This system will be undergoing maintenance Tuesday, December 6 from 9AM to 12PM CST.

  You limited your search to:

 Serial/Series Title: NACA Advanced Restricted Report
 Serial/Series Title: NACA Wartime Reports
 Collection: Technical Report Archive and Image Library
Aerodynamic and hydrodynamic tests of a family of models of flying-boat hulls derived from a streamline body : NACA model 84 series

Aerodynamic and hydrodynamic tests of a family of models of flying-boat hulls derived from a streamline body : NACA model 84 series

Date: September 1943
Creator: Luoma, Arvo A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic tests of a full-scale TBF-1 aileron installation in the Langley 16-foot high-speed tunnel

Aerodynamic tests of a full-scale TBF-1 aileron installation in the Langley 16-foot high-speed tunnel

Date: December 1944
Creator: Becker, John V & Korycinski, Peter F
Description: The failure of wing panels on a number of TBF-1 and TBM-1 airplanes in flight has prompted several investigations of the possible causes of failure. This report describes tests in the Langley 16-foot high-speed tunnel to determine whether these failures could be attributed to changes in the aerodynamic characteristics of the ailerons at high speeds. The tests were made of a 12-foot-span section including the tip and aileron of the right wing of a TBF-1 airplane. Hinge moments, control-link stresses due to aerodynamic buffeting, and fabric-deflection photographs were obtained at true airspeeds ranging from 110 to 365 miles per hour. The aileron hinge-moment coefficients were found to vary only slightly with airspeed in spite of the large fabric deflections that developed as the speed was increased. An analysis of these results indicated that the resultant hinge moment of the ailerons as installed in the airplane would tend to restore the ailerons to their neutral position for all the high-speed flight conditions covered in the tests. Serious aerodynamic buffeting occurred at up aileron angles of -10 degrees or greater because of stalling of the sharp projecting lip of the Frise aileron. The peak stresses set up in the aileron control linkages ...
Contributing Partner: UNT Libraries Government Documents Department
Air-consumption parameters for automatic mixture control of aircraft engines

Air-consumption parameters for automatic mixture control of aircraft engines

Date: September 1944
Creator: Shames, Sidney J
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Airfoil-contour modifications based on (epsilon)-curve method of calculating pressure distribution

Airfoil-contour modifications based on (epsilon)-curve method of calculating pressure distribution

Date: July 1, 1944
Creator: Theodorsen, Theodore
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Airspeed fluctuations as a measure of atmospheric turbulence

Airspeed fluctuations as a measure of atmospheric turbulence

Date: July 1945
Creator: Tolefson, H B
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Analysis of a thermal ice-prevention system for wing leading-edge landing-light installations

Analysis of a thermal ice-prevention system for wing leading-edge landing-light installations

Date: January 1, 1944
Creator: Hillendahl, Wesley H
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Analysis of factors affecting net lift increment attainable with trailing-edge split flaps on tailless airplanes

Analysis of factors affecting net lift increment attainable with trailing-edge split flaps on tailless airplanes

Date: September 1944
Creator: Maggin, Bernard
Description: None
Contributing Partner: UNT Libraries Government Documents Department
An analysis of life expectancy of airplane wings in normal cruising flight

An analysis of life expectancy of airplane wings in normal cruising flight

Date: July 1, 1945
Creator: Putnam, Abbott A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
An analysis of the skipping characteristics of some full-size flying boats

An analysis of the skipping characteristics of some full-size flying boats

Date: January 1946
Creator: Locke, F. W. S., Jr.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Analysis of wind-tunnel stability and control tests in terms of flying qualities in full-scale airplanes

Analysis of wind-tunnel stability and control tests in terms of flying qualities in full-scale airplanes

Date: October 1943
Creator: Kayten, Gerald G
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Application of a numerical procedure to stress analysis of stringer-reinforced panels

Application of a numerical procedure to stress analysis of stringer-reinforced panels

Date: March 1, 1945
Creator: Kempner, Joseph
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The application of data on strength under repeated stresses to the design of aircraft

The application of data on strength under repeated stresses to the design of aircraft

Date: October 1945
Creator: Grover, H. J.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Application of spring tabs to elevator controls

Application of spring tabs to elevator controls

Date: October 1, 1944
Creator: Phillips, William H
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Application of the method of least squares to engine-cooling analysis

