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Influence of Boric Oxide Deposition on Turbojet-Engine Operation

Description: Memorandum presenting a study of the effect of oxide-depositing fuels on engine starting, operation, and performance by using a modified production turbojet engine operated using a trimethyl borate azeotrope as a fuel. Results regarding boric oxide deposition, engine operation and performance, effect of turbine-inlet temperature, and dissipation of boric oxide deposits are provided.
Date: February 15, 1957
Creator: Useller, James W.; Burley, Richard R. & Velie, Wallace W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Spin-Tunnel Investigation of a Model of a 60 Degree Delta-Wing Airplane to Determine the Spin, Recovery, and Longitudinal Trim Characteristics Throughout an Extensive Range of Mass Loadings

Description: Report presenting an investigation to determine the spin, recovery, and longitudinal-trim characteristics of a 60 degree delta-wing model through an extensive range of mass loadings. Variations in the relative density, center-of-gravity position, and inertia parameters were included in testing. Results regarding the single-vertical-tail and multiple-vertical-tail configurations are provided.
Date: February 15, 1950
Creator: Klinar, Walter J. & Jones, Ira P., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Calculation of Aerodynamic Forces on a Propeller in Pitch or Yaw

Description: Report presenting an analysis to determine the applicability of existing propeller theory and the theory of oscillating airfoils to the problem of determining the magnitude of the forces on propellers in pitch or yaw. The steady-state method for calculating propeller forces appears to give satisfactory results.
Date: February 15, 1949
Creator: Crigler, John L. & Gilman, Jean, Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Wind-Tunnel Investigation of the Effects of Various Asymmetric Canopy Modifications on the Behavior of Descending Parachutes

Description: Report presenting an investigation in the free-spinning tunnel to study the behavior in descent of hemispherical and quasi-conical parachutes, some with symmetrical canopy modifications and all with a right circular cylinder suspended by one end below the parachute. Results indicated that a lateral flight component during descent could be obtained by using a circular cutout in the side of the canopy of a hemispherical parachute and a large slit between two panels of a quasi-conical parachute.
Date: February 15, 1952
Creator: Scher, Stanley H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

On the Kernel function of the integral equation relating lift and downwash distributions of oscillating wings in supersonic flow

Description: 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 f… more
Date: February 15, 1955
Creator: Watkins, Charles E. & Berman, Julian H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Tabulated Pressure Coefficient Data from a Tail Loads Investigation on a 1/15-Scale Model of the Goodyear XZP5K Airship

Description: This paper contains tail and hull loads data obtained in an investigation of a l/15-scale model of the Goodyear XZP5K airship. Data are presented in the form of tabulated pressure coefficients over a pitch and yaw range of +/-20 deg and 0 deg to 30 deg respectively, with various rudder and elevator deflections. Two tail configurations of different plan forms were tested on the model. The investigation was conducted in the Langley full-scale tunnel at a Reynolds number of approximately 16.5 x 10… more
Date: February 15, 1956
Creator: Cannon, Michael D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effect of Various Blade Modifications on Performance of a 16-Stage Axial-Flow Compressor 3 - Effect on Over-All Performance Characteristics on Increasing Stator-Blade Angles in Inlet Stages

Description: The stator-blade angles in the first four stages of a 16-stage axial-flow compressor were increased in order to decrease the angles of attack of these stages, and thereby to improve part-speed performance. The performance of this modified compressor was compared with that of the same compressor with original blade angles.
Date: February 15, 1952
Creator: Medeiros, Arthur A. & Hatch, James E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Some effects of side-wall modifications on the drag and pressure recovery of an NACA submerged inlet at transonic speeds

Description: Report presenting comparative drag and pressure recovery for an NACA submerged inlet and two side-wall modifications. One afterbody and diffuser were used for all tests and testing was conducted over a range of Mach numbers. The two modified inlets were found to be superior to the standard inlet from the standpoint of pressure recovery.
Date: February 15, 1952
Creator: Taylor, Robert A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Lift, drag, and pitching moment of low-aspect-ratio wings at subsonic and supersonic speeds: An investigation at large Reynolds numbers of the low-speed characteristics of several wing-body combinations

