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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 a 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:
April 1958
Creator:
Gates, Ordway B., Jr. & Woodling, C. H.
System:
The UNT Digital Library
Experimental investigation of axial and normal force characteristics of skewed nozzles
Report presenting an investigation of normal forces produced by several skewed nozzles and a series of ejectors with skewed shrouds discharging into quiescent air as conducted with cold air at jet total-pressure ratios up to 6.5. Nozzles were terminated at angles of 30 degrees, 45 degrees, 60 degrees, and 75 degrees relative to the normal plane. Results regarding basic data, effect of skew angle and indentation, and effect of a skewed shroud are provided.
Date:
September 1958
Creator:
Carter, David J., Jr. & Vick, Allen R.
System:
The UNT Digital Library
Measurements in a Shock Tube of Heat-Transfer Rates at the Stagnation Point of a 1.0-Inch-Diameter Sphere for Real-Gas Temperatures Up to 7,900 R
Note presenting heat-transfer rates at the stagnation point of 1.0-inch-diameter glass spherical models in shock-tube flows in air which correspond to free-flight conditions between Mach numbers of 6.4 and 13.9 with stagnation temperatures up to 7900 degrees R. The heat-transfer rates were determined from measurements of the surface-temperature change with time of a thin-film-platinum resistance thermometer.
Date:
August 1958
Creator:
Sabol, Alexander P.
System:
The UNT Digital Library
Design and experimental evaluation of a light-weight turbine-wheel assembly
Report presenting lightweight design concepts, which were developed and tested in a full-scale turbine wheel with a tip diameter of 34.3 inches and a tip speed of 1190 feet per second. It consisted of a rotor of two thin alloy disks attached with spacers and bolts and hollow turbine blades. Testing indicated that it would be particularly applicable to an expendable missile engine.
Date:
June 1957
Creator:
Morgan, W. C. & Kemp, R. H.
System:
The UNT Digital Library
An investigation of some phenomena relating to aural detection of airplanes
Report presenting an investigation to determine the effect of modifications made in the propulsion system of a single-engine airplane to substantially reduce its external noise, and, thereby, to evaluate the significance of the external noise level of an airplane with regard to the problem of its detection by ground observers.
Date:
September 1958
Creator:
Hubbard, Harvey H. & Maglieri, Domenic J.
System:
The UNT Digital Library
Effect of the proximity of the wing first-bending frequency and the short-period frequency on the airplane dynamic-response factor
Report presenting a study of the effect of the frequency of the lowest wing structural mode on the airplane center-of-gravity dynamic-response factor was made my employing simplified transfer functions.
Date:
June 1958
Creator:
Huss, Carl R. & Donegan, James J.
System:
The UNT Digital Library
Graphs of reduced variables for computing histories of vaporizing fuel drops, and drop histories under pressure
Report presenting an investigation with two purposes: to obtain a simplified calculation technique for replacing complicated automatic computer calculations and to obtain experimental data for single droplets vaporizing at pressures greater than 1 atmosphere and to check the histories against experimental data.
Date:
September 1958
Creator:
Borman, G. L.; El Wakil, M. M.; Uyehara, O. A. & Myers, P. S.
System:
The UNT Digital Library
An experimental investigation of wake effects on hydro-skis
Report presenting an experimental investigation to determine the effects of planing in a wake on the forces of a planing surface and to locate desirable positions in the wake with regard to the lift and lift-drag ratio of the planing surface. Two combinations of hydro-skis were tested: one with two in tandem and one with three arranged with one hydro-ski in the front and two in the back. Results indicated that the rear hydro-ski in tandem arrangement could have large increases in lift coefficient and small improvements in lift-drag ratio compared with the regular configuration.
Date:
May 1958
Creator:
McBride, Ellis E. & Fisher, Lloyd J.
System:
The UNT Digital Library
Low tip Mach number stall characteristics and high tip Mach number compressibility effects on a helicopter rotor having an NACA 0009 tip airfoil section
Report presenting an investigation conducted on the helicopter test tower to determine experimentally the low tip Mach number stall and high tip Mach number drag divergence characteristics of a helicopter rotor with an NACA 0009 tip airfoil section. Results regarding rotor hovering performance, rotor-blade pitching moments, rotor profile-drag torque, and a comparison with two-dimensional drag-divergence data are provided.
Date:
July 1958
Creator:
Powell, Robert D., Jr. & Carpenter, Paul J.
