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Comparison of the performance of a helicopter-type ram-jet engine under various centrifugal loadings
Report presenting an investigation of an 18-foot-radius helicopter rotor powered by tip-mounted ramjet engines in the helicopter test tower. The engine performance is compared with the performance determined in a previous investigation of a 9-foot-radius rotor with the same engines at similar speeds but with twice the centrifugal forces. Results regarding the propulsive characteristics, minimum specific fuel consumption and corresponding propulsive thrust, and operational characteristics are provided.
Date:
October 7, 1953
Creator:
Radin, Edward J. & Carpenter, Paul J.
System:
The UNT Digital Library
Rocket-Model Investigation to Determine the Hinge-Moment and Normal-Force Properties of a Full-Span, Constant-Chord, Partially Balanced Trailing-Edge Control on a 60 Degree Clipped Delta Wing Between Mach Numbers of 0.50 and 1.26
Report presenting a free-flight investigation of a rocket-powered research model to determine the hinge-moment and normal-force characteristics of a trailing-edge control on a delta wing between Mach numbers of 0.50 and 1.26. The hinge-line location of 40 percent control chord satisfactorily reduced the high hinge moments associated with plain flap-type controls. Results regarding hinge moments and normal force are provided.
Date:
October 30, 1953
Creator:
Martz, C. William & Goslee, John W.
System:
The UNT Digital Library
A pressure-distribution investigation of a fineness-ratio-12.2 parabolic body of revolution (NACA RM-10) at M = 1.59 and angles of attack up to 36 degrees
Report presenting a pressure-distribution investigation of a parabolic body of revolution with a fineness ratio of 12.2, which was performed in the 4- by 4-foot supersonic tunnel at Mach number 1.59 and Reynolds number 3.6 x 10(sub 6), based on body length, for a range of angles of attack. Results regarding basic pressures, aerodynamic coefficients, asymmetrical pressures, comparison of experimental and theoretical pressures, artificial roughness, section coefficients, and body coefficients are provided.
Date:
October 30, 1952
Creator:
Cooper, Morton; Gapcynski, John P. & Hasel, Lowell E.
System:
The UNT Digital Library
Heat-Exchanger-Core Weights for Use With Hydrogen-Expansion Turbine
Memorandum presenting an analysis of probable heat-exchanger weights for stationary and rotary regenerator heat exchangers for use in a hydrogen-expansion turbine engine. This is because rotary regenerators offer possibilities for a considerably lighter heat-exchanger core, possibly one-fourth that of the stationary regenerators.
Date:
October 3, 1957
Creator:
Reynolds, Thaine W.
System:
The UNT Digital Library
Simulator studies of a simple homing system
Report presenting simulator studies of a homing missile pursuing a constant-velocity nonmaneuvering target. The missile dynamics in pitch and roll, seeker method of deflection and control, and the missile-target geometry were simulated to determine whether the method of control and detection in conjunction with the missile dynamics were feasible.
Date:
October 6, 1955
Creator:
Passera, Anthony L. & Garner, H. Douglas
System:
The UNT Digital Library
An Experimental Investigation of the Flow Phenomena Over Bodies at High Angles of Attack at a Mach Number of 2.01
Report presenting an investigation in the supersonic pressure tunnel at Mach number 2.01 to study the wake patterns in the lee of bodies at high angles of attack. The configurations tested consisted of two cylindrical body shapes, one circular and one elliptical in cross section, with a fineness-ratio-3.5 ogival nose and a fineness-ratio-6 conical nose. Results regarding vapor-screen photographs, wake characteristics, wake patterns, wake characteristics, and testing with transition strips are included.
Date:
October 27, 1955
Creator:
Gapcynski, John P.
System:
The UNT Digital Library
Statistical measurements of landing contact conditions of the Boeing B-47 airplane
Report presenting a determination of the landing contact conditions of the Boeing B-47 airplane using a specially built motion picture camera. A statistical analysis of the sinking speeds and horizontal speeds was carried out on the photographs.
Date:
October 27, 1955
Creator:
Kolnick, Joseph J. & Morris, Garland J.
System:
The UNT Digital Library
Modified tubular combustor as high-temperature gas generators
A pair of combustors and transition liners in a quarter-annular, direct-connect assembly was operated at temperatures up to 2400 degrees F to determine the feasibility of using production-type combustor systems as high-tmeperature gas generators for turbine-cooling studies. Operation at high temperatures for 32 hours was possible when minor liner modifications were made that provided greater cooling-air flow between the turbine casing and interior components.
