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Partner
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Technical Report Archive and Image Library
1,250
National Advisory Committee for Aeronautics Collection
775
Office of Scientific & Technical Information Technical Reports
326
TRAIL Microcard Collection
263
Texas State Publications
6
Harris and Eliza Kempner
4
John J. Herrera Papers
2
Texas Cultures Online
2
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2
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1
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NACA Research Memorandums
440
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236
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227
United States Geological Survey Reports
93
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59
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57
Hanford Works Reports
49
HW (Series)
47
Trace elements investigations report
42
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41
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Degree Level
States
Ditching Investigation of a 1/24-Scale Model of the Douglas C-124 Airplane
"An investigation of a 1/24- scale dynamically similar model of the Douglas C-124 airplane was made to determine the ditching characteristics and proper technique for ditching the airplane. Various conditions of damage, landing attitude, flap setting, and speed were investigated. The behavior of the model was determined from visual observations, motion- picture records, and time-history deceleration records. The results of the investigation are presented in table form, photographs, and curves" (p. 1).
Date:
June 18, 1951
Creator:
Fisher, Lloyd J. & Windham, John O.
System:
The UNT Digital Library
Yawed-Landing Investigation of a Model of the Convair Y2-2 Airplane, TED No. NACA DE 363
"A model of the Convair Y2-2 airplane was tested in Langley tank no. 2 to determine whether satisfactory stability in yawed landings was possible with a certain ventral fin. Free-body landings were made in smooth and rough water at two speeds and two rates of descent with the model yawed 15 degrees. The behavior of the model was determined by visual observations and from motion-picture records" (p. 1).
Date:
August 23, 1951
Creator:
Hoffman, Edward L. & Fisher, Lloyd J.
System:
The UNT Digital Library
Tank Investigation of the EDO Model 142 Hydro-Ski Research Airplane
A tank investigation has been conducted of a 1/10-size powered-dynamic model of the Edo model 142 hydra-ski research airplane. The results of tests of two configurations are presented: One included a large ski and a ski well; the other, a small ski without a well. Water take-offs would be possible with the available thrust for either configuration: however, the configuration with the large ski emerged sooner and had less resistance from ski emergence until take-off. Longitudinal stability and landing behavior in smooth water were satisfactory for both configurations. Some alteration to the design of the tail would be desirable in order to reduce the spray loads.
Date:
September 24, 1951
Creator:
Ramsen, John A.; Wadlin, Kenneth L. & Gray, George R.
System:
The UNT Digital Library
Preliminary Investigation of Helmholtz Resonators for Damping Pressure Fluctuations in 3.6-Inch Ram Jet at Mach Number 1.90
Memorandum presenting an investigation conducted at Mach number 1.90 to determine if Helmholtz resonators can be used in a typical ramjet configuration to damp pressure pulsations associated with shock oscillations. Only one of the two resonators was found to effectively damp pressure pulsations that occurred when the ram jet was operating in the vicinity of its peak pressure recovery. Neither was found to effectively damp pressure pulsations over the entire range of ramjet operating conditions.
Date:
May 22, 1951
Creator:
Fox, Jerome L.
System:
The UNT Digital Library
Preliminary Investigation of Use of Conical Flow Separation for Efficient Supersonic Diffusion
Use of flow separation on a rod projecting upstream of a blunt body to decelerate the supersonic stream ahead of an annular nose inlet was investigated at Mach numbers of 1.76, 1.93, and 2.10. Maximum pressure recoveries were obtained with rod tip projections about 1.5 times the radius of the spherical nose and were higher than those obtained with single-shock solid cones. Subcritical operation was similar to that observed with solid-cone inlets, but the effect of angle of attack on maximum pressure recovery was more severe.
Date:
December 17, 1951
Creator:
Moeckel, W. E. & Evans, P. J., Jr.
System:
The UNT Digital Library
Liquid-fuel-distribution and fuel-state effects on combustion performance of a single tubular combustor
Report presenting an investigation to study the effects of liquid-fuel distribution on combustion performance of a single turbojet-engine combustor operating with liquid MIL-F 5624 fuel. Results regarding altitude limits and combustion efficiencies, liquid-fuel distribution, fuel state, and miscellaneous observations are provided.
Date:
May 1, 1951
Creator:
McCafferty, Richard J.
System:
The UNT Digital Library
Concerning the Flow About Ring-Shaped Cowlings Part 6: Further Measurements on Inlet Devices
"The present report presents as a supplement to the fourth report (available as ATI 5045, Air Materiel Command) in the series of investigations concerning the flow about ring-shaped cowlings further wind-tunnel measurements on inlet devices which are to show the influence of the radius of the nose of the cowling on the flow conditions. Moreover, a simple rule for the design of such arrangements, containing a hub in the interior, is suggested" (p. 1).
