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Considerations affecting the additional weight required in mass balance of ailerons

Description: "This paper is essentially a consideration of mass balance of ailerons from a preliminary design standpoint, in which the extra weight of the mass counterbalance is the most important phase of the problem. Equations are developed for the required balance weight for a simple aileron and this weight is correlated with the mass-balance coefficient. It is concluded the location of the c.g. of the basic aileron is of paramount importance and that complete mass balance imposes no great weight penalty… more
Date: August 1937
Creator: Diehl, W. S.
Item Type: Refine your search to only Report
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Contributions to the Theory of Incomplete Tension Bay

Description: The present report offers an approximate theory for the stress and deformation condition after buckling of the skin in reinforced panels and shells loaded in simple shear and compression and under combined stresses. The theory presents a unified scheme for stresses of these types. It is based upon the concept of a nonuniform stress distribution in the metal panel and its marked power of resistance against compressive stresses ("incomplete" tension bay).
Date: July 1937
Creator: Schapitz, E.
Item Type: Refine your search to only Report
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The critical velocity of a body towed by a cable from an airplane

Description: It is sufficient to consider only the equations of motion of the towed body whereas those of the cable may be left out of consideration. The result obtained makes it possible to determine which factors affect the critical velocity and what modifications of the instrument are necessary for extending the upper limit of that velocity.
Date: July 1937
Creator: Koning, C. & DeHaas, T. P.
Item Type: Refine your search to only Report
open access

The Design of Airplane-Engine Superchargers

Description: Report studying the "underlying principles for the computation and design of airplane engine superchargers" (p. 1). With the forms of superchargers and underlying principles of computation, delivery heads per stage of 7,000 to 8,500 meters (air column) at an effective efficiency, based on the adiabatic process, of 0.7 may be attained, the space and weight requirements being kept within reasonable limits.
Date: October 1937
Creator: von der Nüll, Werner
Item Type: Refine your search to only Report
open access

Discharge characteristics of a double injection-valve single-pump injection system

Description: The discharge characteristics of two similar injection valves operated by a single-cylinder fuel-injection pump were determined with an apparatus that measured the quantity of fuel discharged from each valve during every 0.5 degrees of pump rotation. It was found that similar discharges took place from the two valves at all pump speeds when the valve-opening pressures, the nozzle-orifice diameters, and the injection-tube lengths were the same for both valves. Under these conditions, the effects… more
Date: May 1937
Creator: Lee, Dana W. & Marsh, E. T.
Item Type: Refine your search to only Report
open access

A discussion of certain problems connected with the design of hulls of flying boats and the use of general test data

Description: Report presents the results of a survey of problems encountered in applying general test data to the design of flying-boat hulls. It is shown how basic design features may be readily determined from special plots of test data. A study of the effect of the size of a flying boat on the probable limits to be covered by the general test data is included and recommendations for special tests and new methods of presenting test data for direct use in design are given.
Date: November 1937
Creator: Diehl, Walter S.
Item Type: Refine your search to only Report
open access

Drag of Cylinders of Simple Shapes

Description: "In order to determine the effect of shape, compressibility, and Reynolds number on the drag and critical speed for simple forms, the drag forces on models of various simple geometric cross sections were measured in the NACA 11-inch high-speed wind tunnel. The models were circular, semitubular, elliptical, square, and triangular (isosceles) cylinders. They were tested over a speed range from 5 percent of the speed of sound to a value in excess of the critical speed, corresponding, for each mode… more
Date: October 27, 1937
Creator: Lindsey, W. F.
Item Type: Refine your search to only Report
open access

Effect of Air-Entry Angle on Performance of a 2-Stroke-Cycle Compression-Ignition Engine

Description: "An investigation was made to determine the effect of variations in the horizontal and vertical air-entry angles on the performance characteristics of a single-cylinder 2-stroke-cycle compression-ignition test engine. Performance data were obtained over a wide range of engine speed, scavenging pressure, fuel quantity, and injection advance angle with the optimum guide vanes. Friction and blower-power curves are included for calculating the indicated and net performances" (p. 1).
Date: August 1937
Creator: Earle, Sherod L. & Dutee, Francis J.
Item Type: Refine your search to only Report
open access

The Effect of Curvature on the Transition From Laminar to Turbulent Boundary Layer

Description: "In the flow over the upper surface of a wing, a discrepancy between the predicted and actual point of transition from laminar to turbulent boundary layer was found. This effect may be due to the comparatively small radius of curvature of the upper surface of the wing. Tests were undertaken to investigate this effect. As far as the authors know, the present investigation is the first to show that curvature has a pronounced effect on the transition of the boundary layer from the laminar to the t… more
Date: September 1937
Creator: Clauser, Milton & Clauser, Francis
Item Type: Refine your search to only Report
open access

Empirical corrections to the span load distribution at the tip

Description: An analysis of existing pressure-distribution data was made to determine the variation of the tip loading with wing plan form. A series of empirical tip corrections was derived that may be added to theoretical curves in certain cases to obtain a closer approach to the actual loading at the tip. The analysis indicated that the need for a tip correction decreases as either the aspect ratio or the wing taper is increased. In general, it may be said that, for wings of conventional aspect ratio, cor… more
Date: August 1937
Creator: Pearson, H. A.
Item Type: Refine your search to only Report
open access

Energy Loss, Velocity Distribution, and Temperature Distribution for a Baffled Cylinder Model

