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Investigations toward simplification of missile control systems (open access)

Investigations toward simplification of missile control systems

Paper presenting three ideas regarding potential simplifications of missile-control systems in order to make them more reliable without sacrificing system performance. The three methods presented include an autorotating-vane spoiler, a bellows flap, and free controls. All are based on modified airplane control systems.
Date: November 12, 1953
Creator: Curfman, Howard J., Jr.; Strass, H. Kurt & Crane, Harold L.
System: The UNT Digital Library
The Effects of a Small Jet of Air Exhausting From the Nose of a Body of Revolution in Supersonic Flow (open access)

The Effects of a Small Jet of Air Exhausting From the Nose of a Body of Revolution in Supersonic Flow

Report presenting the results of an investigation to determine the effects of a small jet of air exhausting from the nose of an elliptical body of revolution upon boundary-layer transition and the viscous, pressure, and total drag of the forebody at three body stations at Mach number 1.62. The jet effects on body pressure, pressure variations, boundary-layer transition, and total drag are provided.
Date: November 12, 1952
Creator: Love, Eugene S.
System: The UNT Digital Library
Transonic Wind-Tunnel Tests of the Launch, Jettison, and Longitudinal Characteristics of an Airplane and Missile Model Combination (open access)

Transonic Wind-Tunnel Tests of the Launch, Jettison, and Longitudinal Characteristics of an Airplane and Missile Model Combination

Report presenting tests of an airplane model equipped with missiles to investigate the capability of that combination to achieve satisfactory launching and jettisoning of the missiles. Information about pylon modifications, missiles in launch positions, missile trajectory, and missiles in jettison positions is provided.
Date: November 20, 1957
Creator: Cleary, Joseph W.; Frank, Joseph L. & Dewey, C. Forbes, Jr.
System: The UNT Digital Library
Analysis of turbojet and ram-jet engine cycles using various fuels (open access)

Analysis of turbojet and ram-jet engine cycles using various fuels

From Introduction: "These data have been collected for presentation in this report to illustrate the performance of turbojet and ram-jet cycles utilizing several of the more promising high-energy fuels. Results are presented in terms of engine over-all efficiency and thrust per pound of airflow as functions of flight Mach number."
Date: November 27, 1956
Creator: Wilcox, E. Clinton; Weber, Richard J. & Tower, Leonard K.
System: The UNT Digital Library
Wing Pressure Distributions Over the Lift Range of the Convair XF92A Delta-Wing Airplane at Subsonic and Transonic Speeds (open access)

Wing Pressure Distributions Over the Lift Range of the Convair XF92A Delta-Wing Airplane at Subsonic and Transonic Speeds

Report presenting chordwise pressure distributions measured over the left wing of the Convair XF-92A delta-wing airplane to determine the effect of lift on the wing characteristics at subsonic and transonic Mach numbers. Results regarding the chordwise pressure distributions, wing-section aerodynamic characteristics, spanwise distributions, and elevon-section loads are provided.
Date: November 30, 1955
Creator: Keener, Earl R. & Jordan, Gareth H.
System: The UNT Digital Library
Investigation of a high-pressure-ratio eight-stage axial-flow research compressor with two transonic inlet stages 6: over-all performance, rotating stall, and blade vibration at low and intermediate compressor speeds (open access)

Investigation of a high-pressure-ratio eight-stage axial-flow research compressor with two transonic inlet stages 6: over-all performance, rotating stall, and blade vibration at low and intermediate compressor speeds

Report presenting an investigation to determine the overall performance of the modified eight-stage axial-flow compressor with new fourth-stage stator blades as part of a study of the problems encountered in a high-pressure-ratio axial-flow compressor with transonic inlet stages. The performance of the compressor was determined over a range of weight flows at equivalent speeds from 30 to 100 percent of design speed.
Date: November 1, 1955
Creator: Standahar, Raymond M.; Hanson, Morgan P. & Geye, Richard P.
System: The UNT Digital Library
Transonic wind-tunnel investigation of the effects of external stores and store position on the aerodynamic characteristics of a 1/16-scale model of the Douglas D-558-II research airplane (open access)

Transonic wind-tunnel investigation of the effects of external stores and store position on the aerodynamic characteristics of a 1/16-scale model of the Douglas D-558-II research airplane

