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The Effect of Partial-Span Split Flaps on the Aerodynamic Characteristics of a Clark Y Wing

Description: "Aerodynamic force tests were made in the N.A.C.A. 7 by 10 foot wind tunnel on a model Clark Y wing with a 20 percent chord split flap deflected 60 degrees downward. The tests were made to determine the effect of partial-span split flaps, located at various positions along the wing span on the aerodynamic characteristics of the wing-and-flap combination. The different lengths and locations of the flaps were obtained by cutting off portions of a full-span flap, first from the tips and then from the center. The results are given in the form of curves of lift, drag, and center of pressure" (p. 1).
Date: September 1933
Creator: Wenzinger, Carl J.
Partner: UNT Libraries Government Documents Department

Wind-Tunnel Investigation of the Aerodynamic Balancing of Upper-Surface Ailerons and Split Flaps

Description: This report presents the results of wind tunnel tests to determine the effectiveness of various methods of reducing the high control forces of unbalanced upper-surface ailerons and of unbalanced split flaps. A balanced split flap was developed that required control forces about half those of the unbalanced split flap when the balanced split flap was deflected to give approximately the same maximum lift.
Date: August 20, 1935
Creator: Wenzinger, Carl J.
Partner: UNT Libraries Government Documents Department

Wind-Tunnel Investigation of Ordinary and Split Flaps on Airfoils of Different Profile

Description: Report presents the results of wind tunnel tests of the Clark Y, the NACA 23012 and the NACA 23021 airfoils equipped with full-span ordinary flaps and with full-span simple split flaps. The principal object of the tests was to determine the characteristics of the airfoils with ordinary flaps and in addition, to determine the relative merits of the various airfoils when equipped with either ordinary flaps or with simple split flaps. The Clark Y airfoil was tested with 3 widths of ordinary flap, 10, 20, and 30 percent of the airfoil chord.
Date: October 25, 1935
Creator: Wenzinger, Carl J.
Partner: UNT Libraries Government Documents Department

Wind-Tunnel Measurements of Air Loads on Split Flaps

Description: Note presenting tests in a wind tunnel to determine the control forces and air loads acting on split flaps. Clark Y wing models were used with two different sizes of full-span split flaps, one with a medium chord and one with a narrow chord. The results indicated that at angles of attack and flap deflections for maximum lift, the lift loads on the split flaps were only 5 percent and 9 percent of the total lift for the narrow and medium-chord flaps respectively.
Date: May 1934
Creator: Wenzinger, Carl J.
Partner: UNT Libraries Government Documents Department

Wind-Tunnel Investigation of Tapered Wings With Ordinary Ailerons and Partial-Span Split Flaps

Description: Report presents the results of an investigation made in the NACA 7 by 10-foot wind tunnel to determine the aerodynamic properties of tapered wings having partial-span flaps for high lift and ordinary ailerons for lateral control. Each of two Clark-y wings, tapered 5:1 and 5:3, was equipped with partial-span split flaps of two lengths and with ordinary ailerons extending from the outboard ends of the flap to the wing tips. Measurements of wing forces and moments and of aileron hinge moments were made for the two conditions of flaps neutral and deflected.
Date: January 14, 1937
Creator: Wenzinger, Carl J.
Partner: UNT Libraries Government Documents Department

The Effects of Full-Span and Partial-Span Split Flaps on the Aerodynamic Characteristics of a Tapered Wing

Description: "The investigation was made to determine the effects of full-span and of partial-span split flaps on the aerodynamic characteristics of a tapered wing. Aerodynamic force tests were made in the N.A.C.A. 7 by 10 foot wind tunnel on a highly tapered Clark Y wing equipped with various split flaps. Two sizes of tapered-chord flaps were tested as full-span flaps, and a narrow tapered-chord flap was tested as a partial-span flap by cutting off portions first from the tip and then from the center" (p. 1).
Date: September 1934
Creator: Wenzinger, Carl J.
Partner: UNT Libraries Government Documents Department

