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Variation in the Number of Revolutions of Air Propellers
Note describing the variation in the number of revolutions per minute and provides simple formulas that allow for advanced calculation to be made of the variation of propeller speed with variation of one or more dimensions of the propeller and allow the necessary corrections to be applied.
Date:
March 1923
Creator:
Achenbach, W.
System:
The UNT Digital Library
Theoretical study of the lateral frequency response to gusts of a fighter airplane, both with controls fixed and with several types of autopilots
Report presenting a theoretical approach to determine the lateral frequency response of a fighter airplane to side gusts and rolling gusts at a Mach number of 0.7 and an altitude of 30,000 feet. Frequency response and power spectral density were determined with the controls fixed and in combination with three different basic types of attitude autopilots.
Date:
March 1956
Creator:
Adams, James J. & Mathews, Charles W.
System:
The UNT Digital Library
The asymmetric adjustable supersonic nozzle for wind-tunnel application
Report presenting the development of an asymmetric type of adjustable supersonic nozzle suitable for application to wind tunnels. This type of nozzle permits continuous adjustment of the test-section Mach number without the requirement of flexible walls.
Date:
March 1953
Creator:
Allen, H. Julian
System:
The UNT Digital Library
Tank Tests of Model 36 Flying Boat Hull
"N.A.C.A. Model 36, a hull form with parallel middle body for half the length of the forebody and designed particularly for use with stub wings, was tested according to the general fixed-trim method over the range of practical loads, trims, and speeds. It was also tested free to trim with the center of gravity at two different positions. The results are given in the form of nondimensional coefficients. The resistance at the hump was exceptionally low but, at high planing speeds, afterbody interference made the performance only mediocre" (p. 1).
Date:
March 1938
Creator:
Allison, John M.
System:
The UNT Digital Library
Charts for estimation of longitudinal-stability derivatives for a helicopter rotor in forward flight
Report presenting charts to provide a convenient means for obtaining the derivatives of rotor resultant force, rotor pitching amount about the helicopter center of gravity, and rotor torque with respect to rotor angle of attack, forward speed, rotor speed, and collective pitch.
Date:
March 1951
Creator:
Amer, Kenneth B. & Gustafson, Frederic Bowen
System:
The UNT Digital Library
Investigation of a Slat in Several Different Positions on an NACA 64A010 Airfoil for a Wide Range of Subsonic Mach Numbers
Report presenting the two-dimensional aerodynamic characteristics of an NACA 64A010 airfoil with a slat at a range of Mach numbers. Two types of slat positions were investigated, one with the slat leading edge extended forward along the airfoil chord line and one with the slat extended forward and displaced below the chord line. Results regarding lift, drag, pitching moment, and pressure distribution are provided.
Date:
March 1954
Creator:
Axelson, John A. & Stevens, George L.
System:
The UNT Digital Library
Aerodynamic Rolling and Yawing Moments Produced by Floating Wing-Tip Ailerons, as Measured by Spinning Balance
From Summary: "The investigation described in this report was made to determine the effectiveness of floating wing-tip ailerons as an airplane control in the spin. In these tests the ailerons, not being balanced, were set parallel to the axis of rotation, which is probably very nearly the attitude that balanced floating ailerons would assume in a spin. Rolling - and yawing moment coefficients are given as measured for the model with and without the ailerons, and computed values are given for the ailerons alone."
Date:
March 1934
Creator:
Bamber, Millard J.
System:
The UNT Digital Library
Thermal Conductance of Contacts in Aircraft Joints
Note presenting tests conducted to determine the factors influencing the thermal conductance across the interference between 75S-T6 aluminum-alloy and AISI Type 416 stainless-steel structural joints. The type of joints investigated included: bare metal-to-metal contact, contact surfaces coated with zinc-chromate primer, contact surfaces separated by thin foils of good conductors, contact surfaces separated by thin sheets of insulation, contact surfaces joined by strength-giving bonds, and riveted joints. The factors investigated were heat flow, temperature drop, temperature level, and surface condition.