Report presenting an investigation in the transonic tunnel to determine the effects of adding external, pylon-suspended stores to a model of the Douglas D-558-II research airplane. Tests were made for two spanwise store locations and covered a range of angles of attack and Mach numbers. Results regarding the drag, lift, and pitching-moment characteristics are provided.
Date: November 8, 1955
Creator: Kelly, Thomas C.
System: The UNT Digital Library
Analysis of Low-Temperature Nuclear-Powered Ram-Jet Missile for High Altitudes (open access)

Analysis of Low-Temperature Nuclear-Powered Ram-Jet Missile for High Altitudes

Report presenting the gross weight and uranium investment of nuclear-powered, direct-air, shieldless, ram-jet missiles for a range of altitudes and Mach numbers. Results regarding the effect of reactor operating conditions and flight conditions on ramjet performance and effect of assumptions on ramjet performance are provided.
Date: November 9, 1955
Creator: Sams, Eldon W. & Rom, Frank E.
System: The UNT Digital Library
Boundary-Layer Transition at High Reynolds Numbers as Obtained in Flight of a 20 Degree Cone-Cylinder With Wall to Local Stream Temperature Ratios Near 1.0 (open access)

Boundary-Layer Transition at High Reynolds Numbers as Obtained in Flight of a 20 Degree Cone-Cylinder With Wall to Local Stream Temperature Ratios Near 1.0

Boundary-layer transition data at low ratios of wall to local stream temperature have been obtained during the free flight of a highly polished cone-cylinder to a maximum Mach number of 5.02 A maximum transition Reynolds number of 32 x 10(exp 6) occurred at a distance of 25.84 inches from the cone apex. The temperature ratio at transition for a local Mach number of 4.0 was approximately 1.30 as compared with theoretical infinite stability solutions of 1.47 and 1.65 by Dunn and Lin (three-dimensional) and Van Driest (two-dimensional), respectively.
Date: November 3, 1955
Creator: Rabb, Leonard & Disher, John H.
System: The UNT Digital Library
Spark ignition of flowing gases 5: application of fuel-air-ratio and initial-temperature data to ignition theory (open access)

Spark ignition of flowing gases 5: application of fuel-air-ratio and initial-temperature data to ignition theory

Report presenting a study to show the effect of fuel-air ratio and initial temperature on spark-ignition energy and to apply the results to a previously developed theory of ignition. Results regarding initial-temperature effect and fuel-air-ratio effect are provided.
Date: November 1, 1955
Creator: Swett, Clyde C., Jr.
System: The UNT Digital Library
Design considerations of a condensing system for vaporized magnesium (open access)

Design considerations of a condensing system for vaporized magnesium

The effect of the design characteristics of various condensing chambers on magnesium build-up at the chamber inlet was investigated. The condensing chambers are used in the vapor-condensation process for making magnesium slurries. A complete description of the various chamber designs and the procedure used in testing the chambers is given. The results are evaluated on the basis of clogging and total magnesium distilled per run. Orifice design was also considered.
Date: November 30, 1955
Creator: Witzke, Walter R.; Prok, George M. & Keller, Thomas A.
System: The UNT Digital Library
Lateral-control investigation at transonic speeds of differentially deflected horizontal-tail surfaces for a configuration having a 6-percent-thick 45 degree sweptback wing (open access)

Lateral-control investigation at transonic speeds of differentially deflected horizontal-tail surfaces for a configuration having a 6-percent-thick 45 degree sweptback wing

Report presenting an investigation in the 16-foot transonic tunnel to determine the lateral-control effectiveness of differentially deflected horizontal-tail surfaces mounted behind a 45 degree sweptback wing-fuselage combination. The effectiveness of the differentially deflected horizontal tail as a lateral-control device was found to be essentially independent of angle of attack and Mach number even in the transonic region. Results regarding the effects of differential deflection of horizontal-tail surfaces and effects of the vertical tail are provided.
Date: November 15, 1955
Creator: Critzos, Chris C.
System: The UNT Digital Library
Performance of a high-solidity high-pressure-ratio transonic rotor (open access)

Performance of a high-solidity high-pressure-ratio transonic rotor

A high-solidity low-aspect-ratio transonic rotor with an inlet hub-tip ratio of 0.52 was investigated experimentally. The rotor developed a total-pressure tatio of 1.93 and an efficiency of 92 percent at an equivalent wheel tip speed of 1036 feet per second. The feasibility of using this rotor as a component of an inlet stage of an axial-flow compressor was investigated.
Date: November 8, 1955
Creator: Neumann, Harvey E.
System: The UNT Digital Library
Flight Investigation at Supersonic Mach Numbers of an Automatic Acceleration Control Missile in Which Rate Damping Is Obtained From a Linear Accelerometer Placed Ahead of the Missile Center of Gravity (open access)

