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Degree Department
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Year
Month
Language
Investigation of Effect of Sideslip on Lateral Stability Characteristics 3: Rectangular Low Wing on Circular Fuselage With Variations in Vertical-Tail Area and Fuselage Length With and Without Horizontal Tail Surface
Report presenting power-off tests made in the 6- by 6-foot test section of the stability tunnel to determine the variation of the static lateral stability characteristics with vertical-tail area, fuselage length, and wing dihedral. The results are presented as curves showing the variation of the static-lateral-stability slopes with angle of attack, and the rolling-moment, yawing-moment, and lateral-force coefficients with angle of yaw.
Date:
August 1945
Creator:
Hollingworth, Thomas A.
Object Type:
Report
System:
The UNT Digital Library
Stability and Control Characteristics of a Fighter Airplane in Inverted Flight Attitude as Determined by Model Tests
Report discuss the results of force tests, yaw-trim tests, and power-off tests to compare the stability and control characteristics of a powered airplane model in the erect and inverted flight attitudes. Due to the violent and uncontrollable maneuvers that sometimes occur after flight in the inverted attitude, more information was requested about stability and control characteristics in this position. Testing found that with the power on, a serious reduction in longitudinal and directional stability occurred in inverted flight.
Date:
August 1945
Creator:
Paulson, John W. & Bennett, Charles V.
Object Type:
Report
System:
The UNT Digital Library
Charts for the Minimum-Weight Design of 24S-T Aluminum-Alloy Flat Compression Panels With Longitudinal Z-Section Stiffeners
Report presenting design charts for 24S-T aluminum-alloy flat compression panels with longitudinal Z-section stiffeners. It was found that maximum possible structural efficiency with these panels requires closer stiffener spacings than those now in common use.
Date:
August 1945
Creator:
Schuette, Evan H.
Object Type:
Report
System:
The UNT Digital Library
A Comparison of Data Obtained by Two Flight Techniques for Determining the Sideslip Characteristics of a Fighter Airplane
Report discusses data obtained from measuring sideslip characteristics via the continuous-record method and the steady-record method. The situations in which each recording method is preferred are presented.
Date:
August 1945
Creator:
Johnson, Harold I.
Object Type:
Report
System:
The UNT Digital Library
Comparative drag measurements at transonic speeds of rectangular sweptback NACA 65-009 airfoils mounted on a freely falling body
From Summary: "Directly comparable drag measurements have been made of an airfoil with a conventional rectangular plan form and an airfoil with a sweptback plan form mounted on freely falling bodies. Both airfoils had NACA 65-009 sections and were identical in span, frontal area, and chord perpendicular to the leading edge. The sweptback plan form incorporated a sweepback angle of 45 degrees. The data obtained have been used to establish the relation between the airfoil drag coefficients and the free-stream Mach number over a range of Mach numbers from 0.90 to 1.27. The results of the measurements indicate that the drag of the sweptback plan form is less than 0.3 that of the rectangular plan form at a Mach number of 1.00 and is less than 0.4 that at a Mach number of 1.20."
Date:
August 9, 1945
Creator:
Mathews, Charles W. & Thompson, Jim Rogers
Object Type:
Report
System:
The UNT Digital Library
Air-flow and performance characteristics of the engine-stage supercharger of a double-row radial aircraft engine I: effect of operating variables
From Introduction: "The tests reported herein, conducted during the early part of 1945, were made to determine the inherent charge-air distribution characteristics of the engine-stage supercharger of the double-row radial engine."
Date:
August 1945
Creator:
Mesrobian, John M.
Object Type:
Report
System:
The UNT Digital Library
Standard Procedures for Rating and Testing Centrifugal Compressors
Report on the NACA test-rig installation, measurements, instrumentation, test procedure, methods of calculation, and presentation of data for rating and testing centrifugal superchargers. Special precautions for certain portions of testing are also provided.
Date:
August 1945
Creator:
NACA Subcommittee on Supercharger Compressors
Object Type:
Report
System:
The UNT Digital Library
Piston-Ring Vibration and Breakage
Report presenting testing to determine the stresses and bending moments required to break pieces 1 inch or less in length from the ends of cast-iron, keystone, compression piston rings. Strain gages were used to determine the stress pattern for various modes of vibration. The maximum-stress points of vibrating piston rings were at the antinodes or points of maximum deflection.
Date:
August 1945
Creator:
Nettles, J. C. & Meyer, André J., Jr.
Object Type:
Report
System:
The UNT Digital Library
Standard Method of Graphical Presentation of Centrifugal Compressor Performance
Report on the NACA recommended method for comparing the performance of centrifugal compressors. The most important indices of compressor performance are the adiabatic temperature rise ratio or adiabatic efficiency, the adiabatic shaft efficiency, and the pressure ratio, which incorporate many other parameters. Recommendations for reporting on compressor effectiveness and characteristics are provided.
