Resource Type

The Shackleton-Murray SM-1 Light Airplane: A Two-Place High-Wing Monoplane (open access)

The Shackleton-Murray SM-1 Light Airplane: A Two-Place High-Wing Monoplane

Circular presenting a description of the light airplane SM-1, which was designed by W. S. Shackleton and Lee Murray. Information regarding the design and flight characteristics and some photographs of the airplane are provided.
Date: June 1933
Creator: unknown
Object Type: Report
System: The UNT Digital Library
Estimate of the Gas Reserves of the Oklahoma City Oil Field, Oklahoma County, Oklahoma (open access)

Estimate of the Gas Reserves of the Oklahoma City Oil Field, Oklahoma County, Oklahoma

Report issued by the U.S. Bureau of Mines on the exploration of the Oklahoma City oil field for natural gas reserves. This report includes tables, maps, and illustrations.
Date: June 1933
Creator: Hill, Harry Blackburn & Rawlins, E. L.
Object Type: Report
System: The UNT Digital Library
Farmstead water supply. (open access)

Farmstead water supply.

Discusses the importance of a well-planned water system for the farm home. Describes methods for pumping, filtering, and storing water on the farm.
Date: June 1933
Creator: Warren, George M. (George Milton)
Object Type: Book
System: The UNT Digital Library
Formulas for the Stress Analysis of Circular Rings in a Monocoque Fuselage (open access)

Formulas for the Stress Analysis of Circular Rings in a Monocoque Fuselage

"The formulas given in this report provide a simplified method for the stress-analysis of fuselage bulkheads that are approximately circular rings of uniform cross section. Complicated load systems acting on a ring can usually be resolved into simplified load systems; and formulas for moment, axial force, and shear for such simplified load systems are given in this report. Illustrative examples showing the use of this method in practical stress-analysis work are also included" (p. 1).
Date: June 1933
Creator: Miller, Roy A. & Wood, Karl D.
Object Type: Report
System: The UNT Digital Library
Aerodynamic tests of a low aspect ratio tapered wing with various flaps, for use on tailless airplanes (open access)

Aerodynamic tests of a low aspect ratio tapered wing with various flaps, for use on tailless airplanes

From Introduction: "The tests described in this report are the first in an investigation by N.A.C.A. of the aerodynamic characteristics of possible tailless arrangements. The investigations will be extended to include whatever range is through most desirable and may include, among other things, variations in aspect ratio, taper, sweepback, washout, air-foil section, dihedral, and also control flaps or other control devices of different forms and proportions."
Date: June 1933
Creator: Weick, Fred E. & Sanders, Robert
Object Type: Report
System: The UNT Digital Library
A Simple Method for Increasing the Lift of Airplane Wings by Means of Flaps (open access)

A Simple Method for Increasing the Lift of Airplane Wings by Means of Flaps

"Aerodynamic considerations led us, not long ago, to investigate a device which seemed to promise a contribution to the problem of reducing the landing speed of an airplane. We have subsequently learned that similar devices had already been proposed and investigated by others, but it seems advisable, nevertheless, to report our results. The problem is to create, in landing, a region of turbulence on the lower side of the wing near the trailing edge by some obstacle to the air flow" (p. 1).
Date: June 1933
Creator: Gruschwitz, Eugen & Schrenk, Oskar
Object Type: Report
System: The UNT Digital Library
Behavior of Vortex Systems (open access)

Behavior of Vortex Systems

Progressive application of the Kutta-Joukowsky theorem to the relationship between airfoil lift and circulation affords a number of formulas concerning the conduct of vortex systems. The application of this line of reasoning to several problems of airfoil theory yields an insight into many hitherto little observed relations. This report is confined to plane flow, hence all vortex filaments are straight and mutually parallel (perpendicular to the plane of flow).
Date: June 1933
Creator: Betz, A.
Object Type: Report
System: The UNT Digital Library
The Schneider Trophy Contest (open access)

The Schneider Trophy Contest

This report presents a history of the Schneider trophy race with special emphasis of England's win in the 1931 race. Lift and drag are reported on and discussed extensively.
Date: June 1933
Creator: Weyl, Alfred Richard
Object Type: Report
System: The UNT Digital Library
Pressure Rise, Gas Vibrations and Combustion Noises During the Explosion of Fuels (open access)

Pressure Rise, Gas Vibrations and Combustion Noises During the Explosion of Fuels

"In the use of piezo-quartz indicators for high-speed automobile engines, the interpretation of pressure-time diagrams made by an oscillograph offers certain difficulties. On the one hand, the scale of the pressure amplitudes is not always the same under all conditions, while, on the other hand, the atmospheric zero line may be shifted from its correct position in the oscillogram. These facts make necessary to verify the readings of the quartz indicators by direct calibration before and after each series of tests and, on the basis of the results, to determine the scale for the oscillograms" (p. 1).
Date: June 1933
Creator: Wawrziniok
Object Type: Report
System: The UNT Digital Library
Tests for the Elimination of Tail Flutter (open access)

Tests for the Elimination of Tail Flutter

"On various low-wing monoplanes the horizontal tail surfaces flutter in flight at large angles of attack and occasionally in curvilinear flight. This flutter leads to torsional vibrations of the rear end of the fuselage, as manifested by vibrations of the control stick. According to the earlier DVL investigations tail flutter is due to the influence, on horizontal tail surfaces, of eddies or vortices shed at large angles of attack by the upper surface of the wing root. The cause of tail flutter on a low-wing monoplane and the means of preventing it are investigated in the present report" (p. 1).
Date: June 1933
Creator: Biechteler, Curt
Object Type: Report
System: The UNT Digital Library
Determination of the theoretical pressure distribution for twenty airfoils (open access)