Resume of Present Data on Load Distribution on Slots and Flaps, Special Report

Description: This report covers a study of the generally available data on load distribution on slots and flaps. The study was made by the National Advisory Committee for Aeronautics at the request of the Material Division, Army Air Corps to furnish information applicable to design criteria for slots and flaps of various types. The data are presented in three main sections: slots (Handley page type), auxiliary airfoils (fixed), and flaps.
Date: April 1934
Creator: Wenzinger, Carl J.
Partner: UNT Libraries Government Documents Department

Wind-Tunnel Investigation of Several Factors Affecting the Performance of a High-Speed Pursuit Airplane With Air-Cooled Radial Engine

Description: Report details an investigation into various potential improvements and modifications to pursuit airplanes. NACA low-drag airfoil sections and their use for reducing drag and increasing compressibility speeds were examined. Other items covered include the propeller slipstream, high-speed cowling arrangement, and placement of wing guns.
Date: November 1941
Creator: Wenzinger, Carl J.
Partner: UNT Libraries Government Documents Department

Wind-Tunnel Tests of a Clark Y Wing Having Split Flaps With Gaps

Description: "Tests were made of the Clark Y wing having split flaps with a gap between the flap and the lower surface of the wing. Lift, drag, and pitching moments were measured for the wing with three different sizes of flap. It was found that any gap between the flap and the wing reduced the lift, the drag, and the pitching moments, but that the center-of-pressure movement and the ratio of lift to drag were little affected" (p. 1).
Date: May 1938
Creator: Wenzinger, Carl J.
Partner: UNT Libraries Government Documents Department

Pressure Distribution Over an NACA 23012 Airfoil With an NACA 23012 External-Airfoil Flap

Description: Report presents the results of pressure-distribution tests of an NACA 23012 airfoil with an NACA 23012 external airfoil flap made in the 7 by 10-foot wind tunnel. The pressures were measured on the upper and lower surfaces at one chord section on both the main airfoil and on the flap for several different flap deflections and at several angles of attack. A test installation was used in which the airfoil was mounted horizontally in the wind tunnel between vertical end planes so that two-dimensional flow was approximated.
Date: 1938
Creator: Wenzinger, Carl J.
Partner: UNT Libraries Government Documents Department

Pressure Distribution Over a Clark Y-H Airfoil Section With a Split Flap

Description: "An investigation was made in the N.A.C.A. 7 by 10 foot wind tunnel of the distribution of air pressure over one chord section of a Clark Y-H airfoil with a split flap. The results obtained are given in the form of diagrams showing the chordwise distribution of pressure on both airfoil and flap as plots of calculated aerodynamic coefficients for both airfoil and flap" (p. 1).
Date: December 1937
Creator: Wenzinger, Carl J.
Partner: UNT Libraries Government Documents Department

Pressure Distribution Over a Thick, Tapered and Twisted Monoplane Wing Model-N.A.C.A. 81-J

Description: "This reports presents the results of pressure distribution tests on a thick, tapered and twisted monoplane wing model. The investigation was conducted for the purpose of obtaining data on the aerodynamic characteristics of the new wing and to provide additional information suitable for use in the design of tapered cantilever wings. The tests included angles of attack up to 90 degrees. The span loading over the wing was approximately of elliptical shape, which gave rise to relatively small bending moments about the root" (p. 97).
Date: May 21, 1930
Creator: Wenzinger, Carl J.
Partner: UNT Libraries Government Documents Department

Pressure Distribution Over an Airfoil Section With a Flap and Tab

Description: Report presents the results of wind tunnel tests made in the NACA 7 by 10-foot wind tunnel of a Clark Y airfoil with a flap and an inset tab. The pressures were measured on both the upper and lower surfaces at one chord section. Calculations were made of the normal-force and pitching-moment coefficients of the airfoil section with flap section with tab, and the normal-force and hinge-moments coefficients of the tab alone.
Date: 1936
Creator: Wenzinger, Carl J.
Partner: UNT Libraries Government Documents Department

