Resource Type
Partner
Collection
Technical Report Archive and Image Library
740
National Advisory Committee for Aeronautics Collection
509
Office of Scientific & Technical Information Technical Reports
227
TRAIL Microcard Collection
116
Texas State Publications
5
Docs In The News
2
Stillwater History Museum at the Sheerar, Stillwater, Oklahoma
2
General Collection
2
Boy and Girl Scout Annual Reports
1
Federal Communications Reports
1
2 More
Serial/Series Title
NACA Research Memorandums
269
NACA Technical Notes
133
Atomic Energy Commission Reports
113
NACA Technical Reports
54
NACA Technical Memorandums
50
United States Bureau of Mines Reports
47
Hanford Works Reports
33
Report of investigations (United States. Bureau of Mines)
30
HW (Series)
29
United States Geological Survey Reports
27
51 More
States
Gust-tunnel investigation of a wing model with semichord line swept back 30 degrees
Report presenting tests in the gust tunnel of the 30 degree sweptback wing model to provide information on some of the problems encountered in the prediction of gust loads for airplanes incorporating swept wings. The results indicate that within the scope of the data and the values of gradient distance investigated, the maximum acceleration increment depends on the slope of the lift curve of an equivalent straight wing multiplied by the cosine of the angle of sweep and on the effect of gradual penetration of the sweptback wing into the gust.
Date:
January 1949
Creator:
Reisert, Thomas D.
System:
The UNT Digital Library
Application of Radial-Equilibrium Condition to Axial-Flow Compressor and Turbine Design
Note presenting some of the basic general equations governing the three-dimensional compressible flow of gas through a compressor or a turbine in terms of velocity components, total enthalpy, and entropy. The equations are applied to investigate the maximum compatible number of the radial variations of the gas properties between successive blade rows that a designer is free to specify.
Date:
January 1949
Creator:
Wu, Chung-Hua & Wolfenstein, Lincoln
System:
The UNT Digital Library
Effect of hull length-beam ratio on the hydrodynamic characteristics of flying boats in waves
Report presenting an investigation of the take-off and landing behavior in waves of models of a hypothetical flying boat with hull length-beam ratios of 6 and 15. The flying boat had a design gross weight of 75,000 pounds, a wing loading of 41.1 pounds per square foot, and a power loading of 11.5 pounds per brake horsepower for take-off. Results regarding the landing behavior, spray characteristics, and taxiing and take-off behavior are provided.
Date:
January 1949
Creator:
Carter, Arthur W.
System:
The UNT Digital Library
Flight Investigation in Climb and at High Speed of a Two-Blade and a Three-Blade Propeller
Note presenting an investigation of a two-blade and a three-blade propeller on a slender-nose fighter airplane in climb and at high speed.
Date:
January 1949
Creator:
Hammack, Jerome B.
System:
The UNT Digital Library
Comparison of the structural efficiency of panels having straight-web and curved-web Y-section stiffeners
Report presenting comparisons of the structural efficiency of panels with straight-web and curved-web Y-section stiffeners. In the high-stress region in which failure is at least in part associated with local buckling, panels with curved-web Y-section stiffeners have higher structural efficiencies than panels with straight-web Y-section stiffeners, which is evidenced by higher average stresses at failure, smaller stiffener heights, or wider average spacing of rivet lines.
Date:
January 1949
Creator:
Dow, Norris F. & Hickman, William A.
System:
The UNT Digital Library
Effects of Partial Admission on Performance of a Gas Turbine
Report presenting an investigation of the effect of partial admission of the driving fluid on the performance of a representative full-admission, production-type gas turbine. Results regarding losses, full-admission performance, partial-admission performance, partial admission as a means of power control, and a comparison of partial admission with other methods of power control are provided.
Date:
February 1949
Creator:
Kohl, Robert C.; Herzig, Howard Z. & Whitney, Warren J.
System:
The UNT Digital Library
Method for Evaluating From Shadow or Schlieren Photographs the Pressure Drag in Two-Dimensional or Axially Symmetrical Flow Phenomena With Detached Shock
"A method has been developed for evaluating from shadow or schileren photographs the pressure drag of axially symmetrical bodies at zero angle of attack or of two-dimensional bodies producing detached shock. The method consists in the determination of the flow properties along a characteristic line and the application of the momentum theorem to a stream tube around the body. The method can be applied to the determination of external drag of supersonic inlets with subsonic flow at the entrance of the inlet" (p. 1).
