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  Partner: UNT Libraries Government Documents Department
 Decade: 1940-1949
 Year: 1942
 Collection: Technical Report Archive and Image Library
Adjustment of stick force by a nonlinear aileron-stick linkage

Adjustment of stick force by a nonlinear aileron-stick linkage

Date: November 1942
Creator: Lowry, John G
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics and flap loads of the brake-flap installation on the 0.40-scale model of the F4F-3 left wing panel

Aerodynamic characteristics and flap loads of the brake-flap installation on the 0.40-scale model of the F4F-3 left wing panel

Date: October 1942
Creator: Liddell, Robert B
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics for internal-balance and Frise type ailerons on an NACA 6 series low-drag tip section of the wing for the XP-63 airplane

Aerodynamic characteristics for internal-balance and Frise type ailerons on an NACA 6 series low-drag tip section of the wing for the XP-63 airplane

Date: October 1942
Creator: Underwood, William J
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic Heat-Power Engine Operating on a Closed Cycle

Aerodynamic Heat-Power Engine Operating on a Closed Cycle

Date: November 1942
Creator: Ackeret, J. & Keller, D. C.
Description: Hot-air engines with dynamic compressors and turbines offer new prospects of success through utilization of units of high efficiencies and through the employment of modern materials of great strength at high temperature. Particular consideration is given to an aerodynamic prime mover operating on a closed circuit and heated externally. Increase of the pressure level of the circulating air permits a great increase of limit load of the unit. This also affords a possibility of regulation for which the internal efficiency of the unit changes but slightly. The effect of pressure and temperature losses is investigated. A general discussion is given of the experimental installation operating at the Escher Wyss plant in Zurich for a considerable time at high temperatures.
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic problems in the design of efficient propellers

Aerodynamic problems in the design of efficient propellers

Date: August 1942
Creator: Feldman, Lewis
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic tests of an M-31 bomb in the 8-foot high-speed tunnel

Aerodynamic tests of an M-31 bomb in the 8-foot high-speed tunnel

Date: August 25, 1942
Creator: Smith, Norman F
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The aerodynamic tests of three Edo floats for the SB2U-3, 0S2U-2, and XSB2C-2 seaplanes - NACA models 106-K, 107-K, and 125-AH

The aerodynamic tests of three Edo floats for the SB2U-3, 0S2U-2, and XSB2C-2 seaplanes - NACA models 106-K, 107-K, and 125-AH

Date: March 1942
Creator: Liddell, Robert B
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamics of the Fuselage

Aerodynamics of the Fuselage

Date: December 1942
Creator: Multhopp, H.
Description: The present report deals with a number of problems, particularly with the interaction of the fuselage with the wing and tail, on the basis of simple calculating method's derived from greatly idealized concepts. For the fuselage alone it affords, in variance with potential theory, a certain frictional lift in yawed flow, which, similar to the lift of a wing of small aspect ratio, is no longer linearly related to the angle of attack. Nevertheless there exists for this frictional lift something like a neutral stability point the position of which on oblong fuselages appears to be associated with the lift increase of the fuselage in proximity to the zero lift, according to the present experiments. The Pitching moments of the fuselage can be determined with comparatively great reliability so far as the flow conditions in the neighborhood of the axis of the fuselage can be approximated if the fuselage were absent, which, in general, is not very difficult. For the unstable contribution of the fuselage to the static longitudinal stability of the airplane it affords comparatively simple formulas, the evaluation of which offers little difficulty. On the engine nacelles there is, in addition a very substantial wing moment contribution induced ...
Contributing Partner: UNT Libraries Government Documents Department
Analyses of West Virginia Coals

Analyses of West Virginia Coals

Date: 1942
Creator: Price, Paul H.; Heck, E. T.; Fieldner, Arno Carl; Toenges, Albert L.; Anderson, R. L.; Snyder, N. H. et al.
Description: Technical paper issued by the Bureau of Mines over studies of West Virginia coal fields. Characteristics of coals and mines are discussed. This paper includes tables, maps, and illustrations.
Contributing Partner: UNT Libraries Government Documents Department
Analysis of heat and compressibility effects in internal flow systems and high-speed tests of a ram-jet system

Analysis of heat and compressibility effects in internal flow systems and high-speed tests of a ram-jet system

Date: September 1942
Creator: Baals, Donald D
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Analysis of heat and compressibility effects in internal flow systems and high-speed tests of a ram-jet system

Analysis of heat and compressibility effects in internal flow systems and high-speed tests of a ram-jet system

