Resource Type
Serial/Series Title
Atomic Energy Commission Reports
242
NACA Research Memorandums
189
AEC research and development report
79
Hanford Works Reports
65
North American Aviation Reports
56
HW (Series)
52
NACA Technical Reports
41
General Electric Company Atomic Power Reports
38
BNL (Series)
35
Brookhaven National Laboratory Reports
35
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719 Matching Results
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Cooperative Investigation of Relationship Between Static and Fatigue Properties of Wrought N-155 Alloy at Elevated Temperatures
Report presents the correlation of extensive data obtained relating properties of wrought N-155 alloy under static, combined static and dynamic, and complete reversed dynamic stress conditions. Time period for fracture ranged from 50 to 500 hours at room temperature, 1,000 degrees, 1,200 degrees, and 1,500 degrees F.
Date:
June 15, 1953
Creator:
NACA Subcommittee on Power-Plant Materials
Object Type:
Report
System:
The UNT Digital Library
Similar Solutions for the Compressible Laminar Boundary Layer with Heat Transfer and Pressure Gradient
"Stewartson's transformation is applied to the laminar compressible boundary-layer equations and the requirement of similarity is introduced, resulting in a set of ordinary nonlinear differential equations previously quoted by Stewartson, but unsolved. The requirements of the system are Prandtl number of 1.0, linear viscosity-temperature relation across the boundary layer, an isothermal surface, and the particular distributions of free-stream velocity consistent with similar solutions. This system admits axial pressure gradients of arbitrary magnitude, heat flux normal to the surface, and arbitrary Mach numbers" (p. 1).
Date:
October 15, 1954
Creator:
Cohen, Clarence B. & Reshotko, Eli
Object Type:
Report
System:
The UNT Digital Library
On the Kernel function of the integral equation relating lift and downwash distributions of oscillating wings in supersonic flow
From Summary: "This report treats the Kernel function of the integral equation that relates a known or prescribed downwash distribution to an unknown lift distribution for harmonically oscillating wings in supersonic flow. The treatment is essentially an extension to supersonic flow of the treatment given in NACA report 1234 for subsonic flow. For the supersonic case the Kernel function is derived by use of a suitable form of acoustic doublet potential which employs a cutoff or Heaviside unit function. The Kernel functions are reduced to forms that can be accurately evaluated by considering the functions in two parts: a part in which the singularities are isolated and analytically expressed, and a nonsingular part which can be tabulated."
Date:
February 15, 1955
Creator:
Watkins, Charles E. & Berman, Julian H.
Object Type:
Report
System:
The UNT Digital Library
The Flow of a Compressible Fluid Past a Circular Arc Profile
"The Ackeret iteration process is utilized to obtain higher approximations than that of Prandtl and Glauert for the flow of a compressible fluid past a circular arc profile. The procedure is to expand the velocity potential in a power series of the camber coefficient. The first two terms of the development correspond to the Prandtl-Glauert approximation and yield the well-known correction to the circulation about the profile" (p. 385).
Date:
July 15, 1944
Creator:
Kaplan, Carl
Object Type:
Report
System:
The UNT Digital Library
Method of Matching Performance of Compressor Systems with that of Aircraft Power Sections
"A method is developed of easily determining the performance of a compressor system relative to that of the power section for a given altitude. Because compressors, reciprocating engines, and turbines are essentially flow devices, the performance of each of these power-plant components is presented in terms of similar dimensionless ratios. The pressure and temperature changes resulting from restrictions of the charge-air flow and from heat transfer in the ducts connecting the components of the power plant are also expressed by the same dimensionless ratios and the losses are included in the performance of the compressor" (p. 119).
Date:
November 15, 1945
Creator:
Bullock, Robert O.; Keetch, Robert C. & Moses, Jason J.
Object Type:
Report
System:
The UNT Digital Library
Effects of Small Angles of Sweep and Moderate Amounts of Dihedral on Stalling and Lateral Characteristics of a Wing-Fuselage Combination Equipped With Partial- and Full-Span Double Slotted Flaps
"Tests of a wing-fuselage combinations incorporating NACA 65-series airfoil sections were conducted in the NACA 19-foot pressure tunnel. The investigation included the tests with flaps neutral and with partial- and full-span double slotted flaps deflected to determine the effects of (1) variations of wing sweep between -4 degrees and 8 degrees on stalling and lateral stability and control characteristics and (2) variations of dihedral between 0 degree and 6.75 degrees on lateral stability characteristics" (p. 467).