Date:
March 1954
Creator:
Barzelay, Martin E.; Tong, Kin Nee & Hollo, George
System:
The UNT Digital Library
Critical Combinations of Shear and Direct Stress for Simply Supported Rectangular Flat Plates
Note presenting an investigation of the buckling of a simply supported rectangular flat plate under combinations of shear and direct stress by means of an energy method. The critical combinations of stress for several length-width ratios were determined to an accuracy of about 1 percent in conjunction with a modified matrix iteration method. Results regarding the shear and longitudinal stress and shear and transverse stress are provided.
Date:
March 1947
Creator:
Batdorf, S. B. & Stein, Manuel
System:
The UNT Digital Library
Static stability of fuselages having a relatively flat cross section
Report presenting an investigation in the free-flight tunnel to determine the static stability characteristics of several fuselages with a relatively flat cross section and a high fineness ratio. Results regarding the fuselages alone and fuselages with various vertical and horizontal surfaces are provided.
Date:
March 1955
Creator:
Bates, William R.
System:
The UNT Digital Library
Wake measurements behind a wing section of a fighter airplane in fast dives
Report presenting wake measurements made in a vertical plane behind a wind section of a fighter airplane for a range of Mach numbers up to 0.78. The critical Mach number of each wing section was exceeded by 0.05 before large increases in the profile-drag coefficient occurred.
Date:
March 1947
Creator:
Beeler, De E. & Gerard, George
System:
The UNT Digital Library
Effect of Wall Cooling on Inlet Parameters of a Scoop Operating in a Turbulent Boundary Layer on a Flat or Conical Surface for Mach Numbers 2 to 10
Note presenting analytical results obtained for boundary-layer mass flow, momentum, total-temperature, and total-pressure recovery ratios of a scoop inlet with a height equal to the boundary-layer thickness and operating in a turbulent boundary layer, for flat and conical surfaces with wall cooling. The results indicate that design of boundary-layer intake devices or diverters must reflect the effects of wall cooling by either variable or compromised size.
Date:
March 1958
Creator:
Beke, Andrew
System:
The UNT Digital Library
Matrix Methods for Calculating Cantilever-Beam Deflections
Note presenting the method of numerical integration for calculation of beam deflection in matrix form to give it the advantages which are inherent in an influence-coefficient method. Examples are presented to show that the use of weighted matrices reduces the calculation time required to obtain a desired degree of accuracy.
Date:
March 1949
Creator:
Benscoter, Stanley U. & Gossard, Myron L.
System:
The UNT Digital Library
Effects of Parallel-Jet Mixing on Downstream Mach Number and Stagnation Pressure With Application to Engine Testing in Supersonic Tunnels
"A one-dimensional analysis of the results of the parallel-jet mixing encountered in the testing of engines in supersonic wind tunnels is reported. Equations were derived for determining the totla pressure and Mach number behind the tunnel terminal shock. The method represents a simple procedure for determining these quantities while a tunnel is still in the design stage" (p. 1).
Date:
March 1953
Creator:
Bernstein, Harry
System:
The UNT Digital Library
On a Method of Constructing Two-Dimensional Subsonic Compressible Flows Around Closed Profiles
Note showing that under certain conditions, a two-dimensional subsonic compressible flow around an airfoil profile can be derived from an incompressible flow around another profile. The connection between the two "conjugate flows" is given by a simple conformal transformation of the respective hodograph planes.
Date:
March 1945
Creator:
Bers, Lipman
System:
The UNT Digital Library
Velocity Distribution on Wing Sections of Arbitrary Shape in Compressible Potential Flow 3: Circulatory Flows Obeying the Simplified Density-Speed Relation
"The method of computing velocity and pressure distributions along wing profiles under the assumption of the simplified density-speed relation, outlined in NACA Technical Note 1006, is extended to the case of a nonsymmetrical profile and a flow with circulation. The shape of the profile, the speed of the undisturbed flow, and a parameter determining the angle of attack may be prescribed. The problem is reduced to a nonlinear integral equation which can be solved numerically by an iteration method" (p. 1).