Date:
August 1945
Creator:
NACA Subcommittee on Supercharger Compressors
Object Type:
Report
System:
The UNT Digital Library
A method of analysis of V-G records from transport operations
A method has been developed for interpreting v-g records taken during the course of commercial transport operation. This method involves the utilization of fairly simple statistical procedures to obtain "flight envelopes," which predict that, on the average, in a stated number of flight hours, one value of airspeed will exceed the envelope, and one positive and one negative acceleration increment will exceed the envelope with equal probability of being experienced at any airspeed. Comparison with the actual data obtained from various airplanes and from various airlines indicates that these envelopes predict the occurrences of large values of acceleration and airspeed with a high degree of accuracy.
Date:
August 31, 1945
Creator:
Peiser, A. M. & Wilkerson, M.
Object Type:
Report
System:
The UNT Digital Library
Analysis and modification of theory for impact of seaplanes on water
From Summary: "An analysis of available theory on seaplane impact and a proposed modification thereto are presented. In previous methods the overall momentum of the float and virtual mass has been assumed to remain constant during the impact but the present analysis shows that this assumption is rigorously correct only when the resultant velocity of the float is normal to the keel."
Date:
August 20, 1945
Creator:
Mayo, Wilbur L.
Object Type:
Report
System:
The UNT Digital Library
A visual photographic study of cylinder lubrication
From Summary: "A V-type engine provided with a glass cylinder was used to study visually the lubrication characteristics of an aircraft-type piston. Photographs and data were obtained with the engine motored at engine speeds up to 1000 r.p.m. and constant cylinder-head pressures of 0 and 50 pounds per square inch. A study was made of the orientation of the piston under various operating conditions, which indicated that the piston was inclined with the crown nearest the major-thrust cylinder face throughout the greater part of the cycle. The piston moved laterally in the cylinder under the influence of piston side thrust."
Date:
August 1, 1945
Creator:
Shaw, Milton C. & Nussdorfer, Theodore
Object Type:
Report
System:
The UNT Digital Library
Some Effects of Compressibility on the Flow Through Fans and Turbines
"The laws of conservation of mass, momentum, and energy are applied to the compressible flow through a two-dimensional cascade of airfoils. A fundamental relation between the ultimate upstream and downstream flow angles, the inlet Mach number, and the pressure ratio across the cascade is derived. Comparison with the corresponding relation for incompressible flow shows large differences. The fundamental relation reveals two ranges of flow angles and inlet Mach numbers, for which no ideal pressure ratio exists" (p. 123).
Date:
August 1, 1945
Creator:
Perl, W. & Epstein, H. T.
Object Type:
Report
System:
The UNT Digital Library
Operating stresses in aircraft-engine crankshafts and connecting rods 2: instrumentation and test results
Report presenting an investigation to develop methods and equipment for the measurement of operating stresses in aircraft-engine crankshafts and connecting rods. The results indicate that the measurement of stresses in connecting rods is feasible. Results regarding stresses in the crankshaft and stresses in the master connecting rod are provided.
Date:
August 1945
Creator:
Dutee, Francis J.; Phillips, Franklyn W. & Calvert, Howard F.
Object Type:
Report
System:
The UNT Digital Library
Elimination of Galling of Pendulum-Vibration Dampers Used in Aircraft Engines
Report presenting an analysis of the contact stresses in a damper installation of an aircraft engine that indicated that galling could be eliminated by increasing the diameters of damper pins and holes. Torsional-vibration pendulum dampers have been successful in minimizing vibrations at critical speeds in aircraft engines, but serious wearing problems are often encountered when using them. The damper used in this experiment did not suffer any type of damage after many hours of use.
Date:
August 1945
Creator:
Meyer, André J., Jr.
Object Type:
Report
System:
The UNT Digital Library
Determination of Air-Consumption Parameters for Two Radial Aircraft Engines
"Air-consumption data from calibrations of two radial aircraft engines were analyzed to show the relation of engine air consumption to its primary influencing factors: intake-manifold pressure, exhaust back pressure, intake-manifold temperature, and engine speed. The analysis of the test data from these two engines led to the establishment of a relation of variables upon which the design of automatic metering controls can be based. The data obtained from one engine indicate that the air-consumption correlation obtained for this engine is accurate within 2 percent except under certain conditions that are well outside current engine-operation limits" (p. 1).