System:
The UNT Digital Library
Hydrodynamic Impact Loads of a -20 Degree Dead-Rise Inverted-V Model and Comparisons With Loads of a Flat-Bottom Model
Note presenting a model with an inverted-V transverse shape and a dead-rise angle of -20 degrees as part of a study of hydrodynamic impact loads on chine-immersed bodies. A series of fixed-trim impacts of the inverted-V model were made in smooth water over a wide range of trim and initial flight-path angles at a beam-loading coefficient of 19.15 with a few impacts at beam-loading coefficients of 27.90 and 36.07. The data are presented in tables and in figures as variations of loads and motions (in coefficient form) with time, trim angle, and flight-path angle.
Date:
August 1958
Creator:
Edge, Philip M., Jr.
System:
The UNT Digital Library
Stresses in and general instability of monocoque cylinders with cutouts 2: calculation of the stresses in a cylinder with a symmetric cutout
A numerical procedure is presented for the calculation of the stresses in a monocoque cylinder with a cutout. In the procedure the structure is broken up into a great many units; the forces in these units corresponding to specified distortions of the units are calculated; a set of linear equations is established expressing the equilibrium conditions of the units in the distorted state; and the simultaneous linear equations are solved. A fully worked out numerical example, corresponding to the application of a pure bending moment, gave results in good agreement with experiments carried out earlier at the Polytechnic Institute of Brooklyn.
Date:
June 1946
Creator:
Hoff, N. J.; Boley, Bruno A. & Klein, Bertram
System:
The UNT Digital Library
Measurements of Aerodynamic Forces and Moments at Subsonic Speeds on a Simplified T-Tail Oscillating in Yaw About the Fin Midchord
Report presenting some experimental measurements of aerodynamic forces and moments on a simple T-tail configuration oscillating in yaw about an axis through the midchord of the vertical fin. Coefficients regarding the rolling moment of the horizontal stabilizer, rolling moment, yawing moment, and side force of the tail are provided.
Date:
September 1958
Creator:
Clevenson, Sherman A. & Leadbetter, Sumner A.
System:
The UNT Digital Library
Wind-tunnel investigation of the high-subsonic static longitudinal stability characteristics of several wing-body configurations designed for high lift-drag ratios at a Mach number of 1.4
Report presenting testing in the high-speed 7- by 10-foot tunnel to investigate the high-subsonic static longitudinal stability characteristics and lift-drag ratios of several wing-body models designed to provide high lift-drag ratios at Mach number 1.4. The basic configuration had a thin highly swept wing of aspect ratio 2.91 with NACA 65-A series airfoil sections. Results regarding longitudinal stability, lift, drag, and lift-drag ratio are provided.
Date:
July 1958
Creator:
Fournier, Paul G.
System:
The UNT Digital Library
Flight Investigation of Effects of Retreating-Blade Stall on Bending and Torsional Moments Encountered by a Helicopter Rotor Blade
Note presenting flight tests conducted with a medium-size single-rotor helicopter, one blade of which was equipped with strain gages, to determine the effects of retreating-blade stall on the rotor blade bending and torsional moments during high-speed flight and pull-up maneuvers. The results indicate that retreating-blade stall has a substantial effect on the periodic rotor blade moments. Results regarding the effect of stall in steady forward flight and effect of stall in pull-up maneuvers are provided.
Date:
May 1958
Creator:
Ludi, LeRoy H.
System:
The UNT Digital Library
Tests of Ring-Stiffened Circular Cylinders Subjected to a Transverse Shear Load
"Thirty-four circular cylinders stiffened by heavy rings were loaded to failure in combined bending and shear with a transverse shear load. The results are presented in the form of an interaction curve which is applicable to the design of ring-stiffened cylinders that fail as a result of local buckling" (p. 1).
Date:
September 1958
Creator:
Peterson, James P. & Updegraff, Richard G.
System:
The UNT Digital Library
Effects of Thermal Relaxation and Specific-Heat Changes on Measurements With a Pneumatic-Probe Pyrometer
"Equations are derived which evaluate the effects of thermal vibrational relaxation and specific-heat changes on pneumatic-probe pyrometer measurements in the region 1000 to 3000 degrees K and Mach numbers between 0.3 and 2.0. Examples are given for typical probes in two combustion mixtures" (p. 1).
Date:
July 1957
Creator:
Kuhns, P. W.
