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Theoretical Investigation of the Performance of Proportional Navigation Guidance Systems: Effect of Method of Positioning the Radar Antenna on the Speed of Response

Description: Memorandum presenting a linear theoretical analysis made of the performance of three proportional navigation guidance systems installed in a given supersonic, variable-incidence, boost-glide, antiaircraft missile at Mach numbers of 2.7 and 1.3. Three guidance systems are compared on the basis of the maximum obtainable speed of response of the missile and guidance-system combination consistent with adequate stability. Results regarding the effect of method of positioning the radar antenna on the… more
Date: August 13, 1952
Creator: Abramovitz, Marvin
Partner: UNT Libraries Government Documents Department
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A correlation with flight tests of results obtained from the measurement of wing pressure distributions on a 1/4-scale model of the X-1 airplane (10-percent-thick wing)

Description: Report presenting an investigation in the transonic tunnel of the aerodynamic characteristics of a scale model of an X-1 airplane in order to correlate wing pressure-distribution results obtained in a slotted wind tunnel with flight test data on the full-scale airplane. Results regarding basic pressure measurements, and correlation of pressure measurements are provided.
Date: September 3, 1952
Creator: Runckel, Jack F. & Henderson, James H.
Partner: UNT Libraries Government Documents Department
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Investigation of liquid fluorine and hydrazine-ammonia mixture in 100-pound-thrust rocket engine

Description: Report presenting the specific impulse, characteristic velocity, thrust coefficient, and heat rejection of liquid fluorine and a fuel consisting of a hydrazine-ammonia mixture for a range of fuel percentages in a 100-pound-thrust rocket engine designed for a combustion-chamber pressure of 300 pounds per square inch absolute. The fuel consisted of 59 percent hydrazine, 37 percent ammonia, and 4 percent water. The attainment of maximum performance with liquid fluorine as a rocket oxidant will req… more
Date: October 29, 1952
Creator: Ordin, Paul M.; Rothenberg, Edward A. & Rowe, William H.
Partner: UNT Libraries Government Documents Department
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An investigation of some factors affecting the drag of relatively large nonlifting bodies of revolution in a slotted transonic wind tunnel

Description: Report presenting an investigation to study some factors affecting the drag of relatively large nonlifting bodies of revolution at transonic speeds in the 8-foot transonic tunnel. Drag and surface pressure measurements were made for two geometrically similar bodies of revolution of 8-inch and 4-inch maximum diameter at zero angle of attack through a range of Mach numbers.
Date: January 15, 1953
Creator: Pendley, Robert E. & Bryan, Carroll R.
Partner: UNT Libraries Government Documents Department
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Results of flight tests to determine the drag of finite-length cylinders at high Reynolds numbers for a Mach number range of 0.5 to 1.3

Description: Report presenting the results of a free-flight investigation to determine the drag of circular, finite-length cylinders for a range of Mach numbers. For supersonic speeds, the drag of circular cylinders was found to be largely independent of fineness ratio and Reynolds number.
Date: June 16, 1952
Creator: Welsh, Clement J.
Partner: UNT Libraries Government Documents Department
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Effect of water vapor on combustion of magnesium hydrocarbon slurry fuels in small-scale afterburner

Description: Report presenting testing of JP-3 fuel and a slurry of 60 percent powdered magnesium in JP-3 fuel in a small-scale afterburner in the presence of large quantities of water vapor. The results indicated that total temperature, combustion efficiency, and air specific impulse were improved when the magnesium slurry was used, but the improvements came at the cost of increased liquid consumption.
Date: October 22, 1952
Creator: Tower, Leonard K.
Partner: UNT Libraries Government Documents Department
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Influence of fuselage-mounted rocket boosters on flow field at inlet and on diffuser performance of strut-mounted engine at Mach numbers of 1.8 and 2.0

Description: Report presenting an investigation of the effect of fuselage-mounted rocket boosters on a strut-mounted engine in the 8- by 6-foot supersonic wind tunnel at Mach numbers of 1.8 and 2.0. The boosters were pairs of circular cylinders with conical forebodies mounted on the top and bottom of the fuselage, and the engine was mounted on a horizontal strut. Results regarding the characteristics of the flow field, effect of putting the boosters in several positions, and effect of angle of attack are pr… more
Date: October 29, 1952
Creator: Wise, George A. & Obery, Leonard J.
Partner: UNT Libraries Government Documents Department
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A summary and analysis of the low-speed longitudinal characteristics of swept wings at high Reynolds number

