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Investigation of Ejection Releases of an MB-1 Rocket From a 0.04956-Scaled Model of the Convair F-106A Airplane at Mach Number 1.59 : Coord. No. AF-AM-57
Memorandum presenting an investigation in the 27- by 27-inch preflight jet of the ejection release characteristics of the MB-1 rocket from the missile bay of a 0.04956-scaled model of the Convair F-106A. The MB-1 rocket was ejected with its fin tips retracted, for a simulated altitude of 18,670 feet at a Mach number of 1.59.
Date:
May 20, 1957
Creator:
Lee, John B.
System:
The UNT Digital Library
Investigation of translating-double-cone axisymmetric inlets with cowl projected areas 40 and 20 percent of maximum at Mach numbers from 3.0 to 2.0
Report presenting the performance of two translating-double-cone inlets with contrasting rates of turning on the spike shoulder and corresponding cowl projected frontal areas of 40 and 20 percent of maximum compared over a range of Mach numbers. Results regarding internal-flow performance, external-flow performance, inlet airflow patterns, and propulsive-thrust comparison are provided.
Date:
May 20, 1957
Creator:
Connors, James F.; Wise, George A. & Lovell, J. Calvin
System:
The UNT Digital Library
Origin and Development of Leading-Edge Cracks in Turbojet Engine Buckets
Report presenting an investigation to study the origin and development of leading-edge cracking in turbine buckets made of six materials: S-816, M-252, Inconel 550, Inconel 700, Hastelloy R-235, and Jetalloy 1570. Some of the buckets were also given certain stress-relief treatments. Results regarding the development of leading-edge cracks, development of bucket fractures, comparison of performance for the material tested, macro- and microexamination of unfractured and fractured buckets,
Date:
May 20, 1957
Creator:
Springsteen, D. F.; Gyorgak, C. A. & Johnston, J. R.
System:
The UNT Digital Library
Thermal relations for two-phase expansion with phase equilibrium and example for combustion products of boron-containing fuel
Report presenting a procedure for integrating equations involving pressure, temperature, and density in order to analyze an expansion process that occurs when boric oxide from fuels condenses during expansion. An example is provided to illustrate the manner in which the equations can be used to analyze a one-dimensional expansion with phase equilibrium.
Date:
May 20, 1957
Creator:
Tower, Leonard K.
System:
The UNT Digital Library
Concluding Report of Free-Spinning, Tumbling, and Recovery Characteristics of a 1/18-Scale Model of the Ryan X-13 Airplane, Coord. No. AF-199
"An investigation has been completed in the Langley 20-foot free-spinning tunnel on a l/18-scale model of the Ryan X-13 airplane to determine its spin, recovery, and tumbling characteristics, and to determine the minimum altitude from which a belly landing could be made in case of power failure in hovering flight. Model spin tests were conducted with and without simulated engine rotation. Tests without simulated engine rotation indicated two types of spins: one, a slightly oscillatory flat spin; and the other, a violently oscillatory spin" (p. 1).
Date:
May 17, 1957
Creator:
Bowman, James S., Jr.
System:
The UNT Digital Library
A Flight Investigation to Determine the Effectiveness of Mach Number 1.0, 1.2, and 1.41 Fuselage Indentations for Reducing the Pressure Drag of a 45 Degree Sweptback Wing Configuration at Transonic and Low Supersonic Speeds
Report presenting a flight investigation to determine the effectiveness of three fuselage indentations for reducing the pressure drag of a 45 degree sweptback-wing-body configuration at a range of Mach numbers. The results indicate that the supersonic area rule can be used to determine indentations with low pressure drag over a Mach number range in which the blunt leading edge is subsonic. Information about total drag and pressure drag is provided.
Date:
May 16, 1957
Creator:
Blanchard, Willard S., Jr. & Hoffman, Sherwood
System:
The UNT Digital Library
An investigation of wing-body juncture interference effects at transonic speeds for several swept-wing and body combinations
Report presenting the results of an investigation of wing-body juncture interference effects at high subsonic and transonic speeds. Three different model series were used: one with a swept wing of aspect ratio 6 and two with swept wings of aspect ratio 3. Results regarding drag, lift, pressure distributions, and tests with the body alone are provided.
Date:
May 16, 1957
Creator:
McDevitt, John B. & Taylor, Robert A.
System:
The UNT Digital Library
Relation of Currently Estimated ANP Performance to Required ANP Performance
Memorandum presenting an investigation of performance estimates of aircraft nuclear propulsion (ANP) systems. This paper includes a relation of current estimated ANP performance to the future requirements that nuclear propulsion systems will be required to meet.
