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Wind-Tunnel Measurements of Air Loads on Split Flaps

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.

Item Type: Report

Partner: UNT Libraries Government Documents Department

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

"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.

Item Type: Report

Partner: UNT Libraries Government Documents Department

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

"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. … more

Date: September 1934

Creator: Wenzinger, Carl J.

Item Type: Report

Partner: UNT Libraries Government Documents Department

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

"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 … more

Date: September 1933

Creator: Wenzinger, Carl J.

Item Type: Report

Partner: UNT Libraries Government Documents Department

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

"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.

Item Type: Report

Partner: UNT Libraries Government Documents Department

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

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.

Item Type: Report

Partner: UNT Libraries Government Documents Department

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

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.

Item Type: Report

Partner: UNT Libraries Government Documents Department

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

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… more

Date: January 14, 1937

Creator: Wenzinger, Carl J.

Item Type: Report

Partner: UNT Libraries Government Documents Department

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

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-dimensio… more

Date: 1938

Creator: Wenzinger, Carl J.

Item Type: Report

Partner: UNT Libraries Government Documents Department

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Pressure Distribution Over an Airfoil Section With a Flap and Tab

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.

Item Type: Report

Partner: UNT Libraries Government Documents Department

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

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.

Item Type: Report

Partner: UNT Libraries Government Documents Department

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

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, … more

Date: October 25, 1935

Creator: Wenzinger, Carl J.

Item Type: Report

Partner: UNT Libraries Government Documents Department

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

"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 bend… more

Date: May 21, 1930

Creator: Wenzinger, Carl J.

Item Type: Report

Partner: UNT Libraries Government Documents Department

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

"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 … more

Date: March 1930

Creator: Knight, Montgomery & Wenzinger, Carl J.

Item Type: Report

Partner: UNT Libraries Government Documents Department

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Wind-Tunnel Tests on a Series of Wing Models Through a Large Angle of Attack Range Part 1: Force Tests

"This investigation covers force tests through a large range of angle of attack on a series of monoplane and biplane wing models. The tests were conducted in the atmospheric wind tunnel of the National Advisory Committee for Aeronautics. The models were arranged in such a manner as to make possible a determination of the effects of variations in tip shape, aspect ratio, flap setting, stagger, gap, decalage, sweep back, and airfoil profile. The arrangements represented most of the types of wing … more

Date: 1930

Creator: Knight, Montgomery & Wenzinger, Carl J.

Item Type: Report

Partner: UNT Libraries Government Documents Department

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Rolling Moments Due to Rolling and Yaw for Four Wing Models in Rotation

"This report presents the results of a series of autorotation and torque tests on four different rotating wing systems at various rates of roll and at several angles of yaw. The investigation covered an angle of attack range up to 90 degrees and angles of yaw of 0 degree, 5 degrees, 10 degrees, and 20 degrees. The tests were made in a 5-foot, closed-throat atmospheric wind tunnel. The object of the tests was primarily to determine the effects of various angles of yaw on the rolling moments of t… more

Date: August 19, 1930

Creator: Knight, Montgomery & Wenzinger, Carl J.

Item Type: Report

Partner: UNT Libraries Government Documents Department

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Resume of Air-Load Data on Slats and Flaps

"A resume of the generally available test data regarding air loads on slats and flaps is presented and data attained up to the fall of 1938 are included. The data are given in the form of N.A.C.A. standard coefficients of air forces and moments on the lift-increasing device and, when available, the aerodynamic characteristics of the combined wing and high-lift device are included. Slats of the Handley Page type, fixed auxiliary airfoils, and flaps of several different types are covered" (p. 1).

Date: March 1939

Creator: Wenzinger, Carl J. & Rogallo, Francis M.

Item Type: Report

Partner: UNT Libraries Government Documents Department

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

"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 ro… more

Date: July 1932

Creator: Weick, Fred E. & Wenzinger, Carl J.

Item Type: Report

Partner: UNT Libraries Government Documents Department

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

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.

Item Type: Report

Partner: UNT Libraries Government Documents Department

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

"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 … more

Date: April 1932

Creator: Weick, Fred E. & Wenzinger, Carl J.

Item Type: Report

Partner: UNT Libraries Government Documents Department

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Wind Tunnel Research Concerning Lateral Control Devices, Particularly at High Angles of Attack 7: Handley Page Tip and Full-Span Slots With Ailerons and Spoilers

Tests were made with ordinary ailerons and different sizes of spoilers on rectangular Clark Y wing models with Handley Page tip and full span slots. The tests showed the effect of the control devices on the general performance of the wings as well as on the lateral control and lateral stability characteristics.

Date: January 1933

Creator: Weick, Fred E. & Wenzinger, Carl J.

Item Type: Report

Partner: UNT Libraries Government Documents Department

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Wind-Tunnel of Three Lateral-Control Devices in Combination With a Full-Span Slotted Flap on an NACA 23012 Airfoil

"A large-chord NACA 23012 airfoil was tested. The airfoil extended completely across the test section, and two-dimensional flow was approximated. The model was fitted with a full-span slotted flap having a chord 25.66 percent of the airfoil chord. The ailerons investigated extended over the entire span and each had a chord 10 percent of the airfoil chord" (p. 1).

Date: August 1938

Creator: Wenzinger, Carl J. & Bamber, Millard J.

Item Type: Report

Partner: UNT Libraries Government Documents Department

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

"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 li… more

Date: March 1941

Creator: Wenzinger, Carl J. & Bowen, John D.

Item Type: Report

Partner: UNT Libraries Government Documents Department

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Wind Tunnel Pressure Distribution Tests on an Airfoil With Trailing Edge Flap

"This report deals with pressure distribution tests on an airfoil with a conventional trailing edge flap. These tests were conducted in the Atmospheric Wind Tunnel of the National Advisory Committee for Aeronautics. Maximum chord loadings were obtained with the flap displaced downward and with the airfoil at large angles of attack. Greater changes were produced in the normal force and in the center of pressure travel by up-flap than by an equal down-flap displacement" (p. 1).

Date: October 1929

Creator: Wenzinger, Carl J. & Loeser, Oscar, Jr.

Item Type: Report

Partner: UNT Libraries Government Documents Department