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Examination of Recent Lateral-Stability-Derivative Data
"In the present paper attention is directed to the aerodynamic parameters, the so-called stability derivatives, that affect the lateral behavior of airplanes and missiles. The discussion is centered on three important quantities, the effective-dihedral derivative, the directional-stability derivative, and the damping-in-roll derivative. These quantities are considered for a large angle-of-attack range at subsonic speeds" (p. 1).
Date:
October 22, 1953
Creator:
Malvestuto, Frank S., Jr. & Kuhn, Richard E.
Object Type:
Report
System:
The UNT Digital Library
Experimental data concerning the effect of high heat-input rates on the pressure drop through radiator tubes
From Summary: "The pressure drops through electrically heated Inconel tubes with length-diameter ratios of 29.25, 58.50, 87.75, and 117.00 have been measured at entrance Mach numbers from approximately 0.12 to the value at which choking occurred. The heat-input rate was varied from zero to the highest values allowable without damaging the tubes. Experimental data and a number of computed variables are presented in tabular form."
Date:
September 22, 1948
Creator:
Habel, Louis W. & Gallagher, James J.
Object Type:
Report
System:
The UNT Digital Library
Experimental Effects of Propulsive Jets and Afterbody Configurations on the Zero-Lift Drag of Bodies of Revolution at a Mach Number of 1.59
The present investigation was made at a free-stream Mach number of 1.59 to compare the afterbody drags to a series of conical boattailed models at zero angle of attack. Afterbody drags were obtained for both the power-off and the power-on conditions. Power-on drags were obtained as a function of afterbody fineness ratio, jet pressure ratio and divergence, and jet Mach number.
Date:
April 22, 1954
Creator:
de Moraes, Carlos A. & Nowitzky, Albin M.
Object Type:
Report
System:
The UNT Digital Library
Experimental influence coefficients for the deflection of the wing of a full-scale, swept-wing bomber
Report presenting the results of deflection tests on the wing of a full-scale, swept-wing jet bomber in the form of structural influence coefficients relating the deflection of a system of points on the wing and concentrated loads applied on the wing spars. The procedures for determining the coefficients are included.
Date:
April 22, 1954
Creator:
Mayo, Alton P. & Ward, John F.
Object Type:
Report
System:
The UNT Digital Library
Experimental investigation at supersonic speeds of twin-scoop duct inlets of equal area 3: inlet enclosing 37.2 percent of the maximum circumference of the forebody
Report presenting testing of a twin-scoop duct inlet that enclosed 37.2 percent of the forebody circumference at Mach numbers between 1.36 and 2.01. The approach to each scoop consisted of a ramp that deflected the flow to create an oblique shock wave in front of the duct entrance. Results regarding the inlet proportions, ramp angle, slots, and angle of incidence are provided.
Date:
July 22, 1948
Creator:
Davis, Wallace F. & Edwards, Sherman S.
Object Type:
Report
System:
The UNT Digital Library
Experimental investigation of performance of single-stage transonic compressor with guide vanes turning counter to direction of rotor whirl
Report presenting testing of a transonic compressor rotor with double-circular-arc blade sections and inlet guide vanes turning counter to the direction of rotor whirl to determine the effect of blade-row interaction on the performance of a transonic rotor. Results regarding overall performance, guide-vane performance, rotor-inlet conditions, rotor-outlet conditions, consideration of radial equilibrium, blade-element performance, and axial asymmetry in rotor-outlet flow are provided.
Date:
April 22, 1957
Creator:
Jahnsen, Lawrence J. & Fessler, Theodore E.
Object Type:
Report
System:
The UNT Digital Library
Extended operation of turbojet engine with pentaborane
A full-scale turbojet engine was operated with pentaborane fuel continuously for 22 minutes at conditions simulating flight at a Mach number of 0.8 at an altitude of 50,000 feet. This period of operation is approximately three times longer than previously reported operation times. Although the specific fuel consumption was reduced from 1.3 with JP-4 fuel to 0.98 with pentaborane, a 13.2-percent reduction in net thrust was also encountered. A portion of this thrust loss is potentially recoverable with proper design of the engine components. The boron oxide deposition and erosion processes within the engine approached an equilibrium condition after approximately 22 minutes of operation with pentaborane.
Date:
May 22, 1957
Creator:
Useller, James W. & Jones, William L.
Object Type:
Report
System:
The UNT Digital Library
Extrusion Cladding of Fuel Element
From introduction: "This investigation was undertaken with the general objective of determining whether uranium core could be sheathed with aluminum by an extrusion-cladding process. The ultimate objective of this work was to determine the feasibility of extrusion cladding flat plates of uranium."
