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Analysis of horizontal-tail loads in pitching maneuvers on a flexible swept-wing jet bomber
From Introduction: "The analysis of flight data in the present report is, to a large extent, based on analyses and information contained in references 1 and 2 for wing deflections, reference 3 for horizontal-tail parameters, reference 4 for airplane lift-curve slopes and angles of zero lift, and reference 5 for wing centers of pressure."
Date:
December 1957
Creator:
Aiken, William S., Jr.
System:
The UNT Digital Library
Extension of Pack Method for Compressive Tests
"The pack method for determining compressive stress-strain graphs described in NACA Report No. 649 has been modified to extend it's application to thinner gages and stronger materials. The principal modifications consisted in the provision of additional support against instability cementing the specimens of the pack together with fused shellac and the provision of special clamps to hold the specimens together while the test is in progress. The shellac was found to increase the buckling load of the pack without any appreciable effect on the compressive stress-strain graph of the material" (p. 1).
Date:
December 1940
Creator:
Aitchison, C. S.
System:
The UNT Digital Library
A Subpress for Compressive Tests
"A subpress for compressive tests is described. The subpress was designed primarily for use in developing and investigating methods for testing thin sheet metal in compression. Provision was made for testing fixed-end and flat-end specimens with or without various types of lateral support against buckling. Compressive stress-strain data for a sheet of 0.032-inch 24S-RT aluminum alloy were obtained with the subpress by the pack method and by the single-thickness method" (p. 1).
Date:
December 1943
Creator:
Aitchison, C. S. & Miller, James A.
System:
The UNT Digital Library
Tensile and Compressive Tests of Magnesium Alloy J-1 Sheet
Note presenting tensile and compressive stress-strain curves, stress-deviation curves, and secant modulus-stress curves for longitudinal and transverse specimens of magnesium alloy J-1 sheets 0.032 and 0.102 inch thick. Significant differences were found between the tensile and compressive stress-strain curves and between the compressive stress-strain curves for the longitudinal and transverse questions.
Date:
December 1943
Creator:
Aitchison, C. S. & Miller, James A.
System:
The UNT Digital Library
Effect of Concentration on Ignition Delays for Various Fuel-Oxygen-Nitrogen Mixtures at Elevated Temperatures
Note presenting measurements of ignition delays for mixtures of ethane, n-butane, isobutane, hydrogen, or propane with oxygen and nitrogen using a flow system with two experimental procedures. Delays were measured over a range of temperatures for each gas. Results regarding a comparison among fuels and effect of experimental procedure on absolute values of ignition delay are provided.
Date:
December 1956
Creator:
Anagnostou, E.; Brokaw, R. S. & Butler, J. N.
System:
The UNT Digital Library
Charts for determining the pitching moment of tapered wings with sweepback and twist
From Summary: "This report presents a convenient method for calculating the pitching-moment characteristics of tapered wings with sweepback and twist. The method is based on the fact that the pitching-moment characteristics of a wing may be specified by giving the value of the pitching moment at zero lift and the location of the axis about which the axis is constant. Data for calculating these characteristics are presented by curves which apply to wings having a linear distribution of twist along the span and which cover a large range of aspect ratios. The curves are given for wings having straight taper and distorted elliptical plan forms. The characteristics of wings of other shapes may be determined by interpolation."
Date:
December 1933
Creator:
Anderson, Raymond F.
System:
The UNT Digital Library
Operating Characteristics of an Acceleration Restrictor as Determined by Means of a Simulator
Note presenting the operating characteristics of an acceleration restrictor which limits the normal acceleration of an airplane in maneuvers determined from tests on a simulator. The simulator consisted of a control stick geared to a magnetic brake unit and an analog computer which simulated the dynamic characteristics of the airplane.
Date:
December 1954
Creator:
Assadourian, Arthur
System:
The UNT Digital Library
Determination of the Flying Qualities of the Douglas DC-3 Airplane
Report presenting an evaluation of the flying qualities of the Douglas DC-3 airplane to determine its longitudinal and lateral stability and control characteristics and its stalling behavior.
Date:
December 1953
Creator:
Assadourian, Arthur & Harper, John A.
