National Advisory Committee for Aeronautics (NACA) - 190 Matching Results

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Tables of Coefficients for the Analysis of Stresses About Cutouts in Circular Semimonocoque Cylinders with Flexible Rings

Description: Note presenting tables of coefficients which facilitate the stress analysis of circular semimonocoque cylinders with cutouts by the method published in a previous report. When the values of two simple structural parameters are known, use of the coefficients enables shear flows and stringer loads in the neighborhood of a cutout to be calculated.
Date: July 1955
Creator: McComb, Harvey G., Jr. & Low, Emmet F., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Techniques for calculating parameters of nonlinear dynamic systems from response data

Description: Report present a study of the problem of determining nonlinear parameters of dynamic systems, such as aircraft or servomechanisms, whose measured responses are nonlinear. Nonconstant coefficients can be determine satisfactorily for first- or second-order systems using one or a combination of the techniques developed. The methods can be divided into three categories: the equations-of-motion methods, the response curve-fitting methods, and the phase-plane methods.
Date: July 1953
Creator: Briggs, Benjamin R. & Jones, Arthur L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Temperature distribution in internally heated walls of heat exchangers with noncircular flow passages using coolants with very low Prandtl number

Description: Report presenting a prediction of the magnitude of temperature variation in order to detect the places of highest temperature and to determine the operating temperatures admissible for the material of which the heat exchanger is composed. Results regarding the temperature distribution in triangular passages, temperature distribution in rectangular passages, influence of velocity field on temperature field, and a comparison of Prandtl number 1 solution are provided.
Date: July 1951
Creator: Eckert, E. R. G. & Low, George M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Temperatures, thermal stress, and shock in heat-generating plates of constant conductivity and of conductivity that varies linearly with temperature

Description: Report presenting working formulas for the steady-state temperatures and thermal stress in heat-generating infinite plates of constant conductivity. Of all planes in the plate, the plate surfaces are always under the greatest tension, and the midplane is under the greatest compression.
Date: July 1953
Creator: Manson, S. V.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Tensile properties of 7075-T6 and 2024-T3 aluminum-alloy sheet heated at uniform temperature rates under constant load

Description: Results are presented of tests to determine the effect of heating at uniform temperature rates from 0.2 degrees to 100 degrees F per second on the tensile properties of 7075-T6 d(75s-T6) and 2024-T3 (24s-T3) aluminum-alloy sheet under constant-load conditions. Yield and rupture stresses, obtained under rapid-heating conditions, are compared with results of elevated-temperature stress-strain tests for 1/2-hour exposure. Master yield-and-rupture-stress curves based on linear temperature-rate para… more
Date: July 1955
Creator: Heimerl, George J. & Inge, John E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Tensile properties of Inconel and RS-120 titanium-alloy sheet under rapid-heating and constant-temperature conditions

Description: From Summary: "Results are presented of rapid-heating tests to determine the tensile strength of Inconel and RS-120 titanium-alloy sheet heated to failure at uniform temperature rates from 0.2 degrees Fahrenheit to 100 degrees Fahrenheit per second under constant load conditions. Yield and rupture stresses, obtained by rapid heating, are compared with yield and ultimate stresses from elevated-temperature tensile stress-strain tests for 1/2-hour exposure. The applicability of master curves and t… more
Date: July 1956
Creator: Heimerl, George J.; Kurg, Ivo M. & Inge, John E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Theoretical calculations of the lateral force and yawing moment due to rolling at supersonic speeds for sweptback tapered wings with streamwise tipssupersonic leading edges

Description: Report presenting theoretical results for the lateral force and yawing moment due to combined angle of attack and roll. The thin wings are tapered and have leading and trailing edges which are each swept at a constant angle; the tips are parallel to the center section.
Date: July 1950
Creator: Harmon, Sidney M. & Martin, John C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The theoretical characteristics of triangular-tip control surfaces at supersonic speeds: Mach lines behind trailing edges

Description: Report presenting generalized expressions in closed form obtained for the characteristics due to control-surface deflection and wing angle of attack for wing plan forms with triangular-tip control surfaces at supersonic speeds. Charts are presented for the deflection characteristics for configurations having the sweep of the wing and control-surface trailing edges equal and for the location of the hinge line for balanced controls.
Date: July 1952
Creator: Kainer, Julian H. & King, Mary Dowd
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Theoretical Investigation at Subsonic Speeds of the Flow Ahead of a Slender Inclined Parabolic-Arc Body of Revolution and Correlation With Experimental Data Obtained at Low Speeds

Description: Report presenting charts which permit the rapid estimation of deviations from free-stream values of static pressure, angle of attack, and angle of sideslip so that ideal positions for orifices and vanes for measuring these qualities can be selected. The effects of thickness and angle of attack are considered in greater detail.
Date: July 1954
Creator: Letko, William & Danforth, Edward C. B., III
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Theoretical investigation of longitudinal response characteristics of a swept-wing fighter airplane having a normal acceleration control system and a comparison with other types of systems

Description: Report presenting an investigation of the longitudinal response characteristics of a swept-wing fighter airplane using normal-acceleration control system. Results regarding the frequency and transient responses, acceleration systems, pitching-velocity command system, and the pitch-attitude system are provided.
Date: July 1954
Creator: Stokes, Fred H. & Mathews, Charles W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Theoretical pressure distribution and wave drags for conical boattails