Date:
October 21, 1955
Creator:
Friedman, Robert & Zettle, Eugene V.
System:
The UNT Digital Library
Drag and rolling-moment effectiveness of trailing-edge spoilers at Mach numbers 2.2 and 5.0
Report presenting free-flight measurements of the rolling effectiveness and drag of trailing-edge spoilers on low-aspect-ratio wings with both laminar and turbulent boundary layers at two different Mach numbers. The effect of a spoiler deflected from the surface of a wing is to cause boundary-layer separation upstream.
Date:
October 3, 1955
Creator:
Canning, Thomas N. & DeRose, Charles E.
System:
The UNT Digital Library
Free-flight investigation to obtain drag-at-lift and stability data for a 60 degree delta-wing-body configuration over a Mach number range of 1.3 to 1.6
Report presenting flight tests using a rocket-propelled 60 degree delta-wing body configuration, which included a NACA 0003-63 wing airfoil section. Drag at lift and stability data were obtained for a range of Mach numbers.
Date:
October 6, 1955
Creator:
Welsh, Clement J.
System:
The UNT Digital Library
Flight measurements of directional stability to a Mach number of 1.48 for an airplane tested with three different vertical tail configurations
Report presenting flight tests to measure the directional stability of a fighter-type airplane over a range of Mach numbers. Testing occurred at two altitudes and used three vertical tails of varying aspect ratio or area.
Date:
October 7, 1955
Creator:
Drake, Hubert M.; Finch, Thomas W. & Peele, James R.
System:
The UNT Digital Library
Wind-Tunnel Investigation of the Static Longitudinal and Lateral Stability of the Bell X-1A at Supersonic Speeds
"An investigation to determine the static longitudinal and lateral stability characteristics of a 1/62-scale model of the Bell X-1A has been conducted in the Langley 9-inch supersonic tunnel. tests were made at Mach numbers of 1.62, 1.94, 2.22, 2.40, and 2.62 on the wing-body, wing-body-vertical-tail, and complete configurations. Data are presented for both the body and stability axes. Detailed analysis of the test results is omitted" (p. 1).
Date:
October 27, 1955
Creator:
Henderson, Arthur, Jr.
System:
The UNT Digital Library
Temperature Recovery Factors on a Slender 12 Degree Cone-Cylinder at Mach Numbers From 3.0 to 6.3 and Angles of Attack Up to 45 Degrees
Report presenting measurements of recovery temperatures on a slender cone-cylinder with a 12 degree vertex angle and a 1.25-inch-diameter cylinder for a range of Mach numbers. Results regarding the visual evidence, temperature distributions, pressure distributions, summary figures, correlation of temperature patterns with boundary-layer transition and separation, and recovery factors are provided.
Date:
October 3, 1955
Creator:
Reller, John O. & Hamaker, Frank M.
System:
The UNT Digital Library
Investigation of a Three-Stage Transonic Research Axial-Flow Compressor: Aerodynamic Design and Overall Performance
Report discussing an investigation of the performance of a three-stage transonic compressor with high stage pressure ratios to investigate problems encountered when high-pressure-ratio transonic stages are grouped together to form a multistage compressor. Results are presented regarding overall performance in Freon, stage performance, and radial variation in overall stagnation pressure ratio.
Date:
October 27, 1955
Creator:
Savage, Melvyn & Beatty, Loren A.
System:
The UNT Digital Library
A theoretical analysis of the effect of engine angular momentum on longitudinal and directional stability in steady rolling maneuvers
From Summary: "The effect of engine momentum on the longitudinal and directional stability of aircraft in steady rolling maneuvers has been investigated. The results presented indicate that the gyroscopic moments produced on the aircraft by rotating engine in rolling maneuvers can have an appreciable effect on the range of rolling velocities for which longitudinal or directional instability might occur."
Date:
October 7, 1955
Creator:
Gates, Ordway B., Jr. & Woodling, C. H.
System:
The UNT Digital Library
Calculated Heats of Formation and Combustion of Boron Compounds (Boron, Hydrogen, Carbon, Silicon)
Memorandum presenting the calculation of the heats of formation and combustion for liquid and gaseous alkyl- and silyl-substituted boron compounds by a semitheoretical method. The results indicated that alkylation and more especially silylation reduce the heat of combustion. Results regarding alkyl- and silyldecaboranes, diborylmethane, diborylethane, and their alkyl derivatives, bipentaboranyl and bideocaboranyl, dipentaboranyl- and didecaboranylalkanes, and heats of combustion of isomers are provided.