Date:
February 1949
Creator:
Ferri, Antonio
System:
The UNT Digital Library
Comparison between predicted and observed performance of gas-turbine stator blade designed for free-vortex flow
Report presenting a comparison between the calculated design performance of a gas-turbine stator blade and its performance in a sector of an annular cascade tunnel. The gas velocities on the blade surface were computed by the stress filament method and compared with experimental values, with which they agreed satisfactorily. Results regarding discharge angle, vane-surface-velocity distribution, tangential- and axial-velocity distribution, and radial-equilibrium consideration are provided.
Date:
April 1949
Creator:
Huppert, M. C. & MacGregor, Charles
System:
The UNT Digital Library
The application of airfoil studies to helicopter rotor design
From Summary: "In order to facilitate the application of miscellaneous airfoil data to the problems of the helicopter designer, a discussion of a number of the problems most frequently arising is presented. A reference list of published papers on airfoil section characteristics (or their application) which experience has shown to be useful in connection with these helicopter problems is included."
Date:
February 1949
Creator:
Gustafson, F. B.
System:
The UNT Digital Library
A study of flow changes associated with airfoil section drag rise at supercritical speeds
Report presenting a study of experimental pressure distributions and section characteristics for several moderately thick airfoil sections were made. The pressure distributions and section force characteristics of several moderately thick airfoil sections at Mach numbers above the drag-divergence Mach numbers were analyzed.
Date:
February 1949
Creator:
Nitzberg, Gerald E. & Crandall, Stewart
System:
The UNT Digital Library
Effects of Several Design Variables on Turbine-Wheel Weight
Report presenting an analysis showing the effect of several design variables on turbine-wheel flight. Equations are developed for the calculations of weights of the disk, the rim, and the blades, and use the following variables: the blading aspect ratio and solidity, the ratio of the centrifugal stress at the blade roots to that in the disk, and the ratio of wheel diameter at the blade root to wheel diameter at the blade tip.
Date:
February 1949
Creator:
LaValle, Vincent L. & Huppert, Merle C.
System:
The UNT Digital Library
On Compressibility Corrections for Subsonic Flow Over Bodies of Revolution
"A study of the subsonic flow past an infinitely long corrugated circular cylinder is presented to show the relation between two-dimensional and axisymmetrical flow. In fact, a solution is obtained which contains as limiting cases both the Prandtl-Glauert correction for two-dimensional flow and the Göthert correction for flow past slender bodies of revolution. Included in the paper are velocity-correction formulas for a cylinder with a single bump and for a corrugated cylinder in the presence of walls" (p. 1).
Date:
February 1949
Creator:
Reissner, Eric
System:
The UNT Digital Library
Triangular wings cambered and twisted to support specified distributions of lift at supersonic speeds
Report presenting an application of the linearized supersonic flow theory to the calculation of the camber and twist required for various lift distributions on a triangular wing with leading edges behind the Mach cone. Several specific examples are used and plots of the cambered surfaces, corresponding lift distributions, and values of the theoretical drag coefficients are presented.
Date:
February 1949
Creator:
Baldwin, Barrett S., Jr.
System:
The UNT Digital Library
Plastic buckling of simply supported compressed plates
Report presenting an investigation to ascertain the validity of various theories for the plastic buckling of compressed simply supported plates by means of local-instability tests of drawn square tubes of 14S-T6 aluminum alloy. The results obtained were in excellent agreement with Stowell's unified theory for the plastic buckling of columns and plates.
Date:
April 1949
Creator:
Pride, Richard A. & Heimerl, George J.
System:
The UNT Digital Library
Effect of Automatic Stabilization on the Lateral Oscillatory Stability of a Hypothetical Airplane at Supersonic Speeds
Note presenting an investigation to determine the effect of automatic stabilization on the lateral oscillatory stability of a hypothetical supersonic airplane. The investigation included an autopilot sensitive to either the yawing or rolling angular velocity. The results of the investigation indicated that all the automatic pilots improved the stability of the original unstable short-period oscillation.
