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Contribution to the Technique of Landing Large Airships: Part 2
Memorandum presenting a description of the development of the mooring mast and how it contributes to the technique of landing large airships. Some of its fundamental requirements and how it can factor into safe landings are provided.
Date:
May 1929
Creator:
Krell, O.
System:
The UNT Digital Library
Factors of Safety and Indexes of Static Tests
The physical resistance of passengers in establishing an upper limit to the strength of airplane cells is examined and arguments and experiments are discussed.
Date:
May 1923
Creator:
Bailly, Le
System:
The UNT Digital Library
Hydrodynamic tests for determining the take-off characteristics of seaplanes
The resistance of water, even at low speeds, may be such as to render it impossible to take off. For this type of aircraft, it is therefore especially important to determine the take-off characteristics. A new and simple graphical method is given and appears to be the only one for the complete solution of the problem.
Date:
May 1923
Creator:
Verduzio, R.
System:
The UNT Digital Library
Twelfth Rhon Soaring Contest, 1931
The crew of the "Fafnir" was given an excellent opportunity for collecting first-hand data as to the usefulness of gliders in the Alps. It is necessary to recount the remarkable glider achievements ahead of the Rhon Soaring Contest, in order to understand the tension and expectation with which the Rhon contest was anticipated. A description of some of the aircraft present at the event is provided.
Date:
May 1932
Creator:
Georgii, Walter
System:
The UNT Digital Library
Speed Limits of Aircraft
This paper is restricted to the question of attainable speed limits and attacks the problem from different angles. Theoretical limits due to air resistance are presented along with design factors which may affect speed such as wing loads, wing areas, wing section shifting, landing speeds, drag-lift ratios, and power coefficients.
Date:
May 1923
Creator:
Everling, E.
System:
The UNT Digital Library
Determination of Resistance and Trimming Moment of Planing Water Craft
This report presents a new theory which makes it possible to interpret the resistance and the trimming moment for any loading of a planing aircraft when these values are given for one load. This application of the new theory forms the basis of the present paper. Derivations of various conversion formulas are given as well as numerous examples.
Date:
May 1931
Creator:
Schröder, P.
System:
The UNT Digital Library
Balanced and Servo Control Surfaces
"Many reports on various control systems are available, but the results cannot be generally applied since the effect of particular changes of surface-form and mounting are subject to variations depending upon airfoil section and influences of airplane layout. This report presents a simple analysis of several control systems in more general use. Elevators, ailerons, and rudders are all discussed" (p. 1).
Date:
May 1930
Creator:
unknown
System:
The UNT Digital Library
Torsional Vibration of Aircraft Engines
"Exhaustive torsional-vibration investigations are required to determine the reliability of aircraft engines. A general outline of the methods used for such investigations and of the theoretical and mechanical means now available for this purpose is given, illustrated by example. True vibration diagrams are usually obtained from vibration measurements on the completed engine. Two devices for this purpose and supplementing each other, the D.V.L. torsiograph and the D.V.L. torsion recorder, are described in this report" (p. 1).
Date:
May 1932
Creator:
Lürenbaum, Karl
System:
The UNT Digital Library
Determining the Velocity Distribution in the Boundary Layer of an Airfoil Fitted With a Rotary Cylinder
In the closer investigation of the results obtained from a wing model with a rotary cylinder mounted in its leading edge (NACA TM's 307 and 354), the velocity distribution in the vicinity of the surface of the model was determined by a hot-wire anemometer. The results confirmed the belief that the rotary cylinder had considerable effect on the air flow, but demonstrated the fact that the direct influence of the cylinder is confined to a very thin layer in immediate proximity to the surface.
Date:
May 1927
Creator:
Van der Hegge Zijnen, B. G.
System:
The UNT Digital Library
Combined Pitching and Yawing Motion of Airplanes
This report treats the following problems: The beginning of the investigated motions is always a setting of the lateral controls, i.e., the rudder or the ailerons. Now, the first interesting question is how the motion would proceed if these settings were kept unchanged for some time; and particularly, what upward motion would set in, how soon, and for how long, since therein lie the dangers of yawing. Two different motions ensue with a high rate of turn and a steep down slope of flight path in both but a marked difference in angle of attack and consequently different character in the resultant aerodynamic forces: one, the "corkscrew" dive at normal angle, and the other, the "spin" at high angle.
Date:
May 1931
Creator:
v. Baranoff, A. & Hopf, L.
System:
The UNT Digital Library
Ultra-Light Alloys and Their Utilization on Aircraft
Memorandum presenting an overview of ultra-light alloys and their potential use on an aircraft. A definition of ultra-light alloys, some of the present possibilities of ultra-light alloys, and some of the principles governing the use of the alloys in aircraft are provided.
Date:
May 1924
Creator:
Portevin, A. M. & DeFleury, R.
System:
The UNT Digital Library
An Investigation of Loads on Ailerons at Transonic Speeds
"Some aileron load characteristics for three thin wings varying in sweep have been presented for Mach numbers from 0.80 to 1.05. For the transonic Mach number range, shock effects exert a large influence on the loading, but the exact location of each shock for a specific wing design cannot be cataloged at the present time. It is shown, however, that the aileron loading, although greater in magnitude than at subsonic speeds, nevertheless varies in as uniform a fashion as at subsonic speeds" (p. 1).
Date:
May 27, 1955
Creator:
Runckel, Jack F. & Gray, W. H.
System:
The UNT Digital Library
Maximum Rates of Control Motion Obtained From Ground Tests
Report discusses the results of testing to determine the maximum rates of control stick (elevator) motion and corresponding maximum stick forces that could be exerted based on experiments with several pilots. The main topics explored were the comparison of the maximum rates of push and pull, maximum rates of push and pull when a mental restriction was placed on the pilot, and maximum rates at which the pilot though he would apply the elevator control forces versus the actual application of forces. Information about experimental procedures and the rig the testing occurred on is included.