The Effect of Wing Tip Floating Ailerons on the Autorotation of a Monoplane Wing Model

Description: "The preliminary tests described here were made to determine the extent to which wing tip floating ailerons might be effective in reducing airplane spinning tendencies. The tests showed that initial spinning tendencies and rates of stable spinning could doubtless be reduced by the use of tip floating ailerons on an airplane. It also appears to be desirable to reduce to a minimum the interference between wing and aileron. This would serve to maintain uniformity of action at all angles of attack and enable calculation of the aileron characteristics" (p. 1).
Date: March 1930
Creator: Knight, Montgomery & Wenzinger, Carl J.
Partner: UNT Libraries Government Documents Department

Tests of Round and Flat Spoilers on a Tapered Wing in the NACA 19-Foot Pressure Wind Tunnel

Description: "Several arrangements of round and flat spanwise spoilers attached to the upper surface of a tapered wing were tested in the NACA 19-foot pressure wind tunnel to determine the most effective type, location, and size of spoiler necessary to reduce greatly the lift on the wings of large flying boats when moored. The effect of the various spoilers on the lift, the drag, and the pitching-moment characteristics of the tapered wing was measured over a range of angles of attack from zero to maximum lift. The most effective type of spoiler was found to be the flat type with no space between it and the wing surface" (p. 1).
Date: March 1941
Creator: Wenzinger, Carl J. & Bowen, John D.
Partner: UNT Libraries Government Documents Department

Wind-Tunnel Investigation of Spoiler, Deflector, and Slot Lateral-Control Devices on Wings With Full-Span Split and Slotted Flaps

Description: Report presents the results of an extensive investigation made in the NACA 7 by 10-foot wind tunnel of spoiler, deflector, and slot types of lateral-control device on wings with full-span split and slotted flaps. The static rolling and yawing moments were determined for all the devices tested, and the static hinge moments and the time response were determined for a few devices of each type.
Date: August 13, 1940
Creator: Wenzinger, Carl J. & Rogallo, Francis M.
Partner: UNT Libraries Government Documents Department

Effect of Length of Handley Page Tip Slots on the Lateral-Stability Factor, Damping in Roll

Description: "Tests have been made in the NACA 7 by 10 foot wind tunnel on a Clark Y wing model equipped with various lengths of Handley Page slots extending inward from the wing tips. The slot lengths tested ranged from 20 to 100 per cent of the semi span. The effect of slot lengths on damping in roll was determined by means of both free-autorotation and forced-rotation test. In addition, the maximum lift coefficient was found with each slot length. The optimum length of slot for satisfactory damping in roll over a large range of angles of attack was found to be slightly over 50 per cent of the semispan for the form of slot tested" (p. 1).
Date: July 1932
Creator: Weick, Fred E. & Wenzinger, Carl J.
Partner: UNT Libraries Government Documents Department

The Characteristics of a Clark Y Wing Model Equipped With Several Forms of Low-Drag Fixed Slots

Description: This investigation was undertaken to develop a low-drag fixed slot for an airplane wing which would avoid the complications and maintenance difficulties of the present movable-type Handley Page slot. Tests were conducted on a series of fixed slots in an attempt to reduce the minimum drag coefficient without decreasing the maximum lift coefficient or the stalling angle of the slotted wing. The tests were made in the NACA 5-foot vertical wind tunnel on a Clark Y basic section having a 10-inch chord.
Date: 1932
Creator: Weick, Fred E. & Wenzinger, Carl J.
Partner: UNT Libraries Government Documents Department

Preliminary Investigation of Rolling Moments Obtained With Spoilers on Both Slotted and Plain Wings