Description: A study has been made of the important principles involved in the operation of a baffle for an engine cylinder and shows that cooling can be improved by 20 percent by using a correctly designed baffle. Such a gain is as effective as a 65 percent increase in pressure drop across the standard baffle, which had a 1/4 inch clearance between baffle and fin tips.
Date: October 1937
Creator: Brevoort, Maurice J.
Item Type: Refine your search to only Report
open access

Energy Loss, Velocity Distribution, and Temperature Distribution for a Baffled Cylinder Model, Special Report

Description: Report discusses the important principles involved in the operation of a baffle for an engine cylinder and how using a correctly designed baffle can improve cooling. The baffle-exit radius and width and exit-duct length were found to be the most important parts of the baffle and a baffle that gave a relatively uniform temperature distribution was designed.
Date: April 1937
Creator: Brevoort, Maurice J.
Item Type: Refine your search to only Report
open access

The experimental and calculated characteristics of 22 tapered wings

Description: From Summary: "The experimental and calculated aerodynamic characteristics of 22 tapered wings are compared, using tests made in the variable-density wind tunnel. The wings had aspect ratios from 6 to 12 and taper ratios from 1:6:1 and 5:1. The compared characteristics are the pitching moment, the aerodynamic-center position, the lift-curve slope, the maximum lift coefficient, and the curves of drag. The method of obtaining the calculated values is based on the use of wing theory and experiment… more
Date: November 17, 1937
Creator: Anderson, Raymond F.
Item Type: Refine your search to only Report
open access

Experimental Apparatus for the Study of Propellers

Description: The apparatus consists of a universal balance with transmission at variable speeds from 300 to 5,000 rpm and a group directly coupled to the model for speeds of 5 to 30,000 revolutions. This new apparatus was also designed with a torsion meter for measuring the torque. Tests were conducted on the effect of the angle between the propeller axis and the wind direction. The results presented correspond to a first series of tests made without an interposed wing and in which the distance between the … more
Date: March 1937
Creator: Panetti, M.
Item Type: Refine your search to only Report
open access

Experimental investigation of the problem of surface roughness

Description: Based on the universal laws of turbulent velocity distribution at rough and smooth walls, there is in the present work presented a method that allows surface roughness tests and in particular, measurements on the roughness of ship surfaces to be carried out in a much simpler manner. The types of roughness investigated were in the form of flat, rough plates installed in a square-section rectangular channel, the other three walls always being smooth. Twenty-one plates of various roughness were in… more
Date: April 1937
Creator: Schlichting, H.
Item Type: Refine your search to only Report
open access

Experimental Investigation of Wind-Tunnel Interference on the Downwash Behind an Airfoil

Description: "The interference of the wind-tunnel boundaries on the downwash behind an airfoil has been experimentally investigated and the results have been compared with the available theoretical results for open-throat wind tunnels. As in previous studies, the simplified theoretical treatment that assumes the test section to be an infinite free jet has been shown to be satisfactory at the lifting line. The experimental results, however, show that this assumption may lead to erroneous conclusions regardin… more
Date: June 4, 1937
Creator: Silverstein, Abe & Katzoff, S.
Item Type: Refine your search to only Report
open access

A Flight Comparison of Conventional Ailerons on a Rectangular Wing and of Conventional and Floating Wing-Tip Ailerons on a Tapered Wing

Description: Report presents the results of flight tests comparing the relative effectiveness of conventional ailerons of the same size on wings of rectangular and tapered plan forms made with a Fairchild 22 airplane. Information is included comparing conventional and floating wing-tip ailerons on a tapered wing. The results showed that the conventional ailerons were somewhat more effective on the tapered than on the rectangular wing. The difference, however, was so small as to be imperceptible to the pilot… more
Date: October 27, 1937
Creator: Soulé, H. A. & Gracey, W.
Item Type: Refine your search to only Report
open access

Flight tests of an airplane showing dependence of the maximum lift coefficient on the test conditions

Description: "Data are presented to show the extent to which the maximum lift coefficient and consequently the minimum speed of an airplane, determined by flight tests, may vary with test conditions. The data show that cl-max may vary as much as 14 percent, depending on the altitude and wing loading at which the tests were made, the position or motion of the propeller, and the rate at which the angle of attack is changing when the maximum lift coefficient is obtained. The variation of the maximum lift coeff… more
Date: November 1937
Creator: Soulé, H. A. & Hootman, James A.
Item Type: Refine your search to only Report
open access

Free spinning wind-tunnel tests of a low-wing monoplane with systematic wings and tails 2: Mass distributed along the fuselage

Description: Report presenting a study of eight wings and three tails covering a wide range of aerodynamic characteristics in 24 wing-tail combinations. Observations were made of the steady spin for four control settings and of recoveries for five control manipulations. The effect of wing shape, tail arrangement, control settings, relationships between spin characteristics, and comparison with results for basic loading are provided.
Date: December 1937
Creator: Seidman, Oscar & Neihouse, A. I.
Item Type: Refine your search to only Report
open access

Free-spinning wind-tunnel tests of a low-wing monoplane with systemic changes in wings and tails 1: Basic loading condition

Description: A series of tests was made at the National Advisory Committee for Aeronautics (NACA) free-spinning tunnel to determine the effect of systematic changes in wing and tail arrangement upon steady-spinning and recovery characteristics of a conventional low-wing monoplane model for a basic loading condition. Eight wings and three tails, covering a wide range of aerodynamic characteristics, were independently ballasted so as to be interchangeable with no change in mass distribution. For each of the 2… more
Date: August 1937
Creator: Seidman, Oscar & Neihouse, A. I.
Item Type: Refine your search to only Report
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