National Advisory Committee for Aeronautics (NACA) - 11 Matching Results

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An approximate analytical method for studying entry into planetary atmospheres

Description: Report presenting a single, ordinary, nonlinear differential equation of second order that can be used for determining entry into an exponential planetary atmosphere. The reduced equation includes various terms, some of which represent the gravity force, the centrifugal acceleration, and the lift force. A number of solutions for lifting and nonlifting vehicles entering at various initial angles are obtained from the complete nonlinear equation.
Date: May 1958
Creator: Chapman, Dean R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Droplet Impingement and Ingestion by Supersonic Nose Inlet in Subsonic Tunnel Conditions

Description: "The amount of water in cloud droplet form ingested by a full-scale supersonic nose inlet with conical centerbody was measured in the NACA Lewis icing tunnel. Local and total water impingement rates on the cowl and centerbody surfaces were also obtained. All measurements were made with a dye-tracer technique" (p. 1).
Date: May 1958
Creator: Gelder, Thomas F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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An experimental investigation of wake effects on hydro-skis

Description: Report presenting an experimental investigation to determine the effects of planing in a wake on the forces of a planing surface and to locate desirable positions in the wake with regard to the lift and lift-drag ratio of the planing surface. Two combinations of hydro-skis were tested: one with two in tandem and one with three arranged with one hydro-ski in the front and two in the back. Results indicated that the rear hydro-ski in tandem arrangement could have large increases in lift coefficie… more
Date: May 1958
Creator: McBride, Ellis E. & Fisher, Lloyd J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Flight Investigation of Effects of Retreating-Blade Stall on Bending and Torsional Moments Encountered by a Helicopter Rotor Blade

Description: Note presenting flight tests conducted with a medium-size single-rotor helicopter, one blade of which was equipped with strain gages, to determine the effects of retreating-blade stall on the rotor blade bending and torsional moments during high-speed flight and pull-up maneuvers. The results indicate that retreating-blade stall has a substantial effect on the periodic rotor blade moments. Results regarding the effect of stall in steady forward flight and effect of stall in pull-up maneuvers ar… more
Date: May 1958
Creator: Ludi, LeRoy H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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General solutions for flow past slender cambered wings with swept trailing edges and calculation of additional loading due to control surfaces

Description: Report presenting the use of the slender-wing-type analysis to obtain general expressions for the surface pressure, lift, and rolling moment for cambered wings with swept trailing edges. The results are specialized to give the additional loading due to the deflection of trailing-edge control surfaces and the loading due to a particular type of wing twist. A numerical example for aileron control is included.
Date: May 1958
Creator: Klunker, E. B. & Harder, Keith C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Measurement of the Effect of an Axial Magnetic Field on the Reynolds Number of Transition in Mercury Flowing Through a Glass Tube

Description: Note presenting experiments conducted to determine the effect of a strong axial magnetic field on the flow of mercury through a circular channel. The magnetic induction was 15,000 gauss, and the channel was a pyrex tube 17-1/4 inches long and 0.027 inch inside diameter. The results indicated that the stabilizing effect occurred only at Reynolds number above 5,000, so that the region of practical applicability seems to be at fairly high Reynolds numbers and when there are only slight disturbance… more
Date: May 1958
Creator: Bader, Michel & Carlson, William C. A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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A performance analysis of methods for handling excess inlet flow at supersonic speeds

Description: Report presenting a comparison of several methods for handling excess inlet flow for the Mach number range from 1.5 to 4.0. The following techniques were examined and evaluated: normal- and oblique-shock spillage, bypassing through an auxiliary exit, bypassing to an ejector exhaust nozzle, and bypassing the excess flow through an auxiliary ramjet engine. Charts are presented for the thrust penalties at a variety of Mach numbers.
Date: May 1958
Creator: Hearth, Donald P. & Connors, James F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Preliminary Survey of Propulsion Using Chemical Energy Stored in the Upper Atmosphere

Description: Ram-jet cycles that use the chemical energy of dissociated oxygen for propulsion in the ionosphere are presented. After a review of the properties and compositions of the upper atmosphere, the external drag, recombination kinetics, and aerodynamic-heating problems of an orbiting ram jet are analyzed. The study indicates that the recombination ram jet might be useful for sustaining a satellite at an altitude of about 60 miles. Atmospheric composition and recombination-rate coefficients were too … more
Date: May 1958
Creator: Baldwin, Lionel V. & Blackshear, Perry L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Some Measurements of Aerodynamic Forces and Moments at Subsonic Speeds on a Rectangular Wing of Aspect Ratio 2 Oscillating About the Midchord

Description: Report presenting some measurements of the aerodynamic forces and moments on a rectangular wing of aspect ratio 2 which oscillated about the midchord. The measurements were made at four frequencies over a range of Mach and Reynolds numbers. Results regarding the calculated values of various theories and coefficients of lift and moment are provided.
Date: May 1958
Creator: Widmayer, Edward, Jr.; Clevenson, Sherman A. & Leadbetter, Sumner A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Study of ground-reaction forces measured during landing impacts of a large airplane

Description: Report presenting the results of tests conducted on a large bomber-type airplane to determine the ground-reaction forces imposed on the main landing gear under actual landing conditions. The vertical force on the landing gear truck at which the oleopneumatic shock strut began to compress varied over a wide range. Results regarding vertical forces, drag forces, and side forces are provided.
Date: May 1958
Creator: Hall, Albert W.; Sawyer, Richard H. & McKay, James M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Summary of experimental heat-transfer measurements in turbulent flow for a Mach number range from 0.87 to 5.05

Description: Report presenting heat-transfer measurements made in turbulent flow at a variety of Mach and Reynolds numbers through the use of an axially symmetric annular nozzle consisting of an inner shaped center body and an outer cylindrical sleeve. The results are presented as Stanton number and recovery factor as a function of Reynolds number. Stanton number was found to decrease with an increase in Reynolds number and usually decreases with an increase in Mach number.
Date: May 1958
Creator: Brevoort, Maurice J. & Arabian, Barbara D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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