratio-20 wing having thick airfoil sections and employing boundary-layer control by suction

The aerodynamic characteristics of an aspect-ratio-20 wing having thick airfoil sections and employing boundary-layer control by suction

Date: August 1, 1953
Creator: Cocke, Bennie W , Jr & Fink, Marvin P
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The aerodynamic design and calibration of an asymmetric variable Mach number nozzle with a sliding block for the Mach number range 1.27 to 2.75

The aerodynamic design and calibration of an asymmetric variable Mach number nozzle with a sliding block for the Mach number range 1.27 to 2.75

Date: April 1, 1953
Creator: Burbank, Paige B & Byrne, Robert W
Description: A method of designing as asymmetric, fixed geometry, variable Mach number nozzle has been developed by using the method of characteristics. A small nozzle conforming to the analytically determined ordinates was constructed and calibrated over a range of Mach numbers extending from 1.27 to 2.75. The results show the variation in Mach number to be plus or minus 0.01 or less and in the flow direction to be plus or minus 0.2 degrees within the test section. The range of Mach numbers from 1.27 to 2.75 was obtained by translating the lower block in a straight line parallel to the test-section center line for a distance of 2.17 test-section heights.
Contributing Partner: UNT Libraries Government Documents Department
An airborne indicator for measuring vertical velocity of airplanes at wheel contact

An airborne indicator for measuring vertical velocity of airplanes at wheel contact

Date: February 1, 1953
Creator: Dreher, Robert C
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Analogy Between Mass and Heat Transfer with Turbulent Flow

Analogy Between Mass and Heat Transfer with Turbulent Flow

Date: October 1, 1953
Creator: Callaghan, Edmund E.
Description: An analysis of combined heat and mass transfer from a flat plate has been made in terms of Prandtl t s simplified physical concept of the turbulent boundary layer. The results of the analysis show that for conditions of reasonably small heat and mass transfer, the ratio of the mass-and heat-transfer coefficients is dependent on the Reynolds number of the boundary layer, the Prandtl number of the medium of diffusion, and the Schmidt number of the diffusing fluid in the medium of diffusion. For the particular case of water evaporating into air, the ratio of mass-transfer coefficient to heat-transfer coefficient is found to be slightly greater than unity.
Contributing Partner: UNT Libraries Government Documents Department
Analysis of heat addition in a convergent-divergent nozzle

Analysis of heat addition in a convergent-divergent nozzle

Date: April 1, 1953
Creator: Hearth, Donald P & Perchonok, Eugene
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Analysis of multicell delta wings on Cal-Tech analog computer

Analysis of multicell delta wings on Cal-Tech analog computer

Date: December 1, 1953
Creator: Macneal, Richard H & Benscoter, Stanley U
Description: None
Contributing Partner: UNT Libraries Government Documents Department
An analysis of normal-acceleration and airspeed data from a four-engine type of transport airplane in commercial operation on an eastern united states route from november 1947 to february 1950

An analysis of normal-acceleration and airspeed data from a four-engine type of transport airplane in commercial operation on an eastern united states route from november 1947 to february 1950

Date: August 1, 1953
Creator: Coleman, Thomas L & Schumacher, Paul W J
Description: None
Contributing Partner: UNT Libraries Government Documents Department
An analysis of statically indeterminate trusses having members stressed beyond the proportional limit

An analysis of statically indeterminate trusses having members stressed beyond the proportional limit

Date: February 1, 1953
Creator: Wilder, Thomas W , III
Description: None
Contributing Partner: UNT Libraries Government Documents Department
An analysis of the factors affecting the loss in lift and shift in aerodynamic center produced by the distortion of a swept wing under aerodynamic load

An analysis of the factors affecting the loss in lift and shift in aerodynamic center produced by the distortion of a swept wing under aerodynamic load

Date: March 1, 1953
Creator: Mathews, Charles W & Kurbjun, Max C
Description: None
Contributing Partner: UNT Libraries Government Documents Department
An analysis of the power-off landing maneuver in terms of the capabilities of the pilot and the aerodynamic characteristics of the airplane

An analysis of the power-off landing maneuver in terms of the capabilities of the pilot and the aerodynamic characteristics of the airplane