Date:
March 1949
Creator:
Sternfield, Leonard
System:
The UNT Digital Library
Notes on the Foundations of the Theory of Small Displacements of Orthotropic Shells
Note presenting a survey that has been made of the various systems of equations which have been given in the literature for the analysis of small deflections of thin elastic shell. A new system of equations has been derived for the analysis of shells, which includes the effects of transverse shear and normal stresses.
Date:
March 1949
Creator:
Hildebrand, F. B.; Reissner, E. & Thomas, G. B.
System:
The UNT Digital Library
Flutter of a uniform wing with an arbitrarily placed mass according to a differential-equation analysis and a comparison with experiment
Report presenting a method for the calculation of flutter speed of a uniform wing carrying an arbitrarily placed concentrated mass. The method involves the solution of the differential equations of motion of the wing at flutter speed and does not require the assumption of specific normal modes of vibration.
Date:
March 1949
Creator:
Runyan, Harry L. & Watkins, Charles E.
System:
The UNT Digital Library
The influence of blade-width distribution on propeller characteristics
Report presenting combined force and wake survey tests on three-blade model propellers in order to determine the effects of blade-width distribution on constant-speed efficiency characteristics. The most important result is the demonstration that blade-width distribution has a marked influence on the constant-speed efficiency characteristics of propellers.
Date:
March 1949
Creator:
Reid, Elliott G.
System:
The UNT Digital Library
Investigation at low speeds of the effect of aspect ratio and sweep on rolling stability derivatives of untapered wings
Report presenting a wind-tunnel investigation conducted in rolling flow to determine the effects of aspect ratio and sweep on the rolling stability derivatives for a series of untapered wings. The results indicated that when the aspect ratio is held constant, an increase in sweepback angle causes a significant reduction in the damping in roll at low lift coefficients for only the higher aspect ratios tested.
Date:
March 1949
Creator:
Goodman, Alex & Fisher, Lewis R.
System:
The UNT Digital Library
Critical shear stress of infinitely long, simply supported plate with transverse stiffeners
From Summary: "A theoretical solution is given for the critical shear stress of an infinitely long, simply supported, flat plate with identical, equally spaced, transverse stiffeners of zero torsional stiffness. Results are obtained by means of the Lagrangian multiplier method and are presented in the form of design charts. Experimental results are included and are found to be in good agreement with the theoretical results."
Date:
April 1949
Creator:
Stein, Manuel & Fralich, Robert W.
System:
The UNT Digital Library
Reinforced Circular Cutouts in Plane Sheets
Note presenting an attempt to design the reinforcement of a cutout in a plane sheet in such a way that it is as nearly as possible equivalent to the part of the structure which has been cut out. A perfect equivalence would mean that the stresses and displacements of the structure remain the same as those which would have appeared without the cutout.
Date:
April 1949
Creator:
Reissner, H. & Morduchow, M.
System:
The UNT Digital Library
Effect of Increase in Afterbody Length on the Hydrodynamic Qualities of a Flying-Boat Hull of High Length-Beam Ratio
Report presenting an investigation to determine the effects of increased afterbody length on the hydrodynamic qualities of a model of a flying boat with a hull with a length-beam ratio of 15. Results regarding longitudinal stability, spray characteristics, excess thrust for take-off, landings in waves, and a summary chart are provided.
Date:
April 1949
Creator:
Kapryan, Walter J. & Clement, Eugene P.
System:
The UNT Digital Library
The Response of Pressure Measuring Systems to Oscillating Pressures
Note presenting a method for calculating the response and lag in pressure measuring systems subjected to steady-state sinusoidally varying pressures. The pressure system is assumed to consist of an inlet restriction, tubing length, and connected instrument volume. Results of the phase-shift determination are provided.
Date:
February 1949
Creator:
Taback, Israel
System:
The UNT Digital Library
Strength analysis of stiffened thick beam webs
Report presenting a method for the strength analysis of stiffened beam webs as applied to beams with ratios of applied shear to buckling shear less than 2.5. Results regarding critical shear stress, forced crippling failure in uprights, and web failures are provided.
Date:
March 1949
Creator:
Levin, L. Ross & Sandlin, Charles W., Jr.
System:
The UNT Digital Library