Date:
August 1945
Creator:
Shames, Sidney J. & Howes, William
Object Type:
Report
System:
The UNT Digital Library
Charts for Helicopter-Performance Estimation
Report presenting charts relating helicopter aerodynamic design variables to performance in steady powered flight. The flight conditions covered are hovering, climb, and horizontal flight. The use of the charts is illustrated by numerical examples in order that computations can be made for particular problems.
Date:
August 1945
Creator:
Talkin, Herbert W.
Object Type:
Report
System:
The UNT Digital Library
Comparisons of Methods of Computing Bending Moments in Helicopter Rotor Blades in the Plane of Flapping
Report presenting several methods of computing bending moments in helicopter rotor blades in the plane of flapping, and the results of a numerical example analyzed by four different methods are compared. The effect of computed bending moments of the tip-loss correction introduced by Wheatley is also considered.
Date:
August 1945
Creator:
Duberg, John E. & Luecker, Arthur R.
Object Type:
Report
System:
The UNT Digital Library
Comparative Fatigue Tests of Riveted Joints of Alclad 24S-T, Alclad 24S-T81, Alclad 24S-RT, Alclad 24S-T86 and Alclad 75S-T Sheet
Report discusses testing performed to determine the fatigue strength of various types of riveted and spot-welded joints in the following aluminum alloys: Alclad 24S-T, 24S-RT, 758-T, 24S-T81, and 24S-T86. Details of the experiment, tensile properties, and information about failure are provided.
Date:
August 1945
Creator:
Moore, R. L. & Hill, H. N.
Object Type:
Report
System:
The UNT Digital Library
Correlation of Wind-Tunnel Predictions With Flight Tests of a Twin-Engine Patrol Airplane 2: Lateral- and Directional-Stability and Control Characteristics
"The lateral- and directional-stability and -control characteristics of a twin-engine patrol airplane as predicted from the results of wind-tunnel tests of a powered model and as measured in flight are compared in this report. The predictions from wind-tunnel-test data were in good agreement with the flight-test results. The results show that such predicted flying-qualities characteristics are sufficiently accurate to indicate the unsatisfactory lateral- and directional-stability and -control characteristics of airplanes in the preliminary design stage" (p. 1).
Date:
August 30, 1945
Creator:
Delany, Noel K. & Kauffman, William M.
Object Type:
Report
System:
The UNT Digital Library
Comparison of wind-tunnel and flight measurements of stability and control characteristics of a Douglas A-26 airplane
From Summary: "Stability and control characteristics determined from tests in the Langley 19-foot pressure tunnel of a 0.2375-scale model of the Douglas XA-26 airplane are compared with those measured in flight tests of a Douglas A-26 airplane. Agreement regarding static longitudinal stability as indicated by the elevator-fixed neutral points and by the variation of elevator deflection in both straight and turning flight was found to be good except at speeds approaching the stall. At these low speeds the airplane possessed noticeably improved stability, which was attributed to pronounced stalling at the root of the production wing."
Date:
August 11, 1945
Creator:
Kayten, Gerald G. & Koven, William
Object Type:
Report
System:
The UNT Digital Library
Lifting-Surface-Theory Values of the Damping in Roll and of the Parameter Used in Estimating Aileron Stick Forces
Report presenting an investigation by lifting-surface theory of a thin elliptic wing of aspect ratio 6 in a steady roll by means of the electromagnetic-analogy method. The results obtained by lifting-surface theory indicate that the damping in roll for a wing of aspect ratio of 6 is 13 percent less than that give by lifting-line theory and 5 percent less than that given by lifting-line theory with the edge-velocity correction derived by Robert T. Jones applied. Simple practical methods of applying the results of the investigation to wings of other plan forms are given.
Date:
August 1945
Creator:
Swanson, Robert S. & Priddy, E. LaVerne
Object Type:
Report
System:
The UNT Digital Library
Longitudinal-Trim Tests of a 0.059-Scale Model of the Curtiss-Wright XP-55 Airplane
Report discussing tests of a model of the XP-55 to determine which modifications would prevent trim at large positive and negative angles of attack. The model was found to not trim at flat attitudes if the large wing tips with an extension of the wing-tip trimmers and a large elevator are installed on the airplane.
Date:
August 1945
Creator:
MacDougall, George F., Jr. & Schneiter, Leslie E.
Object Type:
Report
System:
The UNT Digital Library
Spin Tests of a 0.059-Scale Model of the Curtiss-Wright XP-55 Airplane
Report discussing spin tests performed on a scale model of the Curtiss-Wright XP-55 airplane. A large elevator with increased deflections and large wing tips with extensions were installed to improve the longitudinal-trim characteristics. Information about the spins, attitude after rotation, and recommended technique for spin recovery is provided.
Date:
August 1945
Creator:
MacDougall, George F., Jr. & Schneiter, Leslie E.
Object Type:
Report
System:
The UNT Digital Library