Application of the method of least squares to engine-cooling analysis

Date: August 1944
Creator: Corson, Blake W , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Artificial running-in of piston rings

Artificial running-in of piston rings

Date: March 1, 1944
Creator: Machlin, E S
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Bending and shear stresses developed by the instantaneous arrest of the root of a cantilever beam rotating with constant angular velocity about a transverse axis through the root

Bending and shear stresses developed by the instantaneous arrest of the root of a cantilever beam rotating with constant angular velocity about a transverse axis through the root

Date: June 1, 1945
Creator: Stowell, Elbridge Z; Schwartz, Edward B & Houbolt, John C
Description: A theoretical investigation was made of the behavior of a cantilever beam in rotational motion about a transverse axis through the root determining the stresses, the deflections, and the accelerations that occur in the beam as a result of the arrest of motion. The equations for bending and shear stress reveal that, at a given percentage of the distance from root to tip and at a given trip velocity, the bending stresses for a particular mode are independent of the length of the beam and the shear stresses vary inversely with the length. When examined with respect to a given angular velocity instead of a given tip velocity, the equations reveal that the bending stress is proportional to the length of the beam whereas the shear stress is independent of the length. Sufficient experimental verification of the theory has previously been given in connection with another problem of the same type.
Contributing Partner: UNT Libraries Government Documents Department
Bending and shear stresses developed by the instantaneous arrest of the root of a moving cantilever beam

Bending and shear stresses developed by the instantaneous arrest of the root of a moving cantilever beam

Date: November 1, 1944
Creator: Houbolt, John C
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Breaking aircraft-engine oil foams by use of electrically charged condenser plates

Breaking aircraft-engine oil foams by use of electrically charged condenser plates

Date: November 1, 1944
Creator: Pinkel, I Irving
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Calculations of economy of 18-cylinder radial aircraft engine with exhaust-gas turbine geared to the crankshaft at cruising speed

Calculations of economy of 18-cylinder radial aircraft engine with exhaust-gas turbine geared to the crankshaft at cruising speed

Date: January 1, 1945
Creator: Zimmerman, Richard H
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Calculations of the Performance of a Compression-Ignition Engine-Compressor Turbine Combination I : Performance of a Highly Supercharged Compression-Ignition Engine

Calculations of the Performance of a Compression-Ignition Engine-Compressor Turbine Combination I : Performance of a Highly Supercharged Compression-Ignition Engine

Date: December 1, 1945
Creator: Sanders, J. C. & Mendelson, Alexander
Description: Small high-speed single-cylinder compression-ignition engines were tested to determine their performance characteristics under high supercharging. Calculations were made on the energy available in the exhaust gas of the compression-ignition engines. The maximum power at any given maximum cylinder pressure was obtained when the compression pressure was equal to the maximum cylinder pressure. Constant-pressure combustion was found possible at an engine speed of 2200 rpm. Exhaust pressures and temperatures were determined from an analysis of indicator cards. The analysis showed that, at rich mixtures with the exhaust back pressure equal to the inlet-air pressure, there is excess energy available for driving a turbine over that required for supercharging. The presence of this excess energy indicates that a highly supercharged compression-ignition engine might be desirable as a compressor and combustion chamber for a turbine.
Contributing Partner: UNT Libraries Government Documents Department
Charts for calculation of the critical compressive stress for local instability of idealized web- and T-stiffened panels

Charts for calculation of the critical compressive stress for local instability of idealized web- and T-stiffened panels

Date: August 1, 1944
Creator: Baab, George W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Charts for calculation of the critical stress for local instability of columns with I-, Z-, channel and rectangular-tube section

Charts for calculation of the critical stress for local instability of columns with I-, Z-, channel and rectangular-tube section

Date: November 1, 1943
Creator: Heimerl, George J
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Charts for critical combinations of longitudinal and transverse direct stress for flat rectangular plates

Charts for critical combinations of longitudinal and transverse direct stress for flat rectangular plates

Date: March 1, 1946
Creator: Stein, Manuel
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Charts for determining jet-boundary corrections for complete models in 7- by 10-foot closed rectangular wind tunnels

Charts for determining jet-boundary corrections for complete models in 7- by 10-foot closed rectangular wind tunnels

Date: September 1, 1945
Creator: Gray, Joseph L , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
FIRST PREV 1 2 3 4 5 NEXT LAST