System:
The UNT Digital Library
Observations in Flight of the Region of Stalled Flow Over the Blades of an Autogiro Rotor
"The flow over the inner halves of the rotor blades on a Kellet YG-1B autogiro was investigated in flight by making camera records of the motion of silk streamers attached to the upper surfaces of the blades. These records were analyzed to determine the boundaries of the region within which the flow over the blade sections was stalled for various tip-speed ratios. For the sake of comparison, corresponding theoretical boundaries were obtained. Both the size of the stalled area and its rate of growth with increasing tip-speed ratio were found to be larger than the theory predicted, although experiment agreed with theory with regard to shape and general location of the stalled area" (p. 1).
Date:
December 1939
Creator:
Bailey, F. J., Jr. & Gustafson, F. B.
System:
The UNT Digital Library
Experimental Investigation of Flutter of a Propeller With Clark Y Section Operating at Zero Forward Velocity at Positive and Negative Blade-Angle Settings
Report presenting an investigation of the flutter of a small one-blade wooden propeller with a Clark Y section. The highest flutter speeds were found in the vicinity of the angle of zero aerodynamic moment, with flutter speed increasing in this region with decreasing pressure.
Date:
December 1949
Creator:
Baker, John E. & Paulnock, Russell S.
System:
The UNT Digital Library
Aerodynamic Effects of a Split Flap on the Spinning Characteristics of a Monoplane Model
From Summary: "The investigation described in this report was made to determine the change in aerodynamic forces and moments produced by split flaps in a steady spin. The test were made with the spinning balance in the NACA 5-foot vertical wind tunnel. A low-wing monoplane model was tested with and without the split flaps in 12 spinning attitudes chosen to cover the probable spinning range. The results obtained indicate that the use of split flaps on an airplane is unlikely, in any case, to have much beneficial effect on a spin, and it might make the spin dangerous."
Date:
December 1934
Creator:
Bamber, M. J.
System:
The UNT Digital Library
Spinning characteristics of wings 4: changes in stagger of rectangular Clark Y cellules
Report presenting testing of rectangular Clark-Y biplane cellules with zero and -0.25 stagger, the gap equal to the chord, and 0 degrees decalage were tested on the NACA spinning balance in the 5-foot vertical tunnel.
Date:
December 1937
Creator:
Bamber, M. J. & House, R. O.
System:
The UNT Digital Library
Progress Made in the Construction of Giant Airplanes in Germany During the War
The construction of giant airplanes was begun in Germany in August, 1914. The tables annexed here show that a large number of airplanes weighing up to 15.5 tons were constructed and tested in Germany during the War, and it is certain that no other country turned out airplanes of this weight nor in such large numbers. An examination of the tables shows that by the end of the War all the manufacturers had arrived at a well-defined type, namely an airplane of about 12 tons with four engines of 260 horsepower each. The aircraft listed here are discussed with regard to useful weight and aerodynamic qualities.
Date:
December 1920
Creator:
Baumann, A.
System:
The UNT Digital Library
Heat transfer and recovery temperatures on a sphere with laminar, transitional, and turbulent boundary layers at Mach numbers of 2.00 and 4.15
Report presenting an investigation of the pressure and equilibrium-temperature distributions on a sphere at Mach numbers of 2.00 and 4.15. The local aerodynamic heat transfer was measured on a sphere at Mach number 2.00 and on a hemisphere-cylinder at Mach number 4.15. Results regarding pressure distributions, equilibrium and recovery temperatures, heat-transfer coefficients, and effect of roughness on transition are provided.
Date:
December 1957
Creator:
Beckwith, Ivan E. & Gallagher, James J.
System:
The UNT Digital Library
On Supersonic and Partially Supersonic Flows
Note presenting an extension of the analytical methods used to successfully in the theory of an incompressible fluid to the case of a compressible fluid.
Date:
December 1946
Creator:
Bergman, Stefan
System:
The UNT Digital Library
Application of the Von Kármán momentum theorem to turbulent boundary layers
Report presenting a study of the Von Kármán momentum theorum with respect to its application to turbulent boundary layers in a positive pressure gradient. The results indicate that the streamwise derivative of the turbulent longitudinal momentum may be large near the separation and therefore should be considered when the momentum theorum is used for turbulent boundary layers near separation.