Date:
May 16, 1957
Creator:
Rothrock, Addison M. & Cesaro, Richard S.
System:
The UNT Digital Library
Relation of currently estimated ANP performance to required ANP performance
Report presenting a comparison of performance estimates of aircraft nuclear propulsion (ANP) systems and an attempt to determine the manner in which the estimated nuclear propulsion system performance in conjunction with the estimated airframe performance will lead to a useful military airplane.
Date:
May 16, 1957
Creator:
Rothrock, Addison M. & Cesaro, Richard S.
System:
The UNT Digital Library
A Wind-Tunnel Investigation of the Low-Amplitude Damping in Yaw and Directional Stability of a Fuselage-Tail Configuration at Mach Numbers Up to 1.10
Report presenting a low-amplitude free-oscillation investigation at zero angle of attack of the damping in yaw and directional stability of a fuselage-tail configuration through a range of reduced frequency. The damping in yaw was found to decrease with Mach numbers above 0.8 and became the lowest at about 1.0. An increase in reduced frequency was observed to cause a decrease in damping in yaw and directional stability for the test frequency range.
Date:
May 16, 1957
Creator:
Palmer, William E.
System:
The UNT Digital Library
Approximate analysis of effects of large deflections and initial twist on torsional stiffness of a cantilever plate subjected to thermal stresses
From Summary: "An approximate analysis of the nonlinear effects of initial twist and large deflections on the torsional stiffness of a cantilever plate subjected to a nonuniform temperature distribution is presented. The Von Karman large-deflection equations are satisfied through the use of a variational principle. The results show that initial twist and applied moments can have significant effects on the changes in stiffness produced by nonuniform heating, particularly in the region of the buckling temperature difference. Results calculated by this approximate analysis are in satisfactory agreement with measured torsional deformations and changes in natural frequency."
Date:
May 15, 1957
Creator:
Heldenfels, Richard R. & Vosteen, Louis F.
System:
The UNT Digital Library
Experimental Evaluation of Swirl Can Elements for Hydrogen Fuel Combustor
Memorandum presenting a study of the performance of swirl-can combustor elements for an experimental short-length turbojet combustor utilizing hydrogen fuel at high-altitude operating conditions. Fuel was injected into each element through a tangential, sonic orifice that created a swirling fuel-air mixture within each element. Results regarding combustor blowout, combustion efficiency, outlet temperature distribution, and preliminary performance of multielement combustor are provided.
Date:
May 13, 1957
Creator:
Rayle, Warren D.; Jones, Robert E. & Friedman, Robert
System:
The UNT Digital Library
Experimental evaluation of 'swirl-can' elements for hydrogen-fuel combustor
Report presenting a study of the performance of "swirl-can" combustor elements for an experimental short-length turbojet combustor utilizing hydrogen fuel at high-altitude operating conditions. Fuel was injected into each element through a tangential , sonic orifice that created a swirling fuel-air mixture within the element. Results regarding combustor blowout, combustion efficiency, outlet temperature distribution, and preliminary performance of the multielement performance of multielement combustor are provided.
Date:
May 13, 1957
Creator:
Rayle, Warren D.; Jones, Robert E. & Friedman, Robert
System:
The UNT Digital Library
An Air-Borne Target Simulator for Use With Scope-Presentation Type Fire-Control Systems
Report describing the design and flight evaluation of an air-borne target simulator using precomputed relative kinematics for use in tracking studies of fighter aircraft equipped with scope-presentation type fire-control systems. Testing occurred in an F86D airplane equipped with a Hughes E-4 fire-control system. Results regarding relative kinematic programming considerations and restrictions to system evaluation are provided.
Date:
May 10, 1957
Creator:
Foster, John V.; Fulcher, Elmer C. & Heinle, Donovan R.
System:
The UNT Digital Library
Experimental investigation of deposition by boron-containing fuels in turbojet combustor
Report presenting an investigation conducted with trimethyl borate azeotrope and pentaborane fuels in a turbojet combustor. The primary purposes of the study were to determine the effect of boron oxide deposits on the turbine-nozzle area, combustor pressure loss, temperature distribution, and combustion efficiency. Three distinct boron deposit patterns were noted in the investigation.
Date:
May 10, 1957
Creator:
Kaufman, Warner B.; Branstetter, J. Robert & Lord, Albert M.
System:
The UNT Digital Library
Free-flight investigation to determine some effects of tail damping and wing-tail interference on the rolling effectiveness of ailerons and a spoiler on a modified-delta wing at Mach numbers from 0.6 to 1.5
Report presenting an investigation to determine some effects of tail damping and wing-tail interference on the rolling effectiveness of ailerons and a spoiler on a modified-delta wing. Results regarding the effect of adding fixed tail surfaces, effect of moving the horizontal tail out of the plane of the wing, and a comparison with theory are provided.