Date: August 1, 1953
Creator: Von Doenhoff, Albert E & Jones, George W , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
An analysis of turbojet-engine-inlet matching

An analysis of turbojet-engine-inlet matching

Date: September 1, 1953
Creator: Wyatt, Demarquis
Description: A method of presenting turbojet-engine air-flow requirements and inlet-system air-flow capacities in identical though independent parametric terms is developed. The application of the air-flow representation technique to the analysis of engine-inlet matching conditions is demonstrated. Several examples are presented to illustrate the application of the method to the explicit determination of inlet geometric variations required to improve the power-plant performance of supersonic airplanes.
Contributing Partner: UNT Libraries Government Documents Department
Analysis of turbulent heat transfer and flow in the entrance regions of smooth passages

Analysis of turbulent heat transfer and flow in the entrance regions of smooth passages

Date: October 1, 1953
Creator: Deissler, Robert G
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Analytical investigation of icing limit for diamond-shaped airfoil in transonic and supersonic flow

Analytical investigation of icing limit for diamond-shaped airfoil in transonic and supersonic flow

Date: January 1, 1953
Creator: Callaghan, Edmund E & Serafini, John S
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Analytical Investigation of Icing Limit for Diamond-Shaped Airfoil in Transonic and Supersonic Flow

Analytical Investigation of Icing Limit for Diamond-Shaped Airfoil in Transonic and Supersonic Flow

Date: January 1, 1953
Creator: Callaghan, Edmund E. & Serafini, John S.
Description: Calculations have been made for the icing limit of a diamond airfoil at zero angle of attack in terms of the stream Mach number, stream temperature, and pressure altitude. The icing limit is defined as a wetted-surface temperature of 320 F and is related to the stream conditions by the method of Hardy. The results show that the point most likely to ice on the airfoil lies immediately behind the shoulder and is subject to possible icing at Mach numbers as high as 1.4.
Contributing Partner: UNT Libraries Government Documents Department
An analytical investigation of the effect of the rate of increase of turbulent kinetic energy in the stream direction on the development of turbulent boundary layers in adverse pressure gradients

An analytical investigation of the effect of the rate of increase of turbulent kinetic energy in the stream direction on the development of turbulent boundary layers in adverse pressure gradients

Date: November 1, 1953
Creator: Rashis, Bernard
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Application of a characteristic blade-to-blade solution to flow in a supersonic rotor with varying stream-filament thickness

Application of a characteristic blade-to-blade solution to flow in a supersonic rotor with varying stream-filament thickness

Date: August 1, 1953
Creator: Costilow, Eleanor L
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Application of an electro-optical two-color pyrometer to measurement of flame temperature for liquid oxygen-hydrocarbon propellant combination

Application of an electro-optical two-color pyrometer to measurement of flame temperature for liquid oxygen-hydrocarbon propellant combination

Date: October 1, 1953
Creator: Heidmann, M F & Priem, R J
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Application of several methods for determining transfer functions and frequency response of aircraft from flight data

Application of several methods for determining transfer functions and frequency response of aircraft from flight data

Date: September 1, 1953
Creator: Eggleston, John M & Mathews, Charles W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Application of silver chloride in investigations of elasto-plastic states of stress

Application of silver chloride in investigations of elasto-plastic states of stress

Date: November 1, 1953
Creator: Goodman, L E & Sutherland, J G
Description: None
Contributing Partner: UNT Libraries Government Documents Department
An application of the method of characteristics to two-dimensional transonic flows with detached shock waves

An application of the method of characteristics to two-dimensional transonic flows with detached shock waves

Date: March 1, 1953
Creator: Harder, Keith C & Klunker, E B
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Appraisal of hazards to human survival in airplane crash fires

Appraisal of hazards to human survival in airplane crash fires

Date: September 1, 1953
Creator: Pesman, Gerard J
Description: None
Contributing Partner: UNT Libraries Government Documents Department
An approximate method of calculating the deformations of wings having swept, M or W, ? and swept-tip plan forms

An approximate method of calculating the deformations of wings having swept, M or W, ? and swept-tip plan forms

Date: October 1, 1953
Creator: Zender, George W & Brooks, William A , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
FIRST PREV 1 2 3 4 5 NEXT LAST