Date:
December 1951
Creator:
Bidwell, Jerold M.
System:
The UNT Digital Library
The planing characteristics of a surface having a basic angle of dead rise of 40 degrees and horizontal chine flare
Report presenting an experimental investigation with a surface with a dead rise angle of 40 degrees and horizontal chine flare to determine the effects of increasing the angle of dead rise on the planing characteristics of horizontally flared prismatic surfaces. Wetted length, resistance, center-of-pressure location, and draft were determined for a range of speed coefficients and trims. Planing characteristics for a given trim were found to depend mainly on lift coefficient.
Date:
December 1952
Creator:
Blanchard, Ulysse J.
System:
The UNT Digital Library
Theoretical Calculations of the Lateral Stability Derivatives for Triangular Vertical Tails with Subsonic Leading Edges Traveling at Supersonic Speeds
Note presenting pressure-distribution expressions and stability derivatives derived by use of linear theory for zero-end-plate triangular vertical tails with subsonic leading edges performing rolling, yawing, and constant-lateral-acceleration motions. Corresponding results for the sideslip motion, most of which have been previously reported, are also included.
Date:
December 1954
Creator:
Bobbitt, Percy J.
System:
The UNT Digital Library
Creep Deformation Patterns of Joints Under Bearing and Tensile Loads
Note presenting an investigation to study the interaction of bearing and tensile loads on the creep behavior of joints. A simplified model was employed which contained many of the features found in riveted connections. Results regarding creep-rupture tests, plate subjected to tension, plate subjected to bearing loads, plate subjected to tensile and bearing loads, and index of joint behavior are provided.
Date:
December 1957
Creator:
Bodine, E. G.; Carlson, R. L. & Manning, G. K.
System:
The UNT Digital Library
Turbulent-heat-transfer measurements at a Mach number of 0.87
Report presenting turbulent-heat-transfer measurements obtained through the use of an axially symmetric annular nozzle consisting of an inner shaped center body and an outer cylindrical sleeve. Results regarding the wall temperatures, variation of local Nusselt number with Reynolds number, density, velocity, and local temperature-recovery factor are provided.
Date:
December 1955
Creator:
Brevoort, Maurice J. & Rashis, Bernard
System:
The UNT Digital Library
Boundary-layer transition at Mach 3.12 with and without single roughness elements
Report presenting temperatures on the external surface of a straight hollow cylinder aligned parallel to the air stream. Results regarding the recovery-factor distribution without roughness, transition without roughness, transition caused by roughness, and analysis of roughness results are provided.
Date:
December 1954
Creator:
Brinich, Paul F.
System:
The UNT Digital Library
Investigation at supersonic speeds of the wave drag of seven boattail bodies of revolution designed for minimum wave drag
Report presenting an investigation in the 9-inch supersonic tunnel to determine the effects of varying Reynolds number at each of three Mach numbers on the wave drag of seven boattail bodies of revolution designed for minimum wave drag. Results indicated that there was little variation in the pressure distribution with Reynolds number. Results regarding pressure distributions and wave drag are provided.
Date:
December 1953
Creator:
Bromm, August F., Jr. & Goodwin, Julia M.
System:
The UNT Digital Library
Analytical determination of the natural coupled frequencies and mode shapes and the response to oscillating forcing functions of tandem helicopters
Report presenting a method for the analytical determination of the natural coupled frequencies and mode shapes of vibrations in the vertical plane of tandem helicopters. That information is then used to calculate the response of the helicopter to applied oscillation forces. Calculated response curves show how the vibrations of the cockpit vary with frequency and method of application of oscillating forces applied at the hubs.
Date:
December 1956
Creator:
Brooks, George W. & Houbolt, John C.
System:
The UNT Digital Library
Theoretical lift and drag of thin triangular wings at supersonic speeds
Report presenting a method for calculating the lift and drag due to lift of point-forward triangular wings and a restricted series of sweptback wings at supersonic speeds.
Date:
December 1946
Creator:
Brown, Clinton E.
System:
The UNT Digital Library