You limited your search to:

  Partner: UNT Libraries Government Documents Department
 Serial/Series Title: NACA Wartime Reports
 Collection: Technical Report Archive and Image Library
An evaluation of the knock-limited performance of triptane

An evaluation of the knock-limited performance of triptane

Date: March 1, 1946
Creator: Barnett, Henry C
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Lead susceptibility of paraffins, cycloparaffins, and olefins

Lead susceptibility of paraffins, cycloparaffins, and olefins

Date: May 1, 1943
Creator: Barnett, Henry C
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Smoking characteristics of various fuels as determined by open-cup and laboratory-burner smoke tests

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

Date: September 1, 1945
Creator: Barnett, Henry C
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Investigation of air flow in right-angle elbows in a rectangular duct

Investigation of air flow in right-angle elbows in a rectangular duct

Date: October 1, 1941
Creator: Bartlett, Walter A , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Wind-tunnel tests of a dual-rotating propeller having one component locked or windmilling

Wind-tunnel tests of a dual-rotating propeller having one component locked or windmilling

Date: January 1, 1945
Creator: Bartlett, Walter A , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Shear tests on DuPont explosive rivets with the countersunk head milled flush after expansion

Shear tests on DuPont explosive rivets with the countersunk head milled flush after expansion

Date: May 1, 1943
Creator: Bartone, Leonard M
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Tensile Tests of NACA and Conventional Machine- Countersunk Flush Rivets

Tensile Tests of NACA and Conventional Machine- Countersunk Flush Rivets

Date: October 1, 1944
Creator: Bartone, Leonard M. & Mandel, Merven W.
Description: An investigation was conducted to determine and compare the tensile strength of NACA and conventional machine-countersunk flush rivets of several rivet-head angles and varying countersunk depth. The results of the investigation are presented in the form of curves that show the variation of the tensile strength of the rivet with the ratio of the sheet thickness to the rivet diameter. For the same rivet-head angle and for a given angle of c/d, the NACA rivets developed higher tensile strength than the conventional rivets.
Contributing Partner: UNT Libraries Government Documents Department
The NACA impact basin and water landing tests of a float model at various velocities and weights

The NACA impact basin and water landing tests of a float model at various velocities and weights

Date: August 1, 1944
Creator: Batterson, Sidney A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Variation of hydrodynamic impact loads with flight-path angle for a prismatic float at 3 degree trim and with a 22 1/2 degree angle of dead rise

Variation of hydrodynamic impact loads with flight-path angle for a prismatic float at 3 degree trim and with a 22 1/2 degree angle of dead rise

Date: February 1, 1945
Creator: Batterson, Sidney A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Variation of hydrodynamic impact loads with flight-path angle for a prismatic float at 12 degree trim and with a 22-1/2 degree angle of dead rise

Variation of hydrodynamic impact loads with flight-path angle for a prismatic float at 12 degree trim and with a 22-1/2 degree angle of dead rise

Date: February 1, 1946
Creator: Batterson, Sidney A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Flight measurements by various methods of the drag characteristics of the XP-51 airplane

Flight measurements by various methods of the drag characteristics of the XP-51 airplane

Date: June 1, 1946
Creator: Beadle, Dorothy E
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Fatigue characteristics of spot-welded 24S-T aluminum alloy

Fatigue characteristics of spot-welded 24S-T aluminum alloy

Date: June 1, 1943
Creator: Beaver, W. W.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Boundary-Layer Transition on the N.A.C.A. 0012 and 23012 Airfoils in the 8-Foot High-Speed Wind Tunnel

Boundary-Layer Transition on the N.A.C.A. 0012 and 23012 Airfoils in the 8-Foot High-Speed Wind Tunnel

Date: January 1, 1940
Creator: Becker, John V
Description: None
Contributing Partner: UNT Libraries Government Documents Department
High-speed tests of radial-engine nacelles on a thick low-drag wing

High-speed tests of radial-engine nacelles on a thick low-drag wing

Date: May 1, 1942
Creator: Becker, John V
Description: None
Contributing Partner: UNT Libraries Government Documents Department
High-speed wind-tunnel tests of the NACA 23012 and 23012-64 airfoils

High-speed wind-tunnel tests of the NACA 23012 and 23012-64 airfoils

Date: February 1, 1941
Creator: Becker, John V
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Wind tunnel tests of air inlet and outlet openings on a streamline body

Wind tunnel tests of air inlet and outlet openings on a streamline body

Date: November 1, 1940
Creator: Becker, John V
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 1, 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
High-Speed Tests of a Ducted Body with Various Air-Outlet Openings

High-Speed Tests of a Ducted Body with Various Air-Outlet Openings

Date: May 1, 1942
Creator: Becker, John V. & Baals, Donald D.
Description: Test of a ducted body with Internal flow were made in the 8-foot high-speed wind tunnel for the purpose of studying the effects on external drag and an critical speed of the addition of efficient inlet and outlet openings to a basic streamline shape. Drag tests of a 13.6- inch-diameter streamline body of fineness ratio 6.14 were made at Mach numbers ranging from 0.20 to 0.75. The model was centrally mounted on a 9-percent-thick airfoil and was designed to have an efficient airfoil-body juncture and a high critical speed. An air inlet at the nose and various outlets at the tail were added: drag and internal-flow data were obtained over the given speed range. The critical speed of the ducted bodies was found to be as high as that of the streamline body. The external - drag with air flow through the body did not exceed the drag of the basic streamline shape. No appreciable variation in the efficiency of the diffuser section of the internal duct occurred throughout the Mach number range of the tests.
Contributing Partner: UNT Libraries Government Documents Department
Performance comparison of two deep inducers as separate components and in combination with an impeller

Performance comparison of two deep inducers as separate components and in combination with an impeller

Date: October 1, 1945
Creator: Beede, William L
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Maximum rates of control motion obtained from ground tests

Maximum rates of control motion obtained from ground tests

Date: May 1, 1944
Creator: Beeler, De E
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Continuous use of internal cooling to suppress knock in aircraft engines cruising at high power

Continuous use of internal cooling to suppress knock in aircraft engines cruising at high power

Date: August 1, 1944
Creator: Bell, Arthur H
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Spray characteristics of a powered dynamic model of a flying boat having a hull with a length-beam ratio of 9.0

Spray characteristics of a powered dynamic model of a flying boat having a hull with a length-beam ratio of 9.0

Date: January 1, 1946
Creator: Bell, Joe W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The knock-limited performance of several miscellaneous fuels blended with a base fuel I

The knock-limited performance of several miscellaneous fuels blended with a base fuel I

Date: July 1, 1944
Creator: Bellman, Donald R
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Wind-tunnel procedure for determination of critical stability and control characteristics of airplanes

Wind-tunnel procedure for determination of critical stability and control characteristics of airplanes

Date: April 1, 1944
Creator: Belsley, Steven E.
Description: None
Contributing Partner: UNT Libraries Government Documents Department