Description: "Afterbody pressure distributions and wave drag were calculated using a second-order theory for a variety of conical boattails at zero angle of attack. Results are presented for Mach numbers from 1.5 to 4.5, area ratios from 0.200 to 0.800, and boattail angle from 3 degrees to 11 degrees. The results indicate that for a given boattail angle, the wave drag decreases with increasing Mach number and area ratio" (p. 1).
Date: July 1953
Creator: Jack, John R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Theoretical study of some methods for increasing the smoothness of flight through rough air

Description: Report presenting a theoretical study of the response to gusts and stability and control characteristics of an airplane equipped with systems in which wing flaps and elevators are operated to reduce accelerations in rough air. The surfaces are actuated by an automatic control system in response to indications of an angle-of-attack vane or accelerometer.
Date: July 1951
Creator: Phillips, William H. & Kraft, Christopher C., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Three-dimensional transonic flow theory applied to slender wings and bodies

Description: Report presenting the derivation of the integral equations for transonic flow around slender wings and bodies of revolution, with special attention paid to conditions resulting from the presence of shock waves and to the reduction of the relations to the special forms necessary for the discussion of sonic flow.
Date: July 1956
Creator: Heaslet, Max A. & Spreiter, John R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Turbulent-Heat-Transfer Measurements at a Mach Number of 3.90

Description: 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 3.90. 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: July 1956
Creator: Brevoort, Maurice J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Unstable Convection in Vertical Channels With Heating From Below, Including Effects of Heat Sources and Frictional Heating

Description: Note presenting an analysis of the effects of heat sources and frictional heating on the laminar fully developed channel flow subject to a body force between two parallel plates oriented in the direction of the body force. Solutions are obtained for combined forced- and natural-convection flows for the cases in which the wall temperature variations are linear and the wall temperatures are specified, the walls are both insulated, and the net mass flow in the channel is zero. Results regarding th… more
Date: July 1955
Creator: Ostrach, Simon
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Vaporization rates and heat-transfer coefficients for pure liquid drops

Description: Report presenting an investigation to determine the vaporization rates of pure liquid drops vaporizing under conditions similar to those encountered in aircraft combustion systems using a heat-balance equation. Results regarding the analysis and experimental results are provided.
Date: July 1951
Creator: Ingebo, Robert D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Variation of Local Liquid-Water Concentration About and Ellipsoid of Fineness Ratio 5 Moving in a Droplet Field

Description: From Summary: "Trajectories of water droplets about an ellipsoid of revolution with a fineness ratio of 5 (which often approximates the shape of an aircraft fuselage or missile) were computed with the aid of a differential analyzer. Analyses of these trajectories indicate that the local concentration of liquid water at various points about an ellipsoid in flight through a droplet field varies considerably and under some conditions may be several times the free-stream concentration."
Date: July 1954
Creator: Dorsch, Robert G. & Brun, Rinaldo J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Vibration survey of four representative types of air-cooled turbine blades

Description: Report presenting an investigation conducted in a turbojet engine mounted in a sea-level test stand to determine the vibrational characteristics of four representative types of air-cooled turbine blades.Two were standard-span blades and two were long-span blades for high mass-flow turbines. Results regarding the coolant-flow rate, vibratory stresses, vibrational characteristics, and failures are provided.
Date: July 1958
Creator: Calvert, Howard F. & Smith, Gordon T.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind-tunnel investigation at low speeds of flight characteristics of a sweptback-wing jet-transport airplane model equipped with an external-flow jet-augmented slotted flap

Description: Report presenting a wind-tunnel investigation at low speeds to determine the flight characteristics of a model of a sweptback-wing jet-transport airplane equipped with an external-flow jet-augmented slotted flap. Results regarding the longitudinal stability characteristics, longitudinal control characteristics, lateral stability characteristics, and lateral control characteristics are provided.
Date: July 1958
Creator: Johnson, Joseph L., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind-tunnel investigation of effects of spoiler location, spoiler size, and fuselage nose shape on directional characteristics of a model of a tandem-rotor helicopter fuselage

Description: Report presenting a low-speed investigation made in the stability tunnel to study the effect of spoiler location, spoiler size, and fuselage nose shape on the directional stability characteristics of a model of a tandem-rotor helicopter fuselage. The model was found to be directionally unstable at certain positive angles of attack.
Date: July 1958
Creator: Williams, James L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind-tunnel investigation of the high-subsonic static longitudinal stability characteristics of several wing-body configurations designed for high lift-drag ratios at a Mach number of 1.4

Description: Report presenting testing in the high-speed 7- by 10-foot tunnel to investigate the high-subsonic static longitudinal stability characteristics and lift-drag ratios of several wing-body models designed to provide high lift-drag ratios at Mach number 1.4. The basic configuration had a thin highly swept wing of aspect ratio 2.91 with NACA 65-A series airfoil sections. Results regarding longitudinal stability, lift, drag, and lift-drag ratio are provided.
Date: July 1958
Creator: Fournier, Paul G.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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