Flight Investigation at Supersonic Mach Numbers of an Automatic Acceleration Control Missile in Which Rate Damping Is Obtained From a Linear Accelerometer Placed Ahead of the Missile Center of Gravity

Report presenting a supersonic flight investigation of a roll-stabilized acceleration control missile for a Mach number range from 1.4 to 1.7. The control system operation was found to be satisfactory and applicable to some present-day missiles using linear acceleration commands. Results regarding analysis, preflight simulator results, a comparison between simulator and analytical results, flight test results, and a comparison between the flight test and preflight simulator results are presented.
Date: November 8, 1955
Creator: Seaberg, Ernest C.; Sproull, Royce H. & Reid, H. J. E., Jr.
System: The UNT Digital Library
The effect of leading-edge droop upon the pressure distribution and aerodynamic loading characteristics of a 45 degree sweptback wing at transonic speeds (open access)

The effect of leading-edge droop upon the pressure distribution and aerodynamic loading characteristics of a 45 degree sweptback wing at transonic speeds

Report presenting an investigation in the 16-foot transonic tunnel to determine the effects of leading-edge droop on the pressure distribution on a 45 degree sweptback wing with an aspect ratio of 4, a taper ratio of 0.6, and NACA 65A006 airfoil sections parallel to the plane of symmetry. Results regarding the chordwise pressure distributions, wing-panel characteristics, wing-section characteristics, and maximum additional normal load on wing leading edge are provided.
Date: November 8, 1955
Creator: Schmeer, James W.
System: The UNT Digital Library
Effect of inlet flow distortion on compressor stall and acceleration characteristics of a J65-B-3 turbojet engine (open access)

Effect of inlet flow distortion on compressor stall and acceleration characteristics of a J65-B-3 turbojet engine

Report presenting an investigation to determine the effects of inlet flow distortion on the compressor stall and engine acceleration characteristics of a J65-B-3 turbojet engine. A sinusoidal circumferential distortion and two abrupt radial tip flow distortions were introduced at the engine inlet at several altitudes and Mach number 0.8. Results regarding the definition of inlet flow distortions, acceleration limits, compressor pressure ratio at stall, fuel flow for stall, and maximum acceleration rate are provided.
Date: November 18, 1955
Creator: Fenn, David B. & Sivo, Joseph N.
System: The UNT Digital Library
Comparative Dispersion Data From Ground-Launched 2.25-Inch Rockets Equipped With Cruciform and Monoplane Fins (open access)

Comparative Dispersion Data From Ground-Launched 2.25-Inch Rockets Equipped With Cruciform and Monoplane Fins

Report presenting testing of about 150 rounds of 2.25-inch subcaliber aircraft rockets equipped with standard cruiform fins and twisted monoplane fins. No significant difference in dispersion was observed for the different configurations of fins on the rockets. Results regarding the stability of the different types of rockets, and general characteristics of the flight paths are provided.
Date: November 1, 1955
Creator: Purser, Paul E.
System: The UNT Digital Library
Preliminary Free-Jet Performance of XRJ43-MA-3 Flight-Weight Ram-Jet Engine at Mach Numbers of 2.35, 2.50, and 2.70 (open access)

Preliminary Free-Jet Performance of XRJ43-MA-3 Flight-Weight Ram-Jet Engine at Mach Numbers of 2.35, 2.50, and 2.70

From Summary: "The performance of the XRJ43-MA-3 flight-weight ram-jet engine has been investigated in a free-jet facility as part of the development program for the "Bomarc," ram-jet powered, interceptor-type missile. The engine performance was obtained at Mach numbers of 2.35, 2.50, and 2.70, altitudes from 50,000 to 75,000 feet, and Miami hot day and cold day inlet temperatures at an angle of attack of +4 deg. At each flight condition investigated, the engine control set an inner-ring fuel flow which was held constant as outer-ring fuel flow was varied."
Date: November 18, 1955
Creator: McAulay, John E. & Prince, William R.
System: The UNT Digital Library
Effect of surface-active additives on physical properties of slurries of vapor-process magnesium (open access)

Effect of surface-active additives on physical properties of slurries of vapor-process magnesium