Date:
March 22, 1955
Creator:
Slunder, C. J.; Fiorentino, R. J. & Hall, A. M.
Object Type:
Report
System:
The UNT Digital Library
Extrusion Cladding of Uranium Fuel Plates
The following report describes two methods of extrusion cladding of uranium fuel plates that were investigated and evaluated.
Date:
August 22, 1958
Creator:
Fiorentino, Robert J.; Drennen, David C.; Slunder, Charles J. & Hall, A. M.
Object Type:
Report
System:
The UNT Digital Library
Fabrication Techniques and Heat-Transfer Results for Cast-Cored Air-Cooled Turbine Blades
Memorandum presenting an investigation to devise an air-cooled turbine blade which eliminated the difficulties encountered with brazing in air-cooled-blade fabrication. Techniques were developed for casting air-cooled blades with a large number of relatively small cooling passages near the airfoil surface; two such blades of HS-21 material were operated in a turbojet engine modified for air cooling. Results regarding the heat-transfer characteristics, stress and durability results, and evaluation of cast-cored-blade potential are provided.
Date:
June 22, 1956
Creator:
Freche, John C. & Oldrieve, Robert E.
Object Type:
Report
System:
The UNT Digital Library
A Fast Coincidence Circuit with Pulse Height Selection
Abstract: The output signal of a linear accelerator may have a rise time of 1-2 x 10[minus]7 seconds. Therefore, the output of a pulse height selector operating on this signal has a variation of delay from the original signal of about this amount. In the instrument to be described in this technical report this difficulty is largely resolved.
Date:
April 22, 1947
Creator:
Bell, P. B.; DeBenedetti, Sergio & Francis, J. B., Jr.
Object Type:
Report
System:
The UNT Digital Library
Flight and Preflight Evaluation of an Automatic Thrust-Coefficient Control System in a Twin-Engine Ram-Jet Missile
Report presenting a flight and preflight evaluation of an automatic thrust-coefficient control system in a twin-engine ram-jet missile. A flicker-type single-loop servocontrol system is shown to be a usable way of controlling ram-jet thrust coefficients.
Date:
January 22, 1954
Creator:
Dettwyler, H. Rudolph & Trout, Otto F., Jr.
Object Type:
Report
System:
The UNT Digital Library
Flight Determination of Drag of Normal-Shock Nose Inlets With Various Cowling Profiles at Mach Numbers From 0.9 to 1.5
Report discussing free-flight tests of normal-shock nose-inlet models with 1-series, parabolic, and conic cowling profiles in order to investigate the external drag characteristics at an angle of attack of 0 degrees. The testing occurred at a variety of Mach numbers, mass-flow ratios, and Reynolds numbers. Information about the effect of afterbody length, basic data, and effect of cowl shape is provided.
Date:
October 22, 1953
Creator:
Sears, R. I.; Merlet, C. F. & Putland, L. W.
Object Type:
Report
System:
The UNT Digital Library
A flight investigation of area-suction and blowing boundary-layer control on the trailing-edge flaps of a 35 degree swept-wing-carrier-type airplane
Report presenting flight tests on an FJ-3 airplane to determine the flight characteristics of a carrier-type airplane with area-suction and blowing boundary-layer control on the trailing-edge flaps. Measurements were made of lift, drag, and bleed-air requirements for the different types of boundary-layer control systems. Results regarding lift, drag, flow requirements, performance, pilots' opinions, and approach-speed criteria are provided.
Date:
April 22, 1957
Creator:
Quigley, Hervey C.; Hom, Francis W. K. & Innis, Robert C.
Object Type:
Report
System:
The UNT Digital Library
Flight investigation of pentaborane fuel in 9.75-inch-diameter ram-jet engine with downstream fuel injection
Report presenting a flight test of pentaborane fuel in an air-launched ramjet engine with a design free-stream Mach number of 1.8. The ramjet used in the investigation had a revised spray bar-flameholder configuration. Results regarding propulsive thrust and propulsive-thrust specific fuel consumption are provided.
Date:
April 22, 1957
Creator:
Disher, John H. & Jones, Merle L.
Object Type:
Report
System:
The UNT Digital Library
Flight Investigation of Pentaborane Fuel in 9.75-inch-diameter Ram-jet Engine With Downstream Fuel Injection
Flight investigation of pentaborane fuel in 9.75- inch-diameter ramjet engine with downstream fuel injection.
Date:
April 22, 1957
Creator:
Disher, John H. & Jones, Merle L.