Date:
April 15, 1944
Creator:
Teplitz, Jerome
Object Type:
Report
System:
The UNT Digital Library
Application of Theodorsen's theory to propeller design
A theoretical analysis is presented for obtaining, by use of Theodorsen's propeller theory, the load distribution along a propeller radius to give the optimum propeller efficiency for any design condition. The efficiencies realized by designing for the optimum load distribution are given in graphs, and the optimum efficiency for any design condition may be read directly from the graph without any laborious calculations. Examples are included to illustrate the method of obtaining the optimum load distributions for both single-rotating and dual-rotating propellers.
Date:
March 15, 1948
Creator:
Crigler, John L.
Object Type:
Report
System:
The UNT Digital Library
Analysis of variation of piston temperature with piston dimensions and undercrown cooling
From Summary: "A theoretical analysis is presented that permits estimation of the changes in piston-temperature distribution induced by variations in the crown thickness, the ring-groove-pad thickness, and the undercrown surface heat-transfer coefficient. The analysis consists of the calculation of operating temperatures at various points in the piston body on the basis of the experimentally determined surface heat-transfer coefficients and boundary-region temperatures, as well as arbitrarily selected surface coefficients."
Date:
January 15, 1948
Creator:
Sanders, J. C. & Schramm, W. B.
Object Type:
Report
System:
The UNT Digital Library
Consideration of Dynamic Loads on the Vertical Tail by the Theory of Flat Yawing Maneuvers
"Dynamic yawing effects on vertical-tail loads are considered by a theory of flat yawing maneuvers. A comparison is shown between computed loads and the loads measured in flight on a fighter airplane. The dynamic effects were investigated on a large flying boat for both an abrupt rudder deflection and sinusoidal rudder deflection" (p. 91).
Date:
March 15, 1946
Creator:
Boshar, John & Davis, Philip
Object Type:
Report
System:
The UNT Digital Library
NACA investigation of fuel performance in piston-type engines
This report is a compilation of many of the pertinent research data acquired by the National Advisory Committee for Aeronautics on fuel performance in piston engines. The original data for this compilation are contained in many separate NACA reports which have in the present report been assembled in logical chapters that summarize the main conclusions of the various investigations. Complete details of each investigation are not included in this summary; however, such details may be found, in the original reports cited at the end of each chapter.
Date:
May 15, 1951
Creator:
Barnett, Henry C.
Object Type:
Report
System:
The UNT Digital Library
Some Features of Artificially Thickened Fully Developed Turbulent Boundary Layers with Zero Pressure Gradient
Report gives an account of an investigation conducted to determine the feasibility of artificially thickening a turbulent boundary layer on a flat plate. A description is given of several methods used to thicken artificially the boundary layer. It is shown that it is possible to do substantial thickening and obtain a fully developed turbulent boundary layer, which is free from any distortions introduced by the thickening process, and, as such, is a suitable medium for fundamental research.
Date:
September 15, 1950
Creator:
Klebanoff, P. S. & Diehl, Z. W.
Object Type:
Report
System:
The UNT Digital Library
Hydrocarbon and nonhydrocarbon derivatives of cyclopropane
The methods used to prepare and purify 19 hydrocarbon derivatives of cyclopropane are discussed. Of these hydrocarbons, 13 were synthesized for the first time. In addition to the hydrocarbons, six cyclopropylcarbinols, five alkyl cyclopropyl ketones, three cyclopropyl chlorides, and one cyclopropanedicarboxylate were prepared as synthesis intermediates. The melting points, boiling points, refractive indices, densities, and, in some instances, heats of combustion of both the hydrocarbon and nonhydrocarbon derivatives of cyclopropane were determined. These data and the infrared spectrum of each of the 34 cyclopropane compounds are presented in this report. The infrared absorption bands characteristic of the cyclopropyl ring are discussed, and some observations are made on the contribution of the cyclopropyl ring to the molecular refractions of cyclopropane compounds.
Date:
August 15, 1952
Creator:
Slabey, Vernon A.; Wise, Paul H. & Gibbons, Louis C.
Object Type:
Report
System:
The UNT Digital Library
Matrix method of determining the longitudinal-stability coefficients and frequency response of an aircraft from transient flight data
From Summary: "A matrix method is presented for determining the longitudinal-stability coefficients and frequency response of an aircraft from arbitrary maneuvers. The method is devised so that it can be applied to time-history measurements of combinations of such simple quantities as angle of attack, pitching velocity, load factor, elevator angle, and hinge moment to obtain the over-all coefficients. Although the method has been devised primarily for the evaluation of stability coefficients which are of primary interest in most aircraft loads and stability studies, it can be used also, with a simple additional computation, to determine the frequency-response characteristics. The entire procedure can be applied or extended to other problems which can be expressed by linear differential equations."