Date:
December 1951
Creator:
Küchemann, Dietrich & Weber, Johanna
System:
The UNT Digital Library
Concerning the Flow About Ring-Shaped Cowlings Part 2: Annular Bodies of Infinite Length With Circulation for Smooth Entrance
The investigations carried out in a previous report (NACA TM 1325) concerning the flow about ring-shaped cowlings were extended by taking a circulation about the cowling into consideration. The present second report treats bodies of infinite length with approximately smooth entrance. The circulation was caused by distributing vortex rings of constant density over a stream surface extending to infinity. Furthermore, the influence of a hub body on such cowlings was dealt with.
Date:
November 1951
Creator:
Küchemann, Dietrich & Weber, Johanna
System:
The UNT Digital Library
Influence of Static Longitudinal Stability on the Behavior of Airplanes in Gusts
The equations of motion for an airplane penetrating a gust are derived using a few simplifying assumptions. Calculations of loads for different static longitudinal stability on two German airplane models, HC 45 and HS 122, are compared with flight tests. Good agreement is obtained between the trend of the flight tests and the calculated values; however no absolute comparison was possible between the flight tests and calculations.
Date:
November 1951
Creator:
Hoene, H.
System:
The UNT Digital Library
Theory of Thin-Walled Rods
Starting with the Love equations for bending of extensible shells, "principal stress states" are sought for a thin-walled rod of arbitrary but open cross section. Principal stress states exclude those local states arising from end conditions which damp out with distance from the ends. It is found that for rods of intermediate length, long enough to avoid local bending at a support, and short enough that elementary torsion and bending are not the most significant stress states, four principal states exist.
Date:
October 1951
Creator:
Goldenveizer, A. L.
System:
The UNT Digital Library
Relations Between the Modulus of Elasticity of Binary Alloys and Their Structure
A comprehensive survey of the elastic modulus of binary alloys as a function of the concentration is presented. Alloys that form continuous solid solutions, limited solid solutions, eutectic alloys, and alloys with intermetallic phases are investigated. Systems having the most important structures have been examined to obtain criteria for the relation between lattice structure, type of binding, and elastic behavior.
Date:
November 1951
Creator:
Köster, Werner & Rauscher, Walter
System:
The UNT Digital Library
Investigations on Wings With and Without Sweepback at High Subsonic Speeds
Drag tests at zero lift have been made at Mach numbers from 0.7 to approximately 0.95 in the high speed wind tunnel of the Institute of Aerodynamics, ETH, Zurich, on a group of untapered wings of aspect ratio 3.25, having sweep angles of 0 degree and 35 degrees. For each sweep angle, a series of geometrically similar models was tested at a constant Reynolds number to provide a verification of computed tunnel blocking corrections. Tests were also made for wings having thickness ratios of 0.09 and 0.12 and the results compared with results predicted by von Karman's similarity law.
Date:
November 1951
Creator:
Ackeret, Jakob; Degen, Max & Rott, Nikolaus
System:
The UNT Digital Library
Resistance of a Plate in Parallel Flow at Low Reynolds Numbers
The present paper gives the results of measurements of the resistance of a plate placed parallel to the flow in the range of Reynolds numbers from 10 to 2300; in this range the resistance deviates from the formula of Blasius. The lower limit of validity of the Blasius formula is determined and also the increase in resistance at the edges parallel to the flow in the case of a plate of finite width.
Date:
November 1951
Creator:
Janour, Zbynek
System:
The UNT Digital Library
Deplacement Effect of the Laminar Boundary Layer and the Pressure Drag
The displacement effect of the boundary layer on the outer frictionless flow is discussed for both steady and unsteady flows. The analysis is restricted to cases in which the potential flow pressure distribution remains valid for the boundary-layer calculation. Formulas are given for the dependence of the pressure drag, friction drag, and total drag of circular cylinders on the time from the start of motion for cases in which the velocity varies as a power of the time. Formulas for the locations and for the time for the appearance of the separation point are given for two dimensional bodies of arbitrary shape.
Date:
October 1951
Creator:
Görtler, H.
System:
The UNT Digital Library
On the Turbulent Friction Layer for Rising Pressure
Among the information presented are included displacement, momentum, and kinetic energy thicknesses, shearing stress distributions across boundary layer, and surface friction coefficients. The Gruschwitz method and its modifications are examined and tested. An energy theorem for the turbulent boundary layer is introduced and discussed but does not lead to a method for the prediction of the behavior of the turbulent boundary layer because relations for the shearing stress and the surface friction are lacking.
Date:
October 1951
Creator:
Wieghardt, K. & Tillmann, W.
System:
The UNT Digital Library
On the recording of turbulent longitudinal and transverse fluctuations
"A thorough understanding of the turbulent flow movements cannot be arrived at from investigations of the temporal mean values of the flows alone. Study of the fluctuation phenomena themselves is indispensable. Thus turbulence research entered a new promising stage when investigators started performing fluctuation measurements and basing theories on those measurements" (p. 1).
