65 Matching Results

Search Results

Advanced search parameters have been applied.

Preliminary Investigation of Modifications to Conventional Airplanes to Give Nonstalling and Short-Landing Characteristics

Description: "This report describes flight and landing tests made on a group of conventional airplanes. The upward deflection of the elevators was limited to the point where the airplanes could not be made to spin without the aid of power. With the elevator travel thus limited, the airplane in every case had good lateral stability and good aileron effectiveness up to the highest angles of attack which could be obtained in a glide, although this was not true in any case without the limited control" (p. 343).
Date: January 25, 1932
Creator: Weick, Fred E.
Partner: UNT Libraries Government Documents Department

The Effect of the Sperry Messenger Fuselage on the Air Flow at the Propeller Plane

Description: "In order to study the effect of the fuselage, landing gear, and engine on the air flow through the propeller, a survey was made in the plane of the Sperry Messenger propeller with the propeller removed. The tests were made in the 20-foot air stream of the propeller research tunnel of the National Advisory Committee for Aeronautics at Langley Field, Virginia. The variation of the velocity with distance from the center in the propeller plane was found to be appreciable and well worth consideration in the design of propellers" (p. 1).
Date: January 1928
Creator: Weick, Fred E.
Partner: UNT Libraries Government Documents Department

Wind-Tunnel Tests of Wing Flaps Suitable for Direct Control of Glide-Path Angle

Description: "Preliminary tests have been made for the purpose of obtaining a flap arrangement suitable for direct and immediate control of the steepness of the glide path of an airplane, a use for which present flaps are not satisfactory. An attempt has been made to develop a flap giving a reasonably high maximum lift coefficient with relatively low deflection and maintaining this value of the maximum lift coefficient with a large increase of deflection, the increase in deflection being accompanied by a large increase in drag. An arrangement was found that gave a maximum lift coefficient of approximately 1.90 for all flap deflections between 25 and 80 degrees, within which range the drag of the wing increased regularly to a large value" (p. 1).
Date: January 1936
Creator: Weick, Fred E.
Partner: UNT Libraries Government Documents Department

The twenty-foot propeller research tunnel of the National Advisory Committee for Aeronautics

Description: This report describes in detail the new propeller research tunnel of the National Advisory Committee for Aeronautics at Langley Field, Va. This tunnel has an open jet air stream 20 feet in diameter in which velocities up to 110 M. P. H. Are obtained. Although the tunnel was built primarily to make possible accurate full-scale tests on aircraft propellers, it may also be used for making aerodynamic tests on full-size fuselages, landing gears, tail surfaces, and other aircraft parts, and on model wings of large size. (author).
Date: January 1929
Creator: Weick, Fred E. & Wood, Donald H.
Partner: UNT Libraries Government Documents Department

The effect of the wings of single engine airplanes on propulsive efficiency as shown by full scale wind tunnel tests

Description: An investigation was conducted to determine the effect of the wings on propulsive efficiency. The wings are shown to cause a reduction of 1 percent to 3 percent in propulsive efficiency, which is about the same for monoplane as well as biplane wings.
Date: October 1929
Creator: Weick, Fred E. & Wood, Donald H.
Partner: UNT Libraries Government Documents Department

The aerodynamic characteristics of a model wing having a split flap deflected downward and moved to the rear

Description: From Summary: "Tests were made on a model wing with three different sized split trailing-edged flaps, in the NACA 7 by 10 foot wind tunnel. The flaps were formed of the lower rear portion of the wing and were rotated downward about axes at their front edges. The lift, drag, and center of pressure were measured with the axis in its original position and also with it moved back in even steps to the trailing edge of the main wing, giving in effect an increase in area. The split flaps when deflected about their original axis locations gave slightly higher maximum lift coefficients than conventional trailing-edge flaps, and the lift coefficients were increased still further by moving the axes toward the rear. The highest value of C(sub L max), which was obtained with the largest flap hinged at 90 per cent of the chord from the leading edge, was 2.52 as compared with 1.27 for the basic wing."
Date: May 1932
Creator: Weick, Fred E. & Harris, Thomas E.
Partner: UNT Libraries Government Documents Department

Preliminary Wind-Tunnel and Flight Tests of a Balanced Split Flap, Special Report

Description: One disadvantage that has been apparent in the operation of split flaps as used to date is the time and effort required to operate them. In this communication an investigation is being made of possible means for balancing them aerodynamically to make their operation easier. Several arrangements have been tested in the 7 by 210 foot wind tunnel, and the results of the wind-tunnel tests as well as preliminary flight tests on one of the more promising forms are given in this paper.
Date: August 1934
Creator: Weick, Fred E. & Thompson, Floyd L.
Partner: UNT Libraries Government Documents Department

The effect of lateral controls in producing motion of an airplane as computed from wind-tunnel data