Description: Report presenting an investigation of several wing-body combinations with wings suitable for supersonic interceptor-type aircraft at high Reynolds numbers and low Mach numbers. Nine wing-body combinations were tested with three different wing aspect ratios and three different plan forms. Results regarding the lift, drag, and pitching moment are provided.
Date: February 15, 1952
Creator: Smith, Donald W.; Shibata, Harry H. & Selan, Ralph
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Static longitudinal and lateral stability data from an exploratory investigation at Mach number 4.06 of an airplane configuration having a wing of trapezoidal plan form

Description: Report presenting an investigation to determine the static longitudinal and lateral stability characteristics of an airplane configuration with a trapezoidal wing with modified hexagonal airfoil section and a cruciform tail with 5 degree semiangle wedge section. Data were obtained at a range of angles of attack and sideslip.
Date: February 15, 1955
Creator: Dunning, Robert W. & Ulmann, Edward F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Investigation of the Lateral Stability Characteristics of the Douglas X-3 Configuration at Mach Numbers From 0.6 to 1.1 by Means of a Rocket-Propelled Model

Description: Report presenting an investigation of a rocket-propelled model of the Douglas X-3 airplane in order to determine the lateral stability characteristics at zero angle of attack and to evaluate test and analysis technique. Results regarding time histories, lateral trim characteristics, general characteristics of lateral oscillation, and lateral stability derivatives are provided.
Date: February 15, 1955
Creator: Mitchell, Jesse L. & Peck, Robert F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Influence of boric oxide deposition on turbojet-engine operation

Description: Report presenting testing of a modified production turbojet engine using a trimethyl borate azeotrope as a fuel. Operation with this fuel for 100 minutes produced a 2-percent deterioration in engine speed and only a 1-percent increase in combustor total-pressure loss with the best engine configuration investigated. Results regarding boric oxide deposition, engine operation and performance, effect of turbine-inlet temperature, and dissipation of boric oxide deposits are provided.
Date: February 15, 1957
Creator: Useller, James W.; Burley, Richard R. & Velie, Wallace W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Experimental investigation of dynamic relations in a 48-inch ram-jet engine

Description: Engine dynamics were investigated for supercritical operation of the ram jet at Mach 2.75 over a range of simulated altitudes from 68,000 to 82,000 feet. Indicial-and frequency-response tests were conducted with fuel flow as the input variable. For a wide range of operating points, the response of static or total pressure to fuel flow consisted of a dead time followed by a response form that generally approximated a linear, first-order, lead-lag. The dead time varied significantly only with dis… more
Date: February 15, 1957
Creator: Hurrell, Herbert G.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Thermal Decomposition of Some Group I, II, and III Metal Alkyls

Description: Memorandum presenting a mechanism for the thermal decomposition of sodium, lithium, beryllium, magnesium, aluminum, and boron alkyls and for the reverse reaction, the addition of olefins to metal hydrides. The reactions are shown to be nonradical and to probably proceed through a cyclic intermediate.
Date: February 15, 1957
Creator: Rosenblum, Louis
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Relative loading on biplane wings

Description: Recent improvements in stress analysis methods have made it necessary to revise and to extend the loading curves to cover all conditions of flight. This report is concerned with a study of existing biplane data by combining the experimental and theoretical data to derive a series of curves from which the lift curves of the individual wings of a biplane may be obtained.
Date: February 15, 1933
Creator: Diehl, Walter S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Theoretical lift and damping in roll at supersonic speeds of thin sweptback tapered wings with streamwise tips, subsonic leading edges, and supersonic trailing edges

Description: "On the basis of linearized supersonic-flow theory, generalized equations were derived and calculations made for the lift and damping in roll of a limited series of thin sweptback tapered wings. Results are applicable to wings with streamwise tips and for a range of supersonic speeds for which the wing is wholly contained between the Mach cones springing from the wing apex and from the trailing edge of the root section. A further limitation is that the tip Mach lines may not intersect on the wi… more
Date: February 15, 1949
Creator: Malvestuto, Frank S., Jr.; Margolis, Kenneth & Ribner, Herbert S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Design Modifications to the SRE during FY 1960

Description: Abstract: The means to prevent the recurrence of tetralin leakage into the SRE sodium systems are discussed. Included is a description of the redesign of system components to utilize alternate coolants such as nitrogen, air, and NaK.
Date: February 15, 1961
Creator: Deegan, G. E.; Dermer, M. D.; Flanagan, J. S.; Gower, G. C.; Hall, R. J.; Hinze, R. B. et al.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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