Description: Report presenting the low-speed longitudinal characteristics of swept wings derived from investigations at high Reynolds numbers. Two different types of flow separation, trialing-edge and leading-edge separation, are identified and discussed.
Date: August 14, 1952
Creator: Furlong, G. Chester & McHugh, James G.
Partner: UNT Libraries Government Documents Department
open access

Effect of Geometry on Secondary Flows in Blade Rows

Description: Memorandum presenting an investigation of the influence of blade-row geometry on secondary flows in a two-dimensional cascade by varying independently stagger angle, aspect ratio, solidity, and angle of attack and by providing blade fillets. Stagger angle and aspect ratio had no appreciable effect on this secondary flow, whereas solidity and angle of attack did affect the flow patterns indicating the turning as a major parameter.
Date: October 16, 1952
Creator: Hansen, A. G.; Costello, G. R. & Herzig, H. Z.
Partner: UNT Libraries Government Documents Department
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Rocket-Model Investigation to Determine the Force and Hinge-Moment Characteristics of a Half-Delta Tip Control on a 59 Degree Sweptback Delta Wing Between Mach Numbers of 0.55 and 1.43

Description: Report presenting a free-flight investigation of a rocket-powered control research model to determine the force and hinge-moment characteristics of a half-delta tip control on a delta wing. Results regarding the control hinge moments, control normal force, and total normal force are provided.
Date: October 6, 1952
Creator: Martz, C. William; Church, James D. & Goslee, John W.
Partner: UNT Libraries Government Documents Department
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Investigation at high and low subsonic Mach numbers of two symmetrical 6-percent-thick airfoil sections designed to have high maximum lift coefficients at low speeds

Description: Report presenting an investigation at high and low subsonic Mach numbers of two symmetrical 6-percent-thick airfoil sections derived to have high maximum lift at low speeds. The high-speed portion of the investigation included lift, drag, and pitching moment measurements.
Date: October 17, 1952
Creator: Paradiso, Nicholas J.
Partner: UNT Libraries Government Documents Department
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Investigation of ram-jet afterburning as a means of varying effective exhaust nozzle area

Description: Report presenting a discussion of the flow mechanism in an afterburner extension to a ramjet engine. An experimental evaluation of the operation of 16-inch ramjet equipped with an afterburner at Mach number 1.8 and 2.0 in the supersonic wind tunnel. The experimental data confirmed the proposed method of afterburner operation.
Date: November 17, 1952
Creator: Perchonok, Eugene & Wilcox, Fred A.
Partner: UNT Libraries Government Documents Department
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An investigation of the subsonic speed range of a full-span and a semispan model of a plane wing and of a cambered and twisted wing, all having 45 degrees of sweepback

Description: Report presenting a wind-tunnel investigation of two full-span and two semispan models with 45 degrees of sweepback, an aspect ratio of 5.5, and a taper ratio of 0.53. The lift and drag data obtained from tests of the semispan agreed well with data obtained on the full-span model. Results regarding a comparison of the data for the full-span and semispan models, full-span model data, and effect of surface roughness are provided.
Date: June 26, 1952
Creator: Shibata, Harry H.; Bandettini, Angelo & Cleary, Joseph
Partner: UNT Libraries Government Documents Department
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Procedure for calculating turbine blade temperatures and comparison of calculated with observed values for two stationary air-cooled blades

Description: Report presenting an investigation for stationary turbine blades with 10 tubes and 13 fins forming the internal heat-transfer surfaces in order to accurately predict local turbine blade temperatures. Results regarding the comparison of calculated and measured midchord blade temperatures, comparison of calculated and measured temperatures near blade trailing edge, comparison of calculated and measured temperatures near the blade leading edge, the influence of errors in calculated temperatures on… more
Date: September 29, 1952
Creator: Brown, W. Byron; Slone, Henry O. & Richards, Hadley T.
Partner: UNT Libraries Government Documents Department
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Investigation of the drag of various axially symmetric nose shapes of fineness ratio 3 for Mach numbers from 1.24 to 3.67

Description: Report presenting foredrag measurements made at zero angle of attack for a series of fineness ratio 3 nose shapes. The types of noses investigated included theoretically derived minimum drag shapes, hemispherically blunted cones, and other more common profiles. Results regarding hemispherically blunted cones, theoretical minimum drag nose shapes, and comparison of foredrag of all the force models are provided.
Date: November 6, 1952
Creator: Perkins, Edward W. & Jorgensen, Leland H.
Partner: UNT Libraries Government Documents Department
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Analysis of the turbojet engine for propulsion of supersonic fighter airplanes