Date: July 21, 1942
Creator: Becker, John V & Baals, Donald D
Description: An analysis has been made by the NACA of the effects of heat and compressibility in the flow through the internal systems of aircraft. Equations and charts are developed whereby the flow characteristics at key stations in a typical internal system may be readily obtained.
Contributing Partner: UNT Libraries Government Documents Department
An analysis of the effect of core structure and performance on volume and shape of cross-flow tubular intercoolers

An analysis of the effect of core structure and performance on volume and shape of cross-flow tubular intercoolers

Date: December 1942
Creator: Valerino, Michael F
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Analytical theory of the Campini propulsion system

Analytical theory of the Campini propulsion system

Date: March 1, 1942
Creator: Campini, S
Description: Following the description of the new propulsion system and the definition of the propulsive efficiency, this efficiency is calculated under various conditions of flight with allowance for all internal losses. The efficiency and consumption curves are plotted, their practical values discussed and the behavior of the system analyzed at various altitudes and speeds. The immediate possibilities of the new system in flight at high and very high altitudes in relation to the theoretical and experimental results are discussed in detail.
Contributing Partner: UNT Libraries Government Documents Department
Annual Report of the Explosives Division, Fiscal Year 1942

Annual Report of the Explosives Division, Fiscal Year 1942

Date: December 1942
Creator: Huff, Wilbert James
Description: Report issued by the U.S. Bureau of Mines on the annual report of work conducted by the Explosives Division during the fiscal year of 1942. Descriptions of testing projects and operations are presented. This report includes tables, graphs, illustrations, and photographs.
Contributing Partner: UNT Libraries Government Documents Department
Annual Report of the Mining Division, Fiscal Year 1942

Annual Report of the Mining Division, Fiscal Year 1942

Date: October 1942
Creator: Jackson, Charles F.
Description: Report issued by the U.S. Bureau of Mines on the annual work conducted by the Mining Division during 1942. Descriptions of projects and operations during the fiscal year are listed. This report contains tables, and photographs.
Contributing Partner: UNT Libraries Government Documents Department
Annual report of the National Advisory Committee for Aeronautics (27th).administrative report including Technical Report nos. 704 to 726

Annual report of the National Advisory Committee for Aeronautics (27th).administrative report including Technical Report nos. 704 to 726

Date: 1942
Creator: unknown
Description: Report includes the National Advisory Committee for Aeronautics letter of submittal to the President, summaries of the committee's activities and research accomplished, bibliographies, and financial report.
Contributing Partner: UNT Libraries Government Documents Department
Application of Balancing Tabs to Ailerons

Application of Balancing Tabs to Ailerons

Date: June 1, 1942
Creator: Sears, Richard I.
Description: Analysis was made to determine characteristics required of a balancing-tab system for ailerons in order to reduce aileron stick forces to any desired magnitude. Series of calculations based on section data were made to determine balancing-tab systems of various chord tabs and ailerons that will give, for a particular airplane, zero rate of aileron hinge moment with aileron deflection and yet will produce same maximum rate of roll as a plain unbalanced 15-percent chord aileron of same span. Effects of rolling velocity and of forces in tab link on aileron hinge moments have been included.
Contributing Partner: UNT Libraries Government Documents Department
Beam and torsion tests of aluminum-alloy 615-T tubing

Beam and torsion tests of aluminum-alloy 615-T tubing

Date: October 1, 1942
Creator: Moore, R L & Holt, Marshall
Description: Tests were made to determine the effect of length and the effect of ratios of diameter to wall thickness upon the flexural and torsional moduli of failure of 61S-T aluminum-alloy tubing. The moduli of failure in bending, as determined by tests in which the tubing was loaded on the neutral axis at the one-third points of the span, were found to bear an approximately linear relationship with diameter-thickness ratio and were practically independent of span within the limits investigated. Empirical equations are given describing the relations obtained. The moduli of failure in torsion were found to be dependent upon length as well as upon diameter-thickness ratios. Empirical equations are given for predicting strengths within the range of plastic buckling. Within the elastic range, available torsion theories were found to be satisfactory.
Contributing Partner: UNT Libraries Government Documents Department
Bending of rectangular plates with large deflections

Bending of rectangular plates with large deflections

Date: January 1, 1942
Creator: Levy, Samuel
Description: The solution of Von Karman's fundamental equations for large deflections of plates is presented for the case of a simply supported rectangular plate under combined edge compression and lateral loading. Numerical solutions are given for square plates and for rectangular plates with a width-span ratio of 3:1. The effective widths under edge compression are compared with effective widths according to Von Karman, Bengston, Marguerre, and Cox and with experimental results by Ramberg, Mcpherson, and Levy. The deflections of a square plate under lateral pressure are compared with experimental and theoretical results by Kaiser. It is found that the effective widths agree closely with Marguerre's formula and with the experimentally observed values and that the deflections agree with the experimental results and with Kaiser's work.
Contributing Partner: UNT Libraries Government Documents Department
Bending of Rectangular Plates with Large Deflections