Date:
December 15, 1950
Creator:
Donegan, James J. & Pearson, Henry A.
Object Type:
Report
System:
The UNT Digital Library
Formulas for the Supersonic Loading, Lift, and Drag of Flat Swept-Back Wings With Leading Edges Behind the Mach Line
"The method of superposition of linearized conical flows has been applied to the calculation of the aerodynamic properties, in supersonic flight, of thin flat, swept-back wings at an angle of attack. The wings are assumed to have rectilinear plan forms, with tips parallel to the stream, and to taper in the conventional sense. The investigation covers the moderately supersonic speed range where the Mach lines from the leading-edge apex lie ahead of the wing" (p. 1147).
Date:
March 15, 1950
Creator:
Cohen, Doris
Object Type:
Report
System:
The UNT Digital Library
A low-speed experimental investigation of the effect of a sandpaper type of roughness on boundary-layer transition
From Summary: "An investigation was made in the Langley low-turbulence pressure tunnel to determine the effect of size and location of a sandpaper type of roughness on the Reynolds number for transition. Transition was observed by means of a hot-wire anemometer located at various chordwise stations for each position of the roughness. These observations indicated that when the roughness is sufficiently submerged in the boundary layer to provide a substantially linear variation of boundary-layer velocity with distance from the surface up to the top of the roughness, turbulent "spots" begin to appear immediately behind the roughness when the Reynolds number based on the velocity at the top of the roughness height exceeds a value of approximately 600. At Reynolds numbers even slightly below the critical value (value for transition), the sandpaper type of roughness introduced no measurable disturbances into the laminar layer downstream of the roughness. The extent of the roughness area does not appear to have an important effect on the critical value of the roughness Reynolds number."
Date:
August 15, 1956
Creator:
von Doenhoff, Albert E. & Horton, Elmer A.
Object Type:
Report
System:
The UNT Digital Library
A method for simulating the atmospheric entry of long-range ballistic missiles
From Summary: "It is demonstrated with the aid of similitude arguments that a model launched from a hypervelocity gun upstream through a special supersonic nozzle should experience aerodynamic heating and resulting thermal stresses like those encountered by a long-range ballistic missile entering the earth's atmosphere. This demonstration hinges on the requirements that model and missile be geometrically similar and made of the same material, and that they have the same flight speed and Reynolds number (based on conditions just outside the boundary layer) at corresponding points in their trajectories. The hypervelocity gun provides the model with the required initial speed, while the nozzle scales the atmosphere, in terms of density variation, to provide the model with speeds and Reynolds numbers over its entire trajectory."
Date:
September 15, 1955
Creator:
Eggers, A. J., Jr.
Object Type:
Report
System:
The UNT Digital Library
Performance and Boundary-Layer Data From 12 Degree and 23 Degree Conical Diffusers of Area Ratio 2.0 at Mach Numbers Up to Choking and Reynolds Numbers Up to 7.5 X 10(6)
"For each of two inlet-boundary-layer thicknesses, performance and boundary-layer characteristics have been determined for a 12 degree, 10-inch-inlet-diameter diffuser, a 12 degree, 21-inch-inlet-diameter diffuser, and a 23 degree, 21-inch-inlet-diameter diffuser. The investigation covered an inlet Mach number range from about 0.10 to coking. The corresponding inlet Reynolds number, based on inlet diameter, varied from about 0.5 x 10(6) to 7.5 x 10(6)" (p. 1013).
Date:
November 15, 1954
Creator:
Little, B. H., Jr. & Wilbur, Stafford W.
Object Type:
Report
System:
The UNT Digital Library
Summary report on the induction of water to the inlet air as a means of internal cooling in aircraft-engine cylinders
Report presenting investigations of a full-scale air-cooled aircraft-engine cylinder of 202-cubic-inch displacement to determine the effects of internal cooling by water induction on the maximum permissible power and output of an internal-combustion engine. Results regarding the maximum permissible engine performance, engine temperatures, and constant inlet-air pressure investigations are provided.
Date:
August 15, 1942
Creator:
Rothrock, Addison M. & Jones, Anthony W.
Object Type:
Report
System:
The UNT Digital Library
Langley full-scale-tunnel investigation of the factors affecting the static lateral-stability characteristics of a typical fighter-type airplane
"The factors that affect the rate of change of rolling moment with yaw of a typical fighter-type airplane were investigated in the Langley full-scale tunnel on a typical fighter-type airplane. Eight representative flight conditions were investigated in detail. The separate effects of propeller operation, of the wing-fuselage combination, and of the vertical tail to the effective dihedral of the airplane in each condition were determined. The results of the tests showed that for the airplane with the propeller removed, the wing-fuselage combination had positive dihedral effect which increased considerably with increasing angle of attack for all conditions" (p. 1).