Description: An analytical investigation was made of two supersonic interceptor type airplanes to determine the most desirable turbojet engine characteristics for this application The airplanes were designed differently primarily because of the amount of subsonic flight incorporated in the flight plan--one flight having none and the other, a cruise radius of 400 nautical miles. Several power plant design variables were varied independently to determine the effect of changes in each parameter on airplane per… more
Date: October 26, 1953
Creator: Gabriel, David S.; Krebs, Richard P.; Wilcox, E. Clinton & Koutz, Stanley L.
Partner: UNT Libraries Government Documents Department
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Effect of trailing edge thickness on lift at supersonic velocities

Description: Report presenting measurements of lift made on various rectangular-plan-form wings differing in trailing-edge thickness, profile shape, maximum thickness ratio, and aspect ratio. Experiments were conducted at a range of Mach numbers, Reynolds numbers, and wings with and without boundary-layer trips. Results regarding a comparison of experimental results with theory at moderate supersonic Mach numbers and calculations for hypersonic Mach numbers are provided.
Date: July 10, 1952
Creator: Chapman, Dean R. & Kester, Robert H.
Partner: UNT Libraries Government Documents Department
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Experimental investigation of air-cooled turbine blades in turbojet engine 11: internal-strut-supported rotor blade

Description: Report presenting an investigation of an air-cooled internal-strut-supported blade in a modified production turbojet engine to determine the cooling effectiveness of this type of blade and the cooling-air pressure loss through the blade under engine operating conditions. Experimental results are presented and compared with the results of an analytical investigation.
Date: June 2, 1952
Creator: Cochran, Reeves P.; Stepka, Francis S. & Krasner, Morton H.
Partner: UNT Libraries Government Documents Department
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A Theoretical Investigation of the Effect of a Target Seeker Sensitive to Pitch Attitude on the Dynamic Stability and Response Characteristics of a Supersonic Canard Missile Configuration

Description: Report presenting a theoretical investigation of the longitudinal dynamic characteristics of an automatically stabilized supersonic canard missile configuration with a target seeker sensitive to changes in pitch altitude. Variables explored include seeker gain, time delay, and non-linearities, including dead spots in the seeker.
Date: August 26, 1952
Creator: Gates, Ordway B., Jr. & Schy, Albert A.
Partner: UNT Libraries Government Documents Department
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Investigation of Stresses Due to Thermal Gradients in Typical Aircraft Structures

Description: Memorandum presenting an investigation of a series of five 75S-T6 aluminum-alloy elementary skin and spar-cap combinations with skin varying from 0.051 to 0.500 inch in thickness to determine the temperature and stress gradients resulting from the application of heat to the surface. The data are presented in the form of tables of the measured temperatures and stresses calculated from the measured strains.
Date: January 25, 1952
Creator: Barzelay, Martin E. & Boison, James C.
Partner: UNT Libraries Government Documents Department
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Study of the Pressure Rise Across Shock Waves Required to Separate Laminar and Turbulent Boundary Layers

Description: Report presenting a study and experimental investigation on the pressure rise across shock waves required to cause separation of the boundary layer on a flat plate. The interaction of shock wave and boundary layer was investigated experimentally when the boundary layer was caused to separate from the surface of a tube. Results regarding testing and correlation with other results are provided.
Date: May 5, 1952
Creator: Donaldson, Coleman duP. & Lange, Roy H.
Partner: UNT Libraries Government Documents Department
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The longitudinal characteristics at Mach numbers up to 0.92 of a cambered and twisted wing having 40 degrees of sweepback and an aspect ratio of 10

Description: Report presenting an investigation of a sweptback wing in combination with a fuselage of a type considered suitable for long-range, high-speed airplanes in the 12-foot pressure wind tunnel. The investigations included tests of the wing alone, the wing-fuselage combination, and the effects of fences.
Date: September 15, 1952
Creator: Edwards, George G.; Tinling, Bruce E. & Ackerman, Arthur C.
Partner: UNT Libraries Government Documents Department
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An Experimental Investigation of the Base Pressure Characteristics of Nonlifting Bodies of Revolution at Mach Numbers From 2.73 to 4.98

Description: Report presenting an investigation in the supersonic wind tunnel to determine some of the base pressure characteristics of related bodies of revolution at zero angle of attack. The basic body shape was a 10-caliber tangent ogive nose with a cylindrical afterbody, while other shapes tested had either a blunt-nosed profile or a boat-tailed afterbody. Results regarding the variation of pressure over the base, variation of base pressure with Reynolds number, effect of nose and afterbody shape, vari… more
Date: September 17, 1952
Creator: Reller, John O., Jr. & Hamaker, Frank M.
Partner: UNT Libraries Government Documents Department
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