Date:
May 1944
Creator:
Beeler, De E.
System:
The UNT Digital Library
Simplified procedures for estimating flap-control loads at supersonic speeds
Report presenting an investigation to determine the possibility of using simplified procedures for the estimation of control loads at supersonic speeds. The results indicated that relatively simple procedures are possible for the estimation of loadings on flap-type controls at supersonic speeds for cases when no flow separation occurs ahead of the hinge line.
Date:
May 27, 1955
Creator:
Czarnecki, K. R. & Lord, Douglas R.
System:
The UNT Digital Library
The Unsteady Normal-Force Characteristics of Selected NACA Profiles at High Subsonic Mach Numbers
Report presenting a wind-tunnel investigation at subsonic Mach numbers up to 0.9 to measure the root-mean-square variation of the normal forces on 27 NACA airfoil sections. The effects of thickness-chord ratio, camber, location of minimum pressure, and leading-edge radius were investigated.
Date:
May 27, 1955
Creator:
Polentz, Perry P.; Page, William A. & Levy, Lionel L., Jr.
System:
The UNT Digital Library
Analysis of Available Data on Control Surfaces Having Plain-Overhang and Frise Balances
From Introduction: "The present paper deals with control surfaces having plain-overhang and Frise balances."
Date:
May 1944
Creator:
Purser, Paul E. & Toll, Thomas A.
System:
The UNT Digital Library
An Automatically Variable Control Linkage and Its Effect on the Lateral-Control Characteristics of a High-Speed Fighter Airplane
Report discusses an analysis and preliminary design of a control linkage that varies automatically with dynamic pressure. The advantages of the device, including greater lateral control than a fixed control linkage without additional aerodynamic balance, are detailed. The effect of variable linkage on lateral-control characteristics is also described.
Date:
May 1944
Creator:
Gillis, Clarence L.
System:
The UNT Digital Library
A special method for finding body distortions that reduce the wave drag of wing and body combinations at supersonic speeds
Report presenting a consideration of the problem of shaping an adjoining fuselage for a given wing and supersonic Mach number so that the combination will have a low wave drag. Only fuselages that can be simulated by singularities distributed along the body axis are studied.
Date:
May 20, 1955
Creator:
Lomax, Harvard & Heaslet, Max A.
System:
The UNT Digital Library
Full-scale tunnel investigation of the pressure distribution over the tail of the P-47B airplane
Report presenting measurements made of the pressures of the tail surfaces of the Republic Aviation Corporation P-47B airplane in the full-scale tunnel. Pressures were measured over the horizontal and vertical tail surfaces for several angles of attack and angles of yaw with numerous control-surface deflections to provide a check on the design loads. Results regarding the normal-force coefficients and predictions of forces on horizontal tail surfaces are provided.
Date:
May 1943
Creator:
Dingeldein, Richard C.
System:
The UNT Digital Library
Analysis of available data on the effectiveness of ailerons without exposed overhang balance
From Introduction: "As a part of the general lateral-control investigation by the NACA, the large amount of two- and three-dimensional data on the rolling effectiveness of ailerons without exposed overhang balance is collected and analyzed in the present paper."
Date:
May 1944
Creator:
Crandall, Stewart M. & Swanson, Robert S.
System:
The UNT Digital Library
Flight Tests of Dive-Recovery Flaps on an XP-51 Airplane
Report presenting a flight investigation made to determine the effectiveness of dive-recovery flaps installed on the XP-51 airplane as a safety device for recovery from contemplated terminal-velocity dives. The flap installation is described and results are presented of measurements obtained during stick-free pull-ups and pull-outs made by deflecting the dive-recovery flaps to two selected values of flap angle .
Date:
May 1945
Creator:
Beeler, De E. & Williams, Walter C.
System:
The UNT Digital Library
Estimation of Pressures on Cockpit Canopies, Gun Turrets, Blisters, and Similar Protuberances
Report presenting methods for estimating pressure distributions over protuberances such as cockpit canopies, gun turrets, blisters, scoops, and sighting domes. The methods are applied to the estimation of the pressure distributions over spherical segment and faired gun turrets and over the protuberances on the Brewster SB2A-1 airplane. The effects of compressibility, interference, and flow separation are discussed.
Date:
May 1944
Creator:
Wright, Ray H.
System:
The UNT Digital Library
The Porpoising Characteristics of a Planing Surface Representing the Forebody of a Flying-Boat Hull
Porpoising characteristics were observed on V-body fitted with tail surfaces for different combinations of load, speed, moment of inertia, location of pivot, elevator setting, and tail area. A critical trim was found which was unaltered by elevator setting or tail area. Critical trim was lowered by moving pivot either forward or down or increasing radius or gyration. Increase in mass and moment of inertia increased amplitude of oscillations. Complete results are tabulated and shown graphically.
Date:
May 1942
Creator:
Benson, James M.
System:
The UNT Digital Library
Effect of Inlet-Guide-Vane Angle on Blade Vibration and Rotating Stall of 13-Stage Axial-Flow Compressor in Turbojet Engine
Report presenting a blade-vibration and rotating-stall survey on a modified version of a production turbojet engine with a 13-stage axial-flow compressor with a design pressure ratio of 7 and an air flow of 120 pounds per second. This testing was carried out due to the problems rotating stall can cause with both experimental and production axial-flow compressors. Results regarding the rotating-stall patterns, rotor-blade vibrations, radial and axial strength of rotating stall, and maximum rotating-stall speed are provided.
Date:
May 22, 1956
Creator:
Calvert, Howard F.; Medeiros, Arthur A. & Johnson, Donald F.
System:
The UNT Digital Library