Description: This report presents the results of an analytical study of the lateral controllability of an airplane in which both the static rolling and yawing moments supplied by the controls and the reactions due to the inherent stability of the airplane have been taken into account. The investigation was undertaken partly for the purpose of coordinating the results of a long series of wind-tunnel investigations with phenomena observed in flight tests; for this reason a hypothetical average airplane, embodying the essential characteristics of both wind-tunnel models and the full-size test airplanes, was assumed for the study.
Date: April 20, 1936
Creator: Weick, Fred E. & Jones, Robert T.
Partner: UNT Libraries Government Documents Department

Resume and analysis of NACA lateral control research

Description: "An analysis of the principal results of recent NACA lateral control research is made by utilizing the experience and progress gained during the course of the investigation. Two things are considered of primary importance in judging the effectiveness of different control devices: the (calculated) banking and yawing motion of a typical small airplane caused by a deflection of the control, and the stick force required to produce this deflection. The report includes a table in which a number of different lateral control devices are compared on these bases" (p. 1).
Date: April 20, 1937
Creator: Weick, Fred E. & Jones, Robert T.
Partner: UNT Libraries Government Documents Department

Wind-tunnel research comparing lateral control devices, particularly at high angles of attack 4: floating tip ailerons on rectangular wings

Description: "This report is the fourth of a series on systematic tests conducted which compares lateral control devices with particular reference to their effectiveness at high angles of attack. The present report covers tests with floating tip ailerons on rectangular Clark y wings. Ailerons of two profiles were tested - symmetrical and Clark y, both with adjustable trailing-edge flaps. Each form was tested at three hinge-axis locations, both with and without vertical end plates between the ailerons and the wing proper. The results from these tests are compared with the results from tests on a wing of the same over-all size equipped with average-sized ordinary ailerons" (p. 481).
Date: February 18, 1932
Creator: Weick, Fred E. & Harris, Thomas A.
Partner: UNT Libraries Government Documents Department

Wind-tunnel research comparing lateral control devices, particularly at high angles of attack 6: skewed ailerons on rectangular wings

Description: "This report covers the sixth of a series of investigations in which various lateral control devices are compared with particular reference to their effectiveness at high angles of attack. The present report deals with flap-type ailerons hinged about axes having an angle with respect to the leading and trailing edges of the wing. Tests were made on four different skewed ailerons, including two different angles of skew and two sizes of ailerons" (p. 81).
Date: July 12, 1932
Creator: Weick, Fred E. & Harris, Thomas A.
Partner: UNT Libraries Government Documents Department

Wind tunnel research comparing lateral control devices, particularly at high angles of attack 11: various floating tip ailerons on both rectangular and tapered wings

Description: Discussed here are a series of systematic tests being conducted to compare different lateral control devices with particular reference to their effectiveness at high angles of attack. The present tests were made with six different forms of floating tip ailerons of symmetrical section. The tests showed the effect of the various ailerons on the general performance characteristics of the wing, and on the lateral controllability and stability characteristics. In addition, the hinge moments were measured for the most interesting cases.
Date: May 1933
Creator: Weick, Fred E. & Harris, Thomas A.
Partner: UNT Libraries Government Documents Department

Wind-tunnel tests on model wing with Fowler flap and specially developed leading-edge slot

Description: From Summary: "An investigation was made in the NACA 7 by 10 foot wind tunnel to find the increase in maximum lift coefficient which could be obtained by providing a model wing with both a Fowler trailing-edge extension flap and a Handley Page type leading-edge slot. A conventional Handley page slot proportioned to operate on the plain wing without a flap gave but a slight increase with the flap; so a special form of slot was developed to work more effectively with the flap. With the best combined arrangement the maximum lift coefficient based on the original area was increased from 3.17, for the Fowler wing, to 3.62."
Date: May 1933
Creator: Weick, Fred E. & Platt, Robert C.
Partner: UNT Libraries Government Documents Department

Wind-tunnel tests of the Fowler variable-area wing

Description: The lift, drag, and center of pressure characteristics of a model of the Fowler variable-area wing were measured in the NACA 7 by 10 foot wind tunnel. The Fowler wing consists of a combination of a main wing and an extension surface, also of airfoil section. The extension surface can be entirely retracted within the lower rear portion of the main wing or it can be moved to the rear and downward. The tests were made with the nose of the extension airfoil in various positions near the trailing edge of the main wing and with the surface at various angular deflections. The highest lift coefficient obtained was C(sub L) = 3.17 as compared with 1.27 for the main wing alone.
Date: May 1932
Creator: Weick, Fred E. & Platt, Robert C.
Partner: UNT Libraries Government Documents Department

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

Description: 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
Partner: UNT Libraries Government Documents Department

Wind tunnel research comparing lateral control devices, particularly at high angles of attack 10: various control devices on a wing with a fixed auxiliary airfoil