Date:
April 15, 1947
Creator:
Lange, Roy H.
Object Type:
Report
System:
The UNT Digital Library
Full-Scale-Wind-Tunnel Tests of a 35 Degree Sweptback Wing Airplane With High-Velocity Blowing Over the Training-Edge Flaps
"A wind-tunnel investigation was made to determine the effects of ejecting high-velocity air near the leading edge of plain trailing-edge flaps on a 35 degree sweptback wing. The tests were made with flap deflections from 45 degrees to 85 degrees and with pressure ratios across the flap nozzles from sub-critical up to 2.9. A limited study of the effects of nozzle location and configuration on the efficiency of the flap was made. Measurements of the lift, drag, and pitching moment were made for Reynolds numbers from 5.8 to 10.1x10(6)" (p. 1).
Date:
November 15, 1955
Creator:
Kelly, Mark W. & Tolhurst, William H., Jr.
Object Type:
Report
System:
The UNT Digital Library
Aerodynamic Loads on an External Store Adjacent to a 45 Degree Sweptback Wing at Mach Numbers From 0.70 to 1.96, Including an Evaluation of Techniques Used
"Aerodynamic forces and moments have been obtained in the Langley 9- by 12-inch blowdown tunnel on an external store and on a 45 degree swept-back wing-body combination measured separately at Mach numbers from 0.70 to 1.96. The wing was cantilevered and had an aspect ratio of 4.0; the store was independently sting-mounted and had a Douglas Aircraft Co. (DAC) store shape. The angle of attack range was from -3 degrees to 12 degrees and the Reynolds number (based on wing mean aerodynamic chord) varied from 1.2 x10(6) to 1.7 x 10(6)" (p. 1).
Date:
November 15, 1955
Creator:
Guy, Lawrence D. & Hadaway, William M.
Object Type:
Report
System:
The UNT Digital Library
Flight Characteristics of a 1/4-Scale Model of the XFV-1 Airplane (TED No. NACA DE-378)
From Summary: "A 1/4-scale dynamically similar model of the XFV-1 airplane has been flown in the Ames 40- by 80-foot wind tunnel, using the trailing flight-cable technique. This investigation was devoted to establishing the flight characteristics of the model in forward flight from hovering to wing stall, and in yawed flight (wing span alined with the relative wind) from hovering to the maximum speed at which controlled flight could be maintained. Landings, take-offs, and hovering characteristics in flights close to the ground were also investigated."
Date:
October 15, 1952
Creator:
Kelly, Mark W. & Smaus, Louis H.
Object Type:
Report
System:
The UNT Digital Library
Wind-Tunnel Investigation of the Low-Speed Characteristics of a 1/8-Scale Model of the Republic XP-91 Airplane with a Vee and a Conventional Tail
"Low-speed wind-tunnel tests of a l/8 scale model of the Republic XP-91 airplane were made to determine its low-speed characteristics and the relative merits of a vee and a conventional tail on the model. The results of the tests showed that for the same amount of longitudinal and directional stability the conventional tail gave less roll due to sideslip than did the vee tail. The directional stability of the model was considered inadequate for both the vee and conventional tails; however, increasing the area and aspect ratio of the conventional vertical tail provided adequate directional stability" (p. 1).
Date:
December 15, 1947
Creator:
Weiberg, James A. & Anderson, Warren E.
Object Type:
Report
System:
The UNT Digital Library
Effect on Drag of Longitudinal Positioning of Half-Submerged and Pylon-Mounted Douglas Aircraft Stores on a Fuselage with and without Cavities between Mach Numbers 0.9 and 1.8
From Summary: "The effect on drag of positioning symmetrically mounted Douglas Aircraft Company, Inc. stores in pairs on a parabolic fuselage of fineness ratio 10.0 has been determined by flight tests of rocket-propelled, zero-lift models through a range of Mach number from 0.9 to 1.8. The stores were mounted in half-submerged positions and on pylons and were tested in three longitudinal locations on the fuselage with the forward position being located at the maximum diameter of the fuselage. The effects on drag of removing the half-submerged stores or extending them outward on pylons also was investigated by tests of models with half-submerged-store cavities on the fuselage. Two pylons differing in airfoil section and thickness were tested at the forward position of the stores on the fuselage with cavities."
Date:
July 15, 1954
Creator:
Hoffman, Sherwood & Wolff, Austin L.
Object Type:
Report
System:
The UNT Digital Library