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Control characteristics of trailing-edge spoilers on untapered blunt trailing-edge wings of aspect ratio 2.7 with 0 degree and 45 degrees sweepback at Mach numbers of 1.41 and 1.96

Description: Report presenting an investigation in the supersonic blowdown tunnel to determine the control characteristics of full-span trailing-edge spoilers on two related full-blunt wings with the same aspect ratio but differing angles of sweepback. A similar unswept wing that was larger and had a partially blunt trailing edge was also tested with a full-span trailing-edge spoiler. Results regarding the lift, rolling-moment, and pitching-moment coefficients for unswept wings, the 45-degree sweptback wing, and a comparison of spoiler data with flap data are provided.
Date: December 3, 1952
Creator: Jacobsen, Carl R.
Partner: UNT Libraries Government Documents Department

Characteristics of flap-type spoiler ailerons at various locations on a 60 degree delta wing with a double slotted flap

Description: Report presenting a low-speed wind-tunnel investigation to determine the static lateral control characteristics of flap-type spoiler ailerons on a thin delta wing equipped with a double slotted flap. A spoiler located on the flap gave rolling-moment coefficients that varied fairly linearly with spoiler projects and with about the same magnitude for either the flap-retracted or flap-deflected position.
Date: December 18, 1952
Creator: Croom, Delwin R.
Partner: UNT Libraries Government Documents Department

Evaluation of a fixed spoiler as a gust alleviator

Description: Report presenting an investigation in the gust tunnel to determine the effectiveness of a fixed spoiler, forwardly located on the upper surface of a wing, in reducing the loads imposed on airplanes in flight through gusty air. Testing occurred through a sharp-edge and a gradient gust with and without spoilers. The results indicate that the model has roughly the same maximum acceleration with and without spoilers in a sharp-edge gust.
Date: November 1948
Creator: Mickleboro, Harry C.
Partner: UNT Libraries Government Documents Department

Preliminary investigation of spoiler lateral control on a 42 degree sweptback wing at transonic speeds

Description: Investigation at transonic speeds in the high-speed 7- by 10-foot tunnel to determine the rolling-effectiveness characteristics of a spoiler on a double-wedge-type semispan wing with a sweepback angle of 42 degrees. Results regarding the variation of rolling-moment coefficient, spoiler effectiveness, and rolling effectiveness are provided.
Date: August 12, 1947
Creator: Schneiter, Leslie E. & Ziff, Howard L.
Partner: UNT Libraries Government Documents Department

Results of an investigation at high subsonic speeds to determine lateral-control and hinge-moment characteristics of a spoiler-slot-deflector configuration on a 35 degree sweptback wing

Description: Report presenting an investigation in the high speed 7- by 10-foot tunnel through a range of Mach numbers to determine the lateral-control and hinge-moment characteristics of a spoiler-slot-deflector configuration on a semispan 35 degree sweptback-wing model. The results indicated that the spoiler-slot-deflector configuration with the ratio of deflector projection to spoiler projection increasing with increasing control projection has good rolling-moment effectiveness throughout the angle of attack range and throughout the high subsonic speed range.
Date: June 5, 1957
Creator: Hammond, Alexander D. & Brown, Albert E.
Partner: UNT Libraries Government Documents Department

Wind-tunnel investigation of the effect of aspect ratio and chordwise location on effectiveness of plain spoilers on thin untapered wings at transonic speeds

Description: From Summary: "A wind-tunnel investigation has been made in the Langley high-speed 7- by 10-foot wind tunnel by use of the transonic-bump technique to study the effectiveness of spoiler-type controls on 9 unswept untapered wings. Full-span spoilers, projected to 7.5 percent wing chord along the 40-, 60-, 80-, and 100-percent wing chord lines, were tested on wings of aspect ratio 1 to 6 at Mach numbers from 0.6 to 1.10. Most of the data are presented without analysis."
Date: September 26, 1956
Creator: Hammond, Alexander D.
Partner: UNT Libraries Government Documents Department

Lateral-control characteristics of various spoiler arrangements as measured in flight

Description: Report presenting an investigation of the lateral-control characteristics of several spoiler arrangements located near the wing trailing edge in flight. In all cases, the control response was satisfactory and the variation of rolling effectiveness with control deflections was smooth and nearly linear. Results regarding response characteristics, rolling effectiveness, control-force and hinge-moment characteristics, yawing characteristics, effects of altitude, characteristics near the stall, and characteristics in inverted flight are provided.
Date: January 1947
Creator: Spahr, J. Richard
Partner: UNT Libraries Government Documents Department