The presence of 3 to 5 percent surface-active additive gave the lowest Brookfield apparent viscosity, plastic viscosity, and yield value that were obtained for slurry fuels containing approximately 50 percent vapor-process magnesium in JP-1 fuel. The slurries settled little and were easily remixed. A polyoxyethylene dodecyl alcohol was the most effective of 13 additives tested in reducing the Brookfield apparent viscosity and the yield value of the slurry. The seven most effective additives all had a hydroxyl group plus an ester or polyoxethylene group in the molecule. The densities of some of the slurries were measured.
Date: November 3, 1955
Creator: Pinns, Murray L.
System: The UNT Digital Library
Low-Amplitude Damping-in-Pitch Characteristics of Four Tailless Swept Wing-Body Combinations at Mach Numbers From 0.85 to 1.30 as Obtained With Rocket-Powered Models (open access)

Low-Amplitude Damping-in-Pitch Characteristics of Four Tailless Swept Wing-Body Combinations at Mach Numbers From 0.85 to 1.30 as Obtained With Rocket-Powered Models

Report presenting an investigation to determine the damping-in-pitch characteristics of four rocket-powered wing-body combinations for a range of Mach numbers from 0.85 to 1.30. The models were tested at the same center-of-gravity location and had identical bodies. Information about the trim, lift, static longitudinal stability, dynamic longitudinal stability, and drag is provided.
Date: November 24, 1954
Creator: D'Aiutolo, Charles T.
System: The UNT Digital Library
Experimental investigation of drag of afterbodies with exiting jet at high subsonic Mach numbers (open access)

Experimental investigation of drag of afterbodies with exiting jet at high subsonic Mach numbers

Report presenting an investigation to determine the pressure drag of various blunt-based conical afterbodies at a range of Mach numbers. A generalized series of bodies was included which incorporated convergent nozzles discharging unheated jets at various pressures from the base. Results regarding the afterbodies without the jet and afterbodies with the jet are provided.
Date: November 29, 1954
Creator: Salmi, Reino J.
System: The UNT Digital Library
A Transonic Wind-Tunnel Investigation of the Longitudinal Force and Moment Characteristics of a Plane and a Cambered 3-Percent-Thick Delta Wing of Aspect Ratio 3 on a Slender Body (open access)

A Transonic Wind-Tunnel Investigation of the Longitudinal Force and Moment Characteristics of a Plane and a Cambered 3-Percent-Thick Delta Wing of Aspect Ratio 3 on a Slender Body

Report presenting an investigation of the effects of leading-edge camber without twist on an aspect-ratio-3 delta wing of thickness ratio 3, a body with an ogive nose, and a cylindrical afterbody. Results regarding the base pressures and body characteristics and wing-body combinations are provided.
Date: November 15, 1954
Creator: Burrows, Dale L. & Palmer, William E.
System: The UNT Digital Library
An investigation at high subsonic speeds of the pressure distributions on a 45 degree  sweptback vertical tail in sideslip with and without a 45 degree sweptback horizontal tail located on the fuselage center line (open access)

An investigation at high subsonic speeds of the pressure distributions on a 45 degree sweptback vertical tail in sideslip with and without a 45 degree sweptback horizontal tail located on the fuselage center line

Report presenting an investigation in the high-speed tunnel at high subsonic speeds and several angles of attack of the chordwise pressure distribution at six spanwise stations on a 45 degree sweptback, untapered vertical tail in sideslip. The presence of the horizontal tail slightly increased the value of section normal-force coefficients on the vertical tail but did not materially alter the nature of the load distribution.
Date: November 2, 1954
Creator: Wiley, Harleth G. & Moseley, William C., Jr.
System: The UNT Digital Library
Thrust and pumping characteristics of a series of ejector-type exhaust nozzles at subsonic and supersonic flight speeds (open access)

Thrust and pumping characteristics of a series of ejector-type exhaust nozzles at subsonic and supersonic flight speeds

Report presenting an investigation conducted in the 8- by 6-foot supersonic wind tunnel to determine the thrust and pumping characteristics of a series of ejector exhaust nozzles. Data were obtained for various ejector diameter and spacing ratios at a range of Mach numbers, pressure-ratio ranges, and secondary-primary weight-flow ratios. Results regarding the primary-nozzle mass-flow coefficients, performance comparison of configurations, effect of free-stream Mach number on the ejectors, net thrust characteristics, and comparison to conventional nozzles are provided.
Date: November 17, 1954
Creator: Hearth, Donald P. & Valerino, Alfred S.
System: The UNT Digital Library