Date:
March 1950
Creator:
Bers, Lipman
System:
The UNT Digital Library
Influence of Span and Load Per Square Meter on the Air Forces of the Supporting Surface
"It should be clear that in order to obtain a lift it is necessary that the air which flows past an aerofoil be given a downward acceleration; indeed the lift can be only the reaction produced by the downward acceleration of the flowing air. The motion of the air in the neighborhood of an aerofoil may be followed theoretically with great exactness. In the following, it will be undertaken to make understood, through the simplest possible considerations, the effect of span and loading on the air force on an aerofoil, and while these do not form a strong proof of the correctness of the formulae developed, yet they explain the essential features of the phenomena" (p. 1).
Date:
March 1921
Creator:
Betz, A.
System:
The UNT Digital Library
Interaction of Column and Local Buckling in Compression Members
Note presenting two methods for calculating actual buckling stress, including the author's exact theory and the method of split rigidities, both of which lead almost identical results. Columns with box-, I-, H-, and T-sections and angles are considered separately.
Date:
March 1952
Creator:
Bijlaard, P. P. & Fisher, G. P.
System:
The UNT Digital Library
Linearized Lifting-Surface and Lifting-Line Evaluations of Sidewash Behind Rolling Triangular Wings at Supersonic Speeds
Note presenting the lifting-surface sidewash behind rolling triangular wings for a range of supersonic Mach numbers for which the wing leading edges remain swept behind the Mach cone emanating from the wing apex. Variations of the sidewash with longitudinal distance in the vertical plane of symmetry are presented in graphical form.
Date:
March 1956
Creator:
Bobbitt, Percy J.
System:
The UNT Digital Library
An investigation of aircraft heaters 33: experimental determination of thermal and hydrodynamical behavior of air flowing along finned plates
Report presenting an experimental investigation on the thermal and hydrodynamical behavior of air flowing along a steam-heated plate to which were attached cylindrical fins. The data indicate that the principal criterion for the application of the equations for heat transfer along unfinned flat plates is the initiation of a thermal boundary layer.
Date:
March 1950
Creator:
Boelter, L. M. K.; Leasure, R.; Romie, F. E.; Sanders, V. D.; Elswick, W. R. & Young, G.
System:
The UNT Digital Library
Effect of Exhaust Pressure on the Performance of an 18-Cylinder Air-Cooled Radial Engine with a Valve Overlap of 40 Degrees
Note presenting an investigation to determine the effect of exhaust pressure on the performance of an 18-cylinder air-cooled radial engine equipped with a conventional exhaust collector ring. The engine power increased at a diminishing rate as exhaust pressure decreased.
Date:
March 1947
Creator:
Boman, David S.; Nagey, Tibor F. & Doyle, Ronald B.
System:
The UNT Digital Library
Shear Lag in a Plywood Sheet-Stringer Combination Used for the Chord Member of a Box Beam
"Theoretical and experimental investigations were made of the distribution of strains in a plywood sheet-stringer combination used as the chord member of a box beam acted upon by bending loads. The theoretical solution was obtained with the help of the principle of minimum potential energy and certain simplifying assumptions. Strain measurements were made on a build-up box beam by means of electrical-resistance strain gages connected with strain indicators" (p. 1).
Date:
March 1948
Creator:
Borsari, Palamede & Yu, Ai-Ting
System:
The UNT Digital Library
Combustion-engine temperatures by the sodium line-reversal method
The sodium line-reversal method has been used in some preliminary measurements of flame temperature. Improvements in the method involving a photographic recorder and a means of correcting for the dirtiness of the windows are described. The temperatures so obtained are compared with those calculated from pressure diagrams.
Date:
March 1936
Creator:
Brevoort, Maurice J.
System:
The UNT Digital Library
Turbulent-heat-transfer measurements at a Mach number of 2.06
Report presenting turbulent-heat-transfer measurements obtained through the use of an axially symmetric annual nozzle consisting of an inner shaped center body and an outer cylindrical sleeve at Mach number 2.06. Results regarding the variation of wall temperature with longitudinal distance, variation of local Nusselt number with local Reynolds number, and variation of local temperature-recovery factor with local Reynolds number are provided.
Date:
March 1955
Creator:
Brevoort, Maurice J. & Rashis, Bernard
System:
The UNT Digital Library