An Additional Investigation of the High-Speed Lateral-Control Characteristics of Spoilers

Description: Report presenting an investigation of the characteristics of partial-span spoilers located at 0.75 of the chord on an NACA 66-series tapered wing, especially at high speeds. The effect of small spoiler projections was found to increase with an increase in speed until the critical Mach number was exceeded.
Date: June 1945
Creator: Laitone, Edmund V. & Summers, James L.
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

An Investigation at Subsonic Speeds of the Rolling Effectiveness of a Small Perforated Spoiler on a Wing Having 45 Degrees of Sweepback

Description: Memorandum presenting an investigation of the rolling effectiveness of a partial-span, perforated spoiler on a wing with 45 degrees of sweepback at Mach numbers from 0.25 to 0.96. The effects of the spoiler on the lift, drag, and pitching moment were also determined. Results regarding Reynolds number, Mach number, and predicted rate of roll are provided.
Date: September 15, 1952
Creator: Bandettini, Angelo
Partner: UNT Libraries Government Documents Department

The Effect of a 4-Percent-High Spoiler on Buffeting Forces on a NACA 65(Sub 06)A004 Two-Dimensional Airfoil at Subsonic Mach Numbers

Description: Memorandum presenting testing of an NACA 65(sub 06)A004 airfoil to determine the effects of a solid-strip spoiler on buffeting forces. Fluctuations of both section normal-force coefficient and of section pitching-moment coefficient are presented as functions of angle of attack and of section normal-force coefficient. Generally, the spoiler decreased the fluctuating section normal-force and pitching-moment coefficients if comparison is made at constant angle of attack and increased these coefficients if comparison is made at constant section normal-force coefficient.
Date: March 23, 1955
Creator: Mellenthin, Jack A.
Partner: UNT Libraries Government Documents Department

Effects of Span and Spanwise and Chordwise Location on the Control Effectiveness of Spoilers on a 50 Degree Sweptback Wing at Mach Numbers of 1.41 and 1.96

Description: Memorandum presenting an investigation in the supersonic blowdown tunnel to determine the effects of span and spanwise and chordwise location on the control characteristics of spoilers on a 6-percent-thick, 50 degrees sweptback wing of aspect ratio 2.5 and taper ratio of 0.625. The results of the investigation indicate that the inboard spoilers located at the rearward chordwise station produce the highest rolling-moment effectiveness.
Date: April 8, 1953
Creator: Kindell, William H.
Partner: UNT Libraries Government Documents Department

Investigation of Effect of Span, Spanwise Location, and Chordwise Location of Spoilers on Lateral Control Characteristics of a Tapered Wing

Description: Note presenting a wind-tunnel investigation of the effect of span, spanwise location, and chordwise location of spoilers on the lateral control characteristics of an unflapped semispan wing equipped with a simple spoiler with a projection 5 percent of the chord. The chordwise investigation involved moving a 50-percent-semispan spoiler from the 50-percent-chord station to the 80-percent-chord station. Results regarding the plain-wing characteristics, spanwise investigation, and chordwise investigation are provided.
Date: May 1947
Creator: Fischel, Jack & Tamburello, Vito
Partner: UNT Libraries Government Documents Department

Investigation of spoilers at a Mach number of 1.93 to determine the effects of height and chordwise location on the section aerodynamic characteristics of a two-dimensional wing

Description: Report presenting an investigation of spoilers at a Mach number of 1.93 to determine the effects of height and chordwise location on the section pressure distributions and section aerodynamic characteristics of a two-dimensional, 6-percent-thick symmetrical wing. Spoilers of three different heights were tested at three different chordwise locations. Results regarding pressure distributions, aerodynamic characteristics, and shock boundary-layer interaction are provided.
Date: February 1958
Creator: Mueller, James N.
Partner: UNT Libraries Government Documents Department

Low-speed investigation of the effect of several flap and spoiler ailerons on the lateral characteristics of a 47.5 degree sweptback-wing-fuselage combination at a Reynolds number of 4.4. x 10(6)

Description: Report presenting an investigation of the low-speed lateral characteristics of a 47.5 degree sweptback-wing-fuselage combination with several flap and spoiler aileron arrangements. Results regarding aileron control characteristics, spoiler-control characteristics, and a comparison of the two are provided.