Description: Results are given of a series of systemic tests comparing lateral control devices with particular reference to their effectiveness at high angles of attack. These tests were made with two sizes of ordinary ailerons and different sizes of spoilers on a Clark Y wing model having a narrow auxiliary airfoil fixed ahead and above the leading edge, the chords of the main and auxiliary airfoils being parallel. In addition, the auxiliary airfoil itself was given angular deflection. The purpose was to provide rolling moments for lateral control.
Date: March 1933
Creator: Weick, Fred E. & Noyes, Richard W.
Partner: UNT Libraries Government Documents Department

Wind-tunnel research comparing lateral control devices, particularly at high angles of attack 2: slotted ailerons and frise ailerons

Description: Three model wings, two with typical slotted ailerons and one with typical frise ailerons, have been tested as part of a general investigation on lateral control devices with particular reference to their effectiveness at high angles of attack, in the 7 by 10 foot wind tunnel of the National Advisory Committee for Aeronautics. Force tests, free-autorotation tests, and forced-rotation tests were made which show the effect of the various ailerons on the general performance of the wing, on the lateral controllability, and on the lateral stability, in general, rolling control at 20 degree angle of attack to plain ailerons of the same size. The adverse yawing moments obtained with the slotted and frise ailerons were, in most cases, slightly smaller than those obtained with plain ailerons of the same size and deflection. However, this improvement was small as compared to the improvement obtainable by the use of suitable differential movements with any of the ailerons, including the plain.
Date: February 18, 1932
Creator: Weick, Fred E. & Noyes, Richard W.
Partner: UNT Libraries Government Documents Department

Wind-tunnel research comparing lateral control devices particularly at high angles of attack 13: auxiliary airfoils used as external ailerons

Description: This is the thirteenth report on a series of systematic tests comparing lateral control devices with particular reference to their effectiveness at high angles of attack. The present wind tunnel tests were made to determine the most feasible locations for lateral control surfaces mounted externally to a rectangular Clark y wing.
Date: July 23, 1934
Creator: Weick, Fred E. & Noyes, Richard W.
Partner: UNT Libraries Government Documents Department

Wind-Tunnel Research Comparing Lateral Control Devices, Particularly at High Angles of Attack 5: Spoilers and Ailerons on Rectangular Wings

Description: "This report covers the fifth of a series of systematic investigations in which lateral control devices are compared with particular reference to their effectiveness at high angles of attack. The present report deals with tests of spoilers and ordinary ailerons on rectangular Clark Y wing models. In an effort to obtain satisfactory control throughout the entire angle-of-attack range that can be maintained in flight, various spoilers were tested in combination with two sizes of previously tested ordinary ailerons - one of average proportions and the other short and wide. In addition, one large spoiler was tested alone" (p. 719).
Date: June 13, 1932
Creator: Weick, Fred E. & Shortal, Joseph A.
Partner: UNT Libraries Government Documents Department

Development of the N.A.C.A. Slot-Lip Aileron

Description: "An investigation of the undesirable delayed action, or lag, of the spoiler-type lateral control device led to the development of the NACA slot-lip aileron. The tests were made in the 7- by 10-foot wind tunnel with a 4- by 8-foot wing hinged at the tunnel jet boundary and restrained in roll by elastic cords. Time histories were taken of the motion of the control device under test and of the resulting wing motion" (p. 1).
Date: November 1935
Creator: Weick, Fred E. & Shortal, Joseph A.
Partner: UNT Libraries Government Documents Department

The Effect of Multiple Fixed Slots and a Trailing-Edge Flap on the Lift and Drag of a Clark Y Airfoil

Description: "Lift and drag tests were made on a Clark Y wing equipped with four fixed slots and a trailing-edge flap in the 5-foot vertical wind tunnel of the National Advisory Committee for Aeronautics. All possible combinations of the four slots were tested with the flap neutral and the most promising combinations were tested with the flap down 45 degrees. Considering both the maximum lift coefficient and the speed-range ratio with the flap neutral no appreciable improvement was found with the use of more than the single leading-edge slot" (p. 3).
Date: 1932
Creator: Weick, Fred E. & Shortal, Joseph A.
Partner: UNT Libraries Government Documents Department

Wind Tunnel Research Comparing Lateral Control Devices, Particularly at High Angles of Attack 8: Straight and Skewed Ailerons on Wings With Rounded Tips

Description: Tests showed the effect of the ailerons and the tip shapes on the general performance of the wing, as well as on the lateral control and stability characteristics. The hinge moments were not measured but the approximate values are given in the first report of the series.
Date: February 1933
Creator: Weick, Fred E. & Shortal, Joseph A.
Partner: UNT Libraries Government Documents Department

Simplified Propeller Design for Low-Powered Airplanes

Description: "The object of this report is to furnish the designer and builder of small airplanes a simple system for designing the propeller and making the drawing. An empirical design method is used, based on tests of model propellers in a wind tunnel and full scale tests of propellers in flight. The actual designing is accomplished by means of charts and involves very little calculation" (p. 1).
Date: January 1925
Creator: Weick, Fred E.
Partner: UNT Libraries Government Documents Department