Determination of the theoretical pressure distribution for twenty airfoils

This report gives the theoretical distribution of pressure at lift coefficients of 0, 0.5, 1.0, and 1.5 for 20 airfoils, calculated on the basis of a rigorous potential theory of arbitrary airfoils. It also provides tables from which the characteristics of the airfoils for any angle of attack in 2-dimensional potential flow are readily calculable. The theoretical values of the angles of zero lift, the lift and moment coefficients, and the ideal angles of attack are listed and some comparisons with experiment are indicated. The results presented may be of value in predicting structural loads and also in a correlation of theoretical pressure gradients with profile resistance.
Date: June 2, 1933
Creator: Garrick, I. E.
Object Type: Report
System: The UNT Digital Library
The experimental determination of the moments of inertia of airplanes (open access)

The experimental determination of the moments of inertia of airplanes

The application of the pendulum method to the experimental determination of the moments of inertia of airplanes is discussed in this report. Particular reference is made to the effects of the air, in which the airplane is immersed, on the swinging tests and to the procedure by which these effects are taken into account. This procedure has been used for some time, and the data on several airplanes for which the moments of inertia have been found are included.
Date: June 8, 1933
Creator: Soulé, Hartley A. & Miller, Marvel P.
Object Type: Report
System: The UNT Digital Library
The interference between struts in various combinations (open access)

The interference between struts in various combinations

This report presents the results of wind tunnel tests made to determine the interference drag arising from various arrangements of streamline struts and round struts, or cylinders. Determinations were made of the interference drag of struts spaced side by side, struts in tandem, tandem struts encased in a single fairing, a strut intersecting a plane, and struts intersecting to form a v. Three sizes of struts were used for most of the tests. These tests show that the interference drag arising from struts in close proximity may be of considerable magnitude, in some instances amounting to more than the drag of the struts themselves.
Date: June 5, 1933
Creator: Biermann, David & Herrnstein, William H., Jr.
Object Type: Report
System: The UNT Digital Library
Increasing the air charge and scavenging the clearance volume of a compression-ignition engine (open access)

Increasing the air charge and scavenging the clearance volume of a compression-ignition engine

The object of the investigation presented in this report was to determine the effects of increasing the air charge and scavenging the clearance volume of a 4-stroke-cycle compression-ignition engine having a vertical-disk form combustion chamber. Boosting the inlet-air pressure with normal valve timing increased the indicated engine power in proportion to the additional air inducted and resulted in smoother engine operation with less combustion shock. Scavenging the clearance volume by using a valve overlap of 145 degrees and an inlet-air boost pressure of approximately 2 1/2 inches of mercury produced a net increase in performance for clear exhaust operation of 33 percent over that obtained with normal valve timing and the same boost pressure. The improved combustion characteristics result in lower specific fuel consumption, and a clearer exhaust.
Date: June 10, 1933
Creator: Spanogle, J. A.; Hicks, C. W. & Foster, H. H.
Object Type: Report
System: The UNT Digital Library
The N.A.C.A. Tank: A High-Speed Towing Basin for Testing Models of Seaplane Floats (open access)

The N.A.C.A. Tank: A High-Speed Towing Basin for Testing Models of Seaplane Floats

"This report describes the high-speed model towing basin of the National Advisory Committee for Aeronautics, usually referred to as the NACA Tank. The purpose of this piece of equipment is to enable the Committee to provide information and data regarding the performance of seaplanes on the water analogous to the information furnished concerning the performance of airplanes in the air" (p. 535).
Date: June 9, 1933
Creator: Truscott, Starr
Object Type: Report
System: The UNT Digital Library
Performance of a fuel-injection spark-ignition engine using a hydrogenated safety fuel (open access)

Performance of a fuel-injection spark-ignition engine using a hydrogenated safety fuel

This report presents the performance of a single-cylinder test engine using a hydrogenated safety fuel. The safety fuel has a flash point of 125 degrees f. (Cleveland open-dup method), which is high enough to remove most of the fire hazard, and an octane number of 95, which permits higher compression ratios to be used than are permissible with most undoped gasolines.
Date: June 13, 1933
Creator: Schey, Oscar W. & Young, Alfred W.
Object Type: Report
System: The UNT Digital Library
Wind-Tunnel Tests on Combinations of a Wing With Fixed Auxiliary Airfoils Having Various Chords and Profiles (open access)

Wind-Tunnel Tests on Combinations of a Wing With Fixed Auxiliary Airfoils Having Various Chords and Profiles

This report presents the results of wind tunnel tests on various auxiliary airfoils having three different airfoil sections and several different chord lengths in combination with a Clark Y model wing in a sufficient number of relative positions to determine the optimum with regard to certain criterions of aerodynamic performance. The airfoil sections included a symmetrical profile, one of medium camber, and a highly cambered one. The chord sizes of the auxiliary airfoils ranged from 7.5 to 25 percent of the chord of the main wing, and the span was equal to that of the main wing.
Date: June 10, 1933
Creator: Weick, Fred E. & Sanders, Robert
Object Type: Report
System: The UNT Digital Library
Strength Tests of Thin-Walled Duralumin Cylinders in Compression (open access)

Strength Tests of Thin-Walled Duralumin Cylinders in Compression

"This report is the second of a series presenting the results of strength tests of thin-walled duralumin cylinders and truncated cones of circular and elliptic section. It contains the results obtained from compression tests on 45 thin-walled duralumin cylinders of circular section with ends clamped to rigid bulkheads. In addition to the tests on duralumin cylinders, there are included the results of numerous tests on rubber, celluloid, steel, and brass cylinders obtained from various sources" (p. 585).
Date: June 10, 1933
Creator: Lundquist, Eugene E.
Object Type: Report
System: The UNT Digital Library