Object Type:
Report
System:
The UNT Digital Library
Flight investigation of the effect of control centering springs on the apparent spiral stability of a personal-owner airplane
Report presents the results of a flight investigation conducted on a typical high-wing personal-owner airplane to determine the effect of control centering springs on apparent spiral stability. Apparent spiral stability is the term used to describe the spiraling tendencies of an airplane in uncontrolled flight as affected both by the true spiral stability of the perfectly trimmed airplane and by out-of-trim control settings. Centering springs were used in both the aileron and rudder control systems to provide both a positive centering action and a means of trimming the airplane.
Date:
March 22, 1951
Creator:
Campbell, John P.; Hunter, Paul A.; Hewes, Donald E. & Whitten, James B.
Object Type:
Report
System:
The UNT Digital Library
Flight tests of an automatic interceptor system with a tracking radar modified to minimize the interaction between antenna and interceptor motions
Report presenting a flight-test program investigating a modification to an interceptor system. Results indicate that a significant improvement in the overall response characteristics of the system. The modification minimizes the interaction between the antenna and interceptor motions, which can have a serious influence on flight path stability during a lead-collision attack.
Date:
May 22, 1957
Creator:
Triplett, William C. & Hom, Francis W. K.
Object Type:
Report
System:
The UNT Digital Library
Flight tests of the drag and torque of the propeller in terminal-velocity dives
From Summary: "The drag and torque of a controllable propeller at various blade-angle settings, and under various diving conditions, were measured by indirect method on F6C-4 airplane in flight. The object of these tests were (1) to provide data on which calculations of the terminal velocity with a throttled engine and the accompanying engine speed could be based and (2) to determine the possibility of utilizing the propeller as an air brake to reduce the terminal velocity. The data obtained were used in the establishment of propeller charts, on the basis of which the terminal velocity and engine speed could be calculated for airplanes whose characteristics fall within the range of these tests."
Date:
August 22, 1933
Creator:
Rhode, Richard V. & Pearson, Henry A.
Object Type:
Report
System:
The UNT Digital Library
Free-flight measurements of the zero-lift drag of several wings at Mach numbers from 1.4 to 3.8
Report presenting the zero-lift drag of several wings obtained at supersonic Mach numbers in free flight with rocket-propelled models. The wings tested all had the same exposed area, mounted on the same basic body configuration, and had one of four different types of wings.
Date:
June 22, 1956
Creator:
Jackson, H. Herbert
Object Type:
Report
System:
The UNT Digital Library
Free-flight performance of 16-inch-diameter supersonic ram-jet units 1: four units designed for combustion-chamber-inlet Mach number of 0.12 at free-stream Mach number of 1.6 (units A-2, A-3, A-4, and A-5)
Report presenting free-flight investigations conducted on four 16-inch-diameter ramjet units to determine the performance at high subsonic and supersonic velocities. Data for evaluating the performance were obtained from radio-telemetering and radar-tracking equipment. Results regarding combustion performance, diffuser total-pressure recovery, thrust coefficient, and external drag coefficient are provided.
Date:
September 22, 1949
Creator:
Carlton, William W. & Messing, Wesley E.
Object Type:
Report
System:
The UNT Digital Library
Full-Scale Investigation of Several Jet-Engine Noise-Reduction Nozzles
"A number of noise-suppression nozzles were tested on full-scale engines. In general, these nozzles achieved noise reduction by the mixing interference of adjacent jets, that is, by using multiple-slot-nozzles. Several of the nozzles achieved reductions in sound power of approximately 5 decibels (nearly 70 percent) with small thrust losses (approx. 1 percent). The maximum sound-pressure level was reduced by as much as 18 decibels in particular frequency bands" (p. 1249).
Date:
January 22, 1957
Creator:
Coles, Willard D. & Callaghan, Edmund E.
Object Type:
Report
System:
The UNT Digital Library
Fundamental Equations Describing Neutron Behavior in a Cavity
This report provides fundamental equations and maps to calculate neutron behavior in a spherical cavity.
Date:
May 22, 1951
Creator:
Willmer, D. B. & Imhoff, D. H.
Object Type:
Report
System:
The UNT Digital Library
Gas-turbine-engine performance when heat from liquid-cooled turbines is rejected ahead of, within, or behind main compressor
Report discussing methods, advantages, and disadvantages of locating rotating heat exchangers ahead of, within, and behind the main engine compressor. Heat rejection should occur at the compressor discharge for best engine performance. Results regarding turbojet-engine performance, turboprop-engine performance, and a comparison of engine performance with liquid- and air-cooling are provided.
Date:
May 22, 1956
Creator:
Esgar, Jack B. & Slone, Henry O.
Object Type:
Report
System:
The UNT Digital Library