Bending of Rectangular Plates with Large Deflections

Date: May 1, 1942
Creator: Levy, Samuel
Description: The solution of von Karman's fundamental equations for large deflections of plates is presented for the case of a simply supported rectangular plate under combined edge compression and lateral loading. Numerical solutions are given for square plates and for rectangular plates with a width-span ratio of 3:1. The effective widths under edge compression are compared with effective widths according to von Karman, Bengston, Marguerre, and Cox and with experimental results by Ramberg, McPherson, and Levy. The deflections for a square plate under lateral pressure are compared with experimental and theoretical results by Kaiser. It is found that the effective widths agree closely with Marguerre's formula and with the experimentally observed values and that the deflections agree with the experimental results and with Kaiser's work.
Contributing Partner: UNT Libraries Government Documents Department
Bending tests of a monocoque box

Bending tests of a monocoque box

Date: January 1, 1942
Creator: Mcpherson, Albert E; Ramberg, Walter & Levy, Samuel
Description: A monocoque box beam consisting of a 24S-T aluminum-alloy sheet reinforced by four bulkheads and by longitudinal stringers and corner posts was subjected to bending loads as follows: pure bending about the lift axis, cantilever bending about the lift axis, and pure bending about both lift and drag axis. Longitudinal strains were measured for loads up to a load at which permanent set became measurable. The loads were sufficient to produce buckling of the sheet between stringers on the compression side of the box. The only noticeable effect of this buckling was a small increase in extreme-fiber strain on the compression side. The measured strains and measured deflections differed less than 10 percent from those computed from the simple beam theory after taking account of the effective width of the buckled sheet. The effect of the bulkheads on the distribution of stringer strain was negligible.
Contributing Partner: UNT Libraries Government Documents Department
Bending with large deflection of a clamped rectangular plate with length-width ratio of 1.5 under normal pressure

Bending with large deflection of a clamped rectangular plate with length-width ratio of 1.5 under normal pressure

Date: April 14, 1942
Creator: Levy, Samuel & Greenman, Samuel
Description: The Von Karman equations for a thin flat plate with large deflections are solved for the special case of a plate with clamped edges having a ratio of length to width of 1.5 and loaded by uniform normal pressure. Center deflections, membrane stresses, and extreme-fiber bending stresses are given as a function of pressure for center deflections up to twice the thickness of the plate. For small deflections the results coincide with those obtained by Hencky from the linear theory. The maximum stresses and center deflection at high pressures differ less than 3 percent from those derived by Bostnov for an infinitely long plate with clamped edges. This agreement suggests that clamped plates with a length-to-width ratio greater than 1.5 may be reared as infinitely long plates for purposes of design.
Contributing Partner: UNT Libraries Government Documents Department
A Brief Study of the Speed Reduction of Overtaking Airplanes by Means of Air Brakes, Special Report

A Brief Study of the Speed Reduction of Overtaking Airplanes by Means of Air Brakes, Special Report

Date: May 1, 1942
Creator: Pearson, H. A. & Amderspm. R. F.
Description: As an aid to airplane designers interested in providing pursuit airplanes with decelerating devices intended to increase the firing time when overtaking another airplane, formulas are given relating the pertinent distances and speeds in horizontal flight to the drag increase required. Charts are given for a representative parasite-drag coefficient from which the drag increase, the time gained, and the closing distance may be found. The charts are made up for three values of the ratio of the final speed of the pursuing airplane to the speed of the pursued airplane and for several values of the ratio of the speed of the pursued airplane to the initial speed of the pursuing airplane. Charts are also given indicating the drag increases obtainable with double split flaps and with conventional propellers. The use of the charts is illustrated by an example in which it is indicated that either double split flaps or, under certain ideal conditions, reversible propellers should provide the speed reductions required.
Contributing Partner: UNT Libraries Government Documents Department
Calculated effects of full-span slotted and Fowler flaps on longitudinal stability and control characteristics for a typical fighter-type airplane with various tail modifications

Calculated effects of full-span slotted and Fowler flaps on longitudinal stability and control characteristics for a typical fighter-type airplane with various tail modifications

Date: July 1, 1942
Creator: Goranson, R Fabian
Description: None
Contributing Partner: UNT Libraries Government Documents Department
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