System:
The UNT Digital Library
Low-speed experimental determination of the effects of leading-edge radius and profile thickness on static and oscillatory lateral stability derivatives for a delta wing with 60 degrees of leading-edge sweep
Report presenting an investigation to determine the effects of leading-edge radius and profile thickness on the oscillatory lateral stability derivatives for a series of delta wings with 60 degrees of leading-edge sweep. The wings were oscillated in yaw about their vertical axes. Results indicated that there were noticeable decreases in all the derivatives due to increase in leading-edge radius at angles of attack above approximately 12 degrees.
Date:
July 1958
Creator:
Fletcher, Herman S.
System:
The UNT Digital Library
Flight Measurements of the Vibratory Bending and Torsional Stresses on a Modified Supersonic Propeller for Forward Mach Numbers up to 0.95
Note presenting vibratory stress measurements obtained in flight on a modified supersonic propeller for forward mach numbers up to 0.95. The magnitude of the vibratory bending stress was low in relation to the strength of the material throughout the flight range of the airplane. Results of a propeller feathering operation at a Mach number of 0.95 indicated no excessive stresses.
Date:
June 1958
Creator:
O'Bryan, Thomas C.
System:
The UNT Digital Library
Effects of Propeller Position and Overlap on the Slipstream Deflection Characteristics of a Wing-Propeller Configuration Equipped With a Sliding and Fowler Flap
Report of an investigation in a static-test facility to determine some of the effects of propeller position and overlap on the slipstream deflection characteristics of a configuration equipped with a sliding and Fowler flap. An investigation of a leading-edge slat, nacelle size, flap segmentation, and number of propellers was also conducted. Results regarding the effect of number of propellers, effect of vertical position of propeller, effect of extending nacelles through flaps, effect of chordwise position of the propellers, effect of propeller overlap, effect of position and deflection of a leading-edge slat, propeller static-thrust efficiency in ground effect, and effect of nacelle size are provided.
Date:
September 1958
Creator:
Hayes, William C., Jr.; Kuhn, Richard E. & Sherman, Irving R.
System:
The UNT Digital Library
Wind-tunnel investigation at low speeds of flight characteristics of a sweptback-wing jet-transport airplane model equipped with an external-flow jet-augmented slotted flap
Report presenting a wind-tunnel investigation at low speeds to determine the flight characteristics of a model of a sweptback-wing jet-transport airplane equipped with an external-flow jet-augmented slotted flap. Results regarding the longitudinal stability characteristics, longitudinal control characteristics, lateral stability characteristics, and lateral control characteristics are provided.
Date:
July 1958
Creator:
Johnson, Joseph L., Jr.
System:
The UNT Digital Library
A comparison of two methods for calculating transient temperatures for thick walls
Report presenting a comparison of two different methods of calculating transient temperatures for thick walls with arbitrary variation of heat-transfer coefficient and adiabatic-wall temperature.
Date:
August 1958
Creator:
Buglia, James J. & Brinkworth, Helen
System:
The UNT Digital Library
Application of obliquely mounted strain gage to measurement of residual stresses in disks
Report presenting a method by which the residual stress distribution in a disk can be determined with the aid of the obliquely mounted strain gage when the directions of the principal stresses are radial and tangential. The strain gages are mounted in such a way as to make them sensitive only to the tangential stresses in the disk. Results regarding cutting procedure, accuracy of the method, and an independent check of the method are required.
Date:
September 1957
Creator:
Hirschberg, M. H.; Kemp, R. H. & Manson, S. S.
System:
The UNT Digital Library
Water-Impact Theory for Aircraft Equipped With Nontrimming Hydro-Skis Mounted on Shock Struts
Note presenting theoretical equations derived for the motion of aircraft equipped with hydro-skis mounted on shock struts during take-off and landing operations on a water surface. Two hydrodynamic force relations, one more accurate but more complex than the other, are considered.
Date:
September 1958
Creator:
Schnitzer, Emanuel
System:
The UNT Digital Library
Performance at low speeds of compressor rotors having low-cambered NACA 65-series blades with high inlet angles and low solities
Report presenting three compressor rotors with low-cambered 6-percent-thick NACA 65-series blade sections tested at low speeds. The tests were made at three solidities, without guide vanes or stators, over ranges of blade-setting angles and quantity-flow rates. Results regarding the efficiency and pressure-rise coefficients, variation of section turning angle with angle of attack, comparison between low-speed rotor and cascade turning angles, and carpet pots are provided.
Date:
August 1958
Creator:
Emery, James C. & Howard, Paul W.
System:
The UNT Digital Library