Description: "A wind-tunnel study has been made to determine the possibility of developing spoilers suitable for providing the lateral control for airplanes in place of the usual ailerons. The first tests were made on a model wing with a fixed tip slot, but when it was found that the effectiveness of the spoilers did not depend to any great extent on the slot, tests were made on a plain wing also. In both cases certain spoiler positions were found which were free from the usual adverse rolling moments with small deflections" (p. 1).
Date: April 1932
Creator: Weick, Fred E. & Wenzinger, Carl J.
Partner: UNT Libraries Government Documents Department

Wind-Tunnel Research Comparing Lateral Control Devices, Particularly at High Angles of Attack 9: Tapered Wings With Ordinary Ailerons

Description: Tests were made with ordinary flap-type ailerons on two wings with different amounts of taper, one medium and the other extreme. On each wing both medium sized tapered ailerons and short wide tapered ailerons were tested.
Date: February 1933
Creator: Weick, Fred E. & Wenzinger, Carl J.
Partner: UNT Libraries Government Documents Department

Wind-Tunnel Research Comparing Lateral Control Devices, Particularly at High Angles of Attack 12: Upper-Surface Ailerons on Wings With Split Flaps

Description: "This report covers the twelfth of a series of tests conducted to compare different lateral control devices with particular reference to their effectiveness at high angles of attack. The present wind tunnel tests were made with two sizes of upper-surface ailerons on rectangular Clark Y wing models equipped with full span split flaps. The tests showed the effect of the upper-surface ailerons and of the split flaps on the general performance characteristics of the wings, and on the lateral controllability and stability characteristics" (p. 463).
Date: June 8, 1934
Creator: Weick, Fred E. & Wenzinger, Carl J.
Partner: UNT Libraries Government Documents Department

Wind-Tunnel Research Comparing Lateral Control Devices, Particularly at High Angles of Attack 3: Ordinary Ailerons Rigged Up 10 Degrees When Neutral

Description: This report presents the results of wind-tunnel tests made on three model wings having different sizes of ordinary ailerons rigged up 10 degrees when neutral, the same models having previously been tested with the ailerons rigged even with the wings in the usual manner. One of the wings had ailerons of medium size, 25 per cent of the wing chord by 40 per cent of the semispan, one had long, narrow ailerons, and one had short, wide ones. These tests are part of a general investigation on lateral control devices, with particular reference to the control at high angles of attack, in which all the devices are being subjected to the same series of tests in the 7 by 10 foot wind tunnel of the National Advisory Committee for Aeronautics.
Date: February 5, 1932
Creator: Weick, Fred E. & Wenzinger, Carl J.
Partner: UNT Libraries Government Documents Department

Preliminary wind-tunnel investigation of an NACA 23012 airfoil with various arrangements of venetian-blind flaps

Description: Report presents the results of an investigation made in the NACA 7 by 10-foot wind tunnel of a large-chord NACA 23012 airfoil with several arrangements of venetian-blind flaps to determine the aerodynamic section characteristics as affected by the over-all flap chord, the chords of the slats used to form the flap, the slat spacing, the number of slats and the position of the flap with respect to the wing. Complete section data are given in the form of graphs for all the combinations tested.
Date: January 10, 1939
Creator: Wenzinger, Carl J. & Harris, Thomas A.
Partner: UNT Libraries Government Documents Department

The aerodynamic characteristics of a slotted Clark y wing as affected by the auxiliary airfoil position

Description: From Summary: "Aerodynamic force tests on a slotted Clark Y wing were conducted in a vertical wind tunnel to determine the best position for a given auxiliary airfoil with respect to the main wing. A systematic series of 100 changes in location of the auxiliary airfoil were made to cover all the probable useful ranges of slot gap, slot width, and slot depth. The results of the investigation may be applied to the design of automatic or controlled slots on wings with geometric characteristics similar to the wing tested. The best positions of the auxiliary airfoil were covered by the range of the tests, and the position for desired aerodynamic characteristics may easily be obtained from charts prepared especially for the purpose."
Date: 1932~
Creator: Wenzinger, Carl J. & Shortal, Joseph A.
Partner: UNT Libraries Government Documents Department