Date:
October 4, 1955
Creator:
Altshuller, Aubrey P.
System:
The UNT Digital Library
A Theoretical Analysis of a Simple Aerodynamic Device to Improve the Longitudinal Damping of a Cruciform Missile Configuration at Supersonic Speeds
Memorandum presenting a theoretical analysis of a cruciform missile configuration equipped with floating controls to determine if such controls can be utilized to improve the airframe transient response characteristics.The investigation covers either forward or aft locations of the floating controls at supersonic speeds. The results indicate that a substantial increase in airframe damping can be obtained through a proper selection of hinge-moment coefficients and through the use of a fixed-rate viscous damper attached to the floating-control surfaces.
Date:
October 27, 1955
Creator:
Clements, James E.
System:
The UNT Digital Library
Flight measurements of the vertical-tail loads on the Convair XF-92A delta-wing airplane
Report presenting the aerodynamic loads acting over the vertical tail, which were determined during an investigation of the lateral stability and control characteristics of the Convair XF-92A. Results regarding the vertical-tail panel characteristics, vertical-tail load parameters, and vertical-tail bending and normal-force coefficients are provided.
Date:
October 27, 1955
Creator:
Johnson, Clinton T.
System:
The UNT Digital Library
The Effect of Wing Profile on the Transonic Characteristics of Rectangular and Triangular Wings Having Aspect Ratios of 3: Transonic Bump Technique
Report presenting an investigation to determine the effect of wing profile on the transonic aerodynamic characteristics of rectangular and triangular wings with aspect ratios of 3. Five wings were compared over a range of Mach and Reynolds number. Results regarding the rectangular and triangular wings and use of transonic area rule are provided.
Date:
October 27, 1954
Creator:
Nelson, Warren H. & Frank, Joseph L.
System:
The UNT Digital Library
Effects of angle of attack and airfoil profile on the two-dimensional flutter derivatives for airfoils oscillating in pitch at high subsonic speeds
Report presenting two-dimensional aerodynamic lift and moment flutter derivatives for moderate and high angles of attack for several airfoil profiles varying in thickness and thickness distribution. The results indicate that the variables angle of attack, airfoil profile, reduced frequency, and Mach number all have significant interdependent effects.
Date:
October 15, 1954
Creator:
Wyss, John A. & Herrera, Raymond
System:
The UNT Digital Library
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
Investigation of the NACA 4-(5)(05)-037 six- and eight-blade, dual-rotation propellers at positive and negative thrust at Mach numbers up to 0.90, including some aerodynamic characteristics of the NACA 4-(5)(05)-041 two- and four-blade, single-rotat
Report presenting an investigation to determine the aerodynamic characteristics of the NACA 4-(5)(05)-037 six- and eight-blade, dual-rotation propellers operating at positive and negative thrust at a range of Mach numbers when operating at near static conditions. The propellers were operated in combination with a long spinner and at a variety of blade angles.
Date:
October 8, 1954
Creator:
Walker, John H. & Reynolds, Robert M.
System:
The UNT Digital Library
Analytical Study of the Effect of Center-of-Gravity Position on the Response to Longitudinal Control in Landing Approaches of a Swept-Wing Airplane of Low Aspect Ratio Having No Horizontal Tail
Report presenting an investigation of the effect of reducing the static stability by a practical center-of-gravity shift in swept-wing airplanes of low aspect ratio with no horizontal tail. Results regarding relocating the center of gravity, the effect of lift due to elevator deflection, the effect of increased total elevator effectiveness, and the effect of response characteristics over long time periods are provided.
Date:
October 15, 1954
Creator:
Stone, Ralph W., Jr.
System:
The UNT Digital Library
Wind pressure distributions at low lift for the XF-92A delta-wing airplane at transonic speeds
Report presenting chordwise pressure distributions measured over the left wing of a Convair XF-92A delta-wing airplane at low lift to determine the effect of Mach number on the wing characteristics at transonic speeds. The critical Mach number of the basic wing was 0.83 for an airplane normal-force coefficient at 0.09. The spanwise load distributions were roughly triangular in shape.
Date:
October 20, 1954
Creator:
Keener, Earl R.
System:
The UNT Digital Library