Date:
August 1951
Creator:
Reichardt, H.
System:
The UNT Digital Library
Calculation of the Bending Stresses in Helicopter Rotor Blades
A comparatively rapid method is presented for determining theoretically the bending stresses of helicopter rotor blades in forward flight. The method is based on the analysis of the properties of a vibrating beam, and its uniqueness lies in the simple solution of the differential equation which governs the motion of the bent blades.
Date:
March 1951
Creator:
de Guillenchmidt, P.
System:
The UNT Digital Library
An Investigation of the Aerodynamic Characteristics in Pitch of an XB-52 Airplane Model in a High-Speed Wind Tunnel
"A wind-tunnel investigation of a 0.049-scale model of the Boeing XB-52 airplane was made at Mach numbers from 0.30 to 0.925 and at corresponding Reynolds numbers from about 2.3 x 10(exp 6) to 4.3 x 10(exp 6). The results of the investigation indicate satisfactory static longitudinal stability throughout the test Mach-number range and some loss in tail effectiveness beginning at about 0.80 Mach number. A comparison of the results of these tests with those of the same model in the Boeing Airplane Company's wind tunnel showed close agreement of lift- and drag-divergence Mach numbers. Slight differences were observed in tail effectiveness and the position of the stick-fixed neutral point."
Date:
March 16, 1951
Creator:
Cleary, Joseph W. & Coe, Charles F.
System:
The UNT Digital Library
Effect of Angle of Incidence of Second-Stage Vane Assembly on Third-Stage Compressor-Blade Vibration and Engine Performance
"Strain-gages were used to measure blade vibrations causing failures in the third stage of a production 11-stage axial-flow compressor. After the serious third-stage vibration was detected, a series of investigations were conducted with second-stage vane assemblies of varying angles of incidence. Curves presented herein show the effect of varying the angle of incidence of second-stage vane assembly on third-stage rotor-blade vibration amplitude and engine performance" (p. 1).
Date:
June 12, 1951
Creator:
Meyer, André J., Jr. & Calvert, Howard F.
System:
The UNT Digital Library
Altitude Performance of J35-A-17 Turbojet Engine in an Altitude Chamber
"An investigation of the altitude performance characteristics of an Allison J35-A-17 turbojet engines have been conducted in an altitude chamber at the NACA Lewis laboratory. Engine performance was obtained over a range of altitudes from 20,000 to 60,000 feet at a flight Mach number of 0.62 and a range of flight Mach numbers from 0.42 to 1.22 at an altitude of 30,000 feet. The performance of the engine over the range investigated could be generalized up to an altitude of 30,000 feet" (p. 1).
Date:
January 3, 1951
Creator:
Vincent, K. R. & Gale, B. M.
System:
The UNT Digital Library
Arrangement of Bodies of Revolution in Supersonic Flow to Reduce Wave Drag
"The wave drag of a combination of slender bodies of revolution at zero angle of attack is studied with a view to determining the arrangements for which the total drag is a minimum. Linearized theory is used to calculate the pressure distribution in the field surrounding the bodies. The interference drag coefficient is computed for different arrangements" (p. 1).
Date:
December 17, 1951
Creator:
Friedman, Morris D.
System:
The UNT Digital Library
Investigation of Surge Characteristics of XJ34-WE-32 Turbojet Engine
Surge characteristics of the XJ34-WE-32 turbojet engine were determined over a range of altitudes. Several typical oscillograph traces during which surge occurred are presented. The effect of altitude on the surge line and it's relation to the steady-state operating region are shown.
Date:
October 2, 1951
Creator:
Groesbeck, Donald E. & Peters, Daniel J.
System:
The UNT Digital Library
Matching Characteristics of J35-A-23 Compressor and Two-stage Turbine
Component data on the J35-A-23 compressor and two-stage turbine were used to determine the problems in matching the two units for operation in a turbojet engine. Possible operating regions were determined and an equilibrium operating line was also determined for the assumed conditions of zero flight speed and a jet nozzle area approximately 5.5 percent greater than the wide-open nozzle area.
Date:
August 6, 1951
Creator:
Dugan, James F., Jr.; Rebeske, John J., Jr. & Finger, Harold B.
System:
The UNT Digital Library
Buckling of thin-walled cylinder under axial compression and internal pressure
An investigation was made of a thin-walled cylinder under axial compression and various internal pressures to study the effect of the internal pressure on the compressive buckling stress of the cylinder. A theoretical analysis based on a large-deflection theory was also made. The theoretically predicted increase of compressive buckling stress due to internal pressure agrees fairly well with the experimental results. (author).
Date:
1951
Creator:
Lo, Hsu; Crate, Harold & Schwartz, Edward B.
System:
The UNT Digital Library