Preliminary Analysis of a Nuclear Powered Supersonic Airplane Using Ramjet Engines (open access)

Preliminary Analysis of a Nuclear Powered Supersonic Airplane Using Ramjet Engines

Report discussing performance estimates for several airplanes using General Electric AC-210 ramjet nuclear-powered engines. Assumptions used for designing the engines, radiation shield, and airframe are described. Potential tradeoffs in regards to power and weight reduction are also discussed.
Date: April 11, 1958
Creator: Weber, Richard J. & Connolley, Donald J.
System: The UNT Digital Library
Transonic wind-tunnel investigation of the effects of indentation on the wing loads of a 45 degree sweptback wing-body combination (open access)

Transonic wind-tunnel investigation of the effects of indentation on the wing loads of a 45 degree sweptback wing-body combination

Report presenting the effects of an angle of incidence of 4 degrees and body indentation on wing loads of a sweptback wing-body combination at a range of Mach numbers. The wing had an aspect ratio of 4, taper ratio of 0.3, 45 degrees of sweepback of the quarter-chord line, and NACA 65A006 airfoil sections parallel to the plane of symmetry. Results regarding the effect of incidence and effect of body indentation are provided.
Date: January 11, 1956
Creator: Platt, Robert J., Jr.
System: The UNT Digital Library
Effects of Secondary-Air Flow on Annular Base Force of a Supersonic Airplane (open access)

Effects of Secondary-Air Flow on Annular Base Force of a Supersonic Airplane

Memorandum presenting an investigation of the effect of base bleed on the base force of a supersonic-interceptor model in the 8- by 6-foot supersonic wind tunnel. Two groups of fixed-geometry nozzles and shroud combinations simulating double-iris-type configurations were evaluated over a range of secondary to primary exit-diameter ratios.
Date: October 11, 1954
Creator: Vargo, Donald J.
System: The UNT Digital Library
Flight Measurements of Section Efficiency, Thrust, and Power of a Supersonic-Type Propeller at Mach Numbers to 0.9 (open access)

Flight Measurements of Section Efficiency, Thrust, and Power of a Supersonic-Type Propeller at Mach Numbers to 0.9

Report discussing testing on a supersonic-type propeller designed for a forward Mach number of 0.95, advance ratio of 2.2, and power coefficient of 0.26. Thrust distributions were found to be smooth and uniform over a range of Mach numbers, indicating efficient operation.
Date: January 11, 1956
Creator: Hammack, Jerome B. & O'Bryan, Thomas C.
System: The UNT Digital Library
The Origin and Distribution of Supersonic Store Interference From Measurement of Individual Forces on Several Wing-Fuselagestore Configurations 1. - Swept-Wing Heavy-Bomber Configuration With Large Store (Nacelle). Lift and Drag; Mach Number, 1.61 (open access)

The Origin and Distribution of Supersonic Store Interference From Measurement of Individual Forces on Several Wing-Fuselagestore Configurations 1. - Swept-Wing Heavy-Bomber Configuration With Large Store (Nacelle). Lift and Drag; Mach Number, 1.61

Memorandum presenting a supersonic wind-tunnel investigation of the origin and distribution of store interference in the 4- by 4-foot supersonic pressure tunnel at Mach number 1.6 in which separate forces on a store, a fuselage, a swept wing, and a swept-wing-fuselage combination were measured. The store was separately sting-mounted on its own six-component internal balance and was traversed through a wide systematic range of spanwise, chordwise, and vertical positions.
Date: March 11, 1955
Creator: Smith, Norman F. & Carlson, Harry W.
System: The UNT Digital Library
Performance of JP-4 Fuel With Fluorine-Oxygen Mixtures in 1000-Pound-Thrust Rocket Engines (open access)

Performance of JP-4 Fuel With Fluorine-Oxygen Mixtures in 1000-Pound-Thrust Rocket Engines