Date:
May 10, 1957
Creator:
English, Roland D.
System:
The UNT Digital Library
Free-flight performance of a rotating-vane-spoiler roll control system with low actuating forces
Report presenting free-flight tests of two rocket models at a range of Mach numbers to determine the control rolling effectiveness and system operation of an autorotating-vane spoiler on a missile configuration with an 80 degree delta, cruciform wing. Results indicated that the system operated fairly satisfactorily as a flicker-type roll control except at low supersonic speeds.
Date:
May 10, 1957
Creator:
Schult, Eugene D.
System:
The UNT Digital Library
Investigation of Static Stability and Drag Characteristics of a 1/10-Scale Model of the Avco Booster Vehicle at Mach Numbers of 1.60 and 2.00, Coord. No. AF-AM-58
"An investigation has been conducted in the Langley Unitary Plan Wind tunnel to determine the static stability and drag characteristics of a 1/10-scale model of the AVCO booster vehicle. The tests were made at a constant Reynolds number, based on maximum nose diameter, of 1.09 x 10(exp 6)6 at Mach numbers of 1.60 and 2.00" (p. 1).
Date:
May 10, 1957
Creator:
Church, James D. & Sista, Lawrence M.
System:
The UNT Digital Library
Performance at High Temperatures and Pressures of an Annular Turbojet Combustor Having Articulated Liner Walls
Report discussing the performance of an experimental quarter-sector annular combustor at conditions simulating supersonic flight of a cooled-turbine engine, as well as 20 different modification to the design. The final configuration was found to show no structural failures and little or no warping of liner parts after 40 hours of operation.
Date:
May 10, 1957
Creator:
McCafferty, Richard J.; Wear, Jerrold D. & Cook, William P.
System:
The UNT Digital Library
Analysis of coolant flow and pressure requirements for a return-flow turbine rotor blade design using hydrogen, helium, or air as coolant
From Introduction: "This report presents the results of an analysis to determine the coolant flow and pressure requirements for a particular return-flow turbine rooter blade design utilizing hydrogen, helium, or air as the coolant."
Date:
May 7, 1957
Creator:
Slone, Henry O. & Donoughe, Patrick L.
System:
The UNT Digital Library
An Analysis of Vertical-Tail Loads Measured in Flight on a Swept-Wing Bomber Airplane
From Introduction: "This paper presents results of an analysis of shear, bending-moment, and torque loads measured on the vertical tail during rudder-step, rudder-pulse, aileron-roll, and steady-sideslip maneuvers. In order to assess effects of Mach number and altitude, the maneuvers were performed at altitudes of 15,000, 25,000, and 35,000 feet and Mach numbers from 0.49 to 0.82."
Date:
May 7, 1957
Creator:
McGowan, William A. & Cooney, T. V.
System:
The UNT Digital Library
Bonded lead monoxide films as solid lubricants for temperatures up to 1250 degrees F
Report presenting a friction, wear, and endurance-lift study made with bonded films of mixed oxides containing lead monoxide (PbO) as the main component. The coatings lubricated over the entire temperature range, but were far more effective from 500 to 1250 degrees Fahrenheit than at the lower temperatures. Results regarding the effect of silica additions on coating formation, determination of coating composition, effect of coating thickness on friction and wear, effect of temperature on friction and wear, and endurance properties are provided.
Date:
May 7, 1957
Creator:
Sliney, Harold E. & Johnson, Robert L.
System:
The UNT Digital Library
Experimental Investigation of a Five-Stage Axial-Flow Research Compressor with Transonic Rotors in All Stages 4: Blade-Element Performance
Memorandum presenting the detailed blade-element performance of a five-stage axial-flow compressor for analysis purposes as well as to provide a contribution to the growing body of information necessary for continuing improvement in designing compressors. Results regarding overall and stage performance, blade-element performance, rotor blade-element performance, stator blade-element performance, comparison with design, consideration of boundary-layer blockage effects, and solution of equilibrium equation are provided.
Date:
May 7, 1957
Creator:
Sandercock, Donald M.
System:
The UNT Digital Library
The application of matrix methods to coordinate transformations occurring in systems studies involving large motions of aircraft
Report presenting the method and advantages of matrix algebra in setting up the geometric aspects of problems of airplane motion. The paper is divided into two parts. The first is about the aspects of matrix algebra required for use in orthogonal transformations and the other shows how to use orthogonal transformations in matrix form by applying them in several examples.
Date:
May 1957
Creator:
Doolin, Brian F.
System:
The UNT Digital Library