Memorandum presenting seven injectors of four different types that were tested for use with JP-4-oxygen-fluorine propellant combinations. By using the best of the injectors, high characteristic velocities were obtained over the complete range of 0- to 70-percent fluorine in the oxidant. Results regarding injector performance, heat rejection, injector with triplet-jet elements in skewed array, and fluorine addition are provided.
Date: June 11, 1958
Creator: Nored, Donald L. & Douglass, Howard W.
System: The UNT Digital Library
Initial inclination of the mixing boundary separating an exhausting supersonic jet from a supersonic ambient stream (open access)

Initial inclination of the mixing boundary separating an exhausting supersonic jet from a supersonic ambient stream

Report presenting calculations of the initial inclination of the mixing boundary separating an exhausting supersonic jet from an external supersonic stream as a function of jet static-pressure ratio.
Date: January 11, 1956
Creator: Love, Eugene S.
System: The UNT Digital Library
Analysis of Meteorological Data Obtained During Flight in a Supercooled Stratiform Cloud of High Liquid-Water Content (open access)

Analysis of Meteorological Data Obtained During Flight in a Supercooled Stratiform Cloud of High Liquid-Water Content

"Flight icing-rate data obtained in a dense and abnormally deep supercooled stratiform cloud system indicated the existence of liquid-water contents generally exceeding values in amount and extent previously reported over the midwestern sections of the United States. Additional information obtained during descent through a part of the cloud system indicated liquid-water contents that significantly exceeded theoretical values, especially near the middle of the cloud layer. The growth of cloud droplets to sizes that resulted in sedimentation from the upper portions of the cloud is considered to be a possible cause of the high water contents near the center of the cloud layer" (p. 1).
Date: July 11, 1951
Creator: Perkins, Porter J. & Kline, Dwight B.
System: The UNT Digital Library
Stability of Ballistic Reentry Bodies (open access)

Stability of Ballistic Reentry Bodies

Report discussing various features of the stability of ballistic reentry shapes, including considerations for ballistic-missile and manned-satellite reentry capsules. Attainment of satisfactory stability of reentry bodies with subsonic terminal velocities was not found to be too difficult, but undesirable features that may cause marginal stability characteristics may be introduced in an effort to minimize weight. Reentry bodies with supersonic terminal velocities have fewer stability issues.
Date: August 11, 1958
Creator: Bird, John D. & Reese, David E., Jr.
System: The UNT Digital Library
Flight, Analog-Simulator, and Analytical Studies of an Automatically Controlled Interceptor Which Uses a Bank-Angle-Error Computer for Lateral Commands (open access)

Flight, Analog-Simulator, and Analytical Studies of an Automatically Controlled Interceptor Which Uses a Bank-Angle-Error Computer for Lateral Commands

Report presenting the tracking performance of an automatically controlled interceptor in which the deflection channel incorporated a bank-angle-error computer that commanded rolling velocities of the interceptor proportional to the computed bank-angle errors. Results regarding gravity terms included in bank-angle-error computation and a comparison of modified system using bank-angle-error computer with the prototype system are provided.
Date: August 11, 1958
Creator: Cheatham, Donald C. & Brissenden, Roy F.
System: The UNT Digital Library
Investigation at Mach Number 1.91 of Spreading Characteristics of Jet Expanding From Choked Nozzles (open access)

Investigation at Mach Number 1.91 of Spreading Characteristics of Jet Expanding From Choked Nozzles

Report presenting an investigation at Mach number 1.91 to determine the gross spreading characteristics of jets expanding from convergent and convergent-divergent nozzles using total-temperature surveys. Results regarding the preliminary development and jet spreading characteristics of the different types of nozzles are provided.
Date: February 11, 1952
Creator: Rousso, Morris D. & Baughman, L. Eugene
System: The UNT Digital Library
Flutter Tests of a 1/25-Scale Model of the B-36J/RF-84F Tip-Coupled Airplane Configuration in the Langley 19-Foot Pressure Tunnel (open access)

Flutter Tests of a 1/25-Scale Model of the B-36J/RF-84F Tip-Coupled Airplane Configuration in the Langley 19-Foot Pressure Tunnel

Report discussing tests of a model of a B-36J/RF-84F tip-coupled airplane to evaluate the flutter characteristics where bomber-body freedoms are allowed and to obtain information about the dynamic stability characteristics. The variables studied were the skew angle of the fighter-bomber coupling, the fighter longitudinal position, the fighter and bomber loading, angle of sideslip, degrees of body freedom, and number of fighters. Flutter was primarily found to occur when the fighter roll frequency was near the natural chordwise-bending frequency of the bomber wing.
Date: January 11, 1956
Creator: Neely, Robert H.
System: The UNT Digital Library
Analysis of Rocket, Ramjet, Turbojet Engines for Supersonic Propulsion of Long-Range Missiles 2:  Rocket Missile Performance (open access)

Analysis of Rocket, Ramjet, Turbojet Engines for Supersonic Propulsion of Long-Range Missiles 2: Rocket Missile Performance

Memorandum presenting an investigation of the theoretical performance of a two-stage ballistic rocket missile with a centerbody and two parallel boosters for JP4-oxygen and ammonia-fluorine propellants. The missile using the ammonia-fluorine propellant weighs about one-half as much as a missile using JP4-oxygen. Results regarding the optimum missile and effect of variation of design parameters are provided.
Date: October 11, 1954
Creator: Huff, Vearl N. & Kerrebrock, Jack
System: The UNT Digital Library
Aerodynamic Heating of Blunt Nose Shapes at Mach Numbers Up to 14 (open access)

Aerodynamic Heating of Blunt Nose Shapes at Mach Numbers Up to 14

From Introduction: "The importance of blunt noses as a means of reducing the heat transfer to high velocity missiles has recently received much publicity. The question of just what blunt shape is best is still moot, and it is the purpose of this paper to present and examine some recent experimental results which may throw some light on this problem."
Date: August 11, 1958
Creator: Stoney, William E., Jr.
System: The UNT Digital Library
Preliminary Results From Free-Jet Tests of a 48-Inch-Diameter Ram-Jet Combustor With an Annular-Piloted Baffle-Type Flameholder (open access)

Preliminary Results From Free-Jet Tests of a 48-Inch-Diameter Ram-Jet Combustor With an Annular-Piloted Baffle-Type Flameholder

"A ram-jet engine with an experimental 48-inch-diameter combustor was investigated in a free-jet facility. The combustor design comprised a large-volume annular pilot region and an array of sloping baffle- or gutter-type flameholders. The combustor was intended to operate at a fuel-air ratio of about 0.037" (p. 1).
Date: May 11, 1955
Creator: Rayle, Warren D.; Smith, Ivan D. & Wentworth, Carl B.
System: The UNT Digital Library
An Investigation of the Low-Speed Stability and Control Characteristics of a 1/10-Scale Model of the McDonnell XF3H-1 Airplane (open access)

An Investigation of the Low-Speed Stability and Control Characteristics of a 1/10-Scale Model of the McDonnell XF3H-1 Airplane

Report presenting an investigation of the low-speed, power-off stability and control characteristics of a model of the McDonnell XF3H-1 airplane. Flight testing occurred in the clean and slat- and flaps-extended conditions over a range of lift coefficients.
Date: October 11, 1951
Creator: Draper, John W.
System: The UNT Digital Library
Drag and Static Stability at Low Lift of Rocket-Powered Models of the Convair MX-1626 Airplane at Mach Numbers From 0.7 to 1.5 (open access)

Drag and Static Stability at Low Lift of Rocket-Powered Models of the Convair MX-1626 Airplane at Mach Numbers From 0.7 to 1.5

Report presenting flight testing on models of the proposed Consolidated Vultee Aircraft Corporation MX-1626 airplane with nacelles and without nacelles. Results regarding drag level, design modifications, dampening, trimming, and the use of ventral boosters are provided.
Date: June 11, 1953
Creator: Hall, James R. & Hopko, Russell N.
System: The UNT Digital Library
Effect of Dissociation on Exhaust-Nozzle Performance (open access)

Effect of Dissociation on Exhaust-Nozzle Performance

Memorandum presenting net jet thrusts for stoichiometric hydrocarbon-air, hydrogen-air and pentaborane-air mixtures for equilibrium and frozen expansion in the exhaust nozzle at flight Mach numbers up to 10. Net jet thrusts for equilibrium flow were three to five times that for frozen flow at Mach 10 for the three fuels cited, a hydrocarbon, hydrogen, and pentaborane. Results regarding dissociation energies, reaction rate, residence time, and estimated minimum performance are provided.
Date: June 11, 1958
Creator: Reynolds, T. W.
System: The UNT Digital Library
Preliminary Results From Free-Jet Tests of a 48-Inch-Diameter Ram-Jet Combustor With an Annular Can-Type Flame Holder (open access)

Preliminary Results From Free-Jet Tests of a 48-Inch-Diameter Ram-Jet Combustor With an Annular Can-Type Flame Holder

Free jet tests of 48 inch diameter ramjet combustor with annular can-type flame holder.
Date: May 11, 1955
Creator: Wentworth, Carl B.; Dobson, Wilbur F. & Rayle, Warren D.
System: The UNT Digital Library
Transonic Free-Flight Investigation of the Longitudinal Aerodynamic Characteristics of a 1/10-Scale Steel-Wing Model of the Northrop MX-775A Missile with Leading-Edge Extensions, Inboard Trailing-Edge Flaps, and a Speed Brake on the Vertical Tail (open access)

Transonic Free-Flight Investigation of the Longitudinal Aerodynamic Characteristics of a 1/10-Scale Steel-Wing Model of the Northrop MX-775A Missile with Leading-Edge Extensions, Inboard Trailing-Edge Flaps, and a Speed Brake on the Vertical Tail

"Results are presented of a free-flight investigation between Mach numbers of 0.7 to 1.3 and Reynolds numbers of 3.1 x 10(exp 6) to 7.0 x 10(exp 6) to determine the longitudinal aerodynamic characteristics of the Northrop MX-775A missile. This missile has a wing, body, and vertical tail, but has no horizontal tail. The basic wing plan form has an aspect ratio of 5.5, 45 deg of sweepback of the 0.406 streamwise chord line, and a taper ratio of 0.4" (p. 1).
Date: February 11, 1955
Creator: Arbic, Richard G.
System: The UNT Digital Library
Wind-Tunnel Investigation of a 1/6-Scale Model of the Bumblebee XPM Missile at High Subsonic Speeds (open access)

Wind-Tunnel Investigation of a 1/6-Scale Model of the Bumblebee XPM Missile at High Subsonic Speeds

Report presenting an investigation of a model of the Bumblebee XPM missile to determine the causes of booster-fin failures for a range of Mach numbers and Reynolds numbers. The cause of fin failure was determined to be the launching shoes that caused the missiles to trim at increasingly negative angles of attack. Additional testing with wing spoilers and alternate booster fins was also conducted.
Date: December 11, 1950
Creator: Nelson, Warren H.
System: The UNT Digital Library
Effect of pressure level on afterburner-wall temperatures (open access)

Effect of pressure level on afterburner-wall temperatures

Report presenting an investigation conducted on a full-scale afterburner and turbojet engine to determine the effect of pressure level on afterburner-wall temperature. For a given ratio of cooling airflow to afterburner gas flow, the afterburner-wall temperature increased as afterburner-outlet pressure was increased. The results indicated that heat transfer by luminous radiation was not significant any pressure level investigated.
Date: June 11, 1958
Creator: Shillito, Thomas B. & Smolak, George R.
System: The UNT Digital Library
Effects of Secondary-Air Flow on Annular Base Force of a Supersonic Airplane (open access)

Effects of Secondary-Air Flow on Annular Base Force of a Supersonic Airplane

Memorandum presenting an investigation of the effect of base bleed on the base force of a supersonic-interceptor model in the 8- by 6-foot supersonic wind tunnel. Generally, base pressures greater than ambient were obtained at the engine operating pressure ratios of the primary nozzle.
Date: October 11, 1954
Creator: Vargo, Donald J.
System: The UNT Digital Library
Experimental Sea-Level Static Investigation of a Short Afterburner (open access)

Experimental Sea-Level Static Investigation of a Short Afterburner

Sea-level static testing of turbojet engine afterburner.
Date: May 11, 1954
Creator: Harp, James L., Jr.; Mallett, William E. & Shillito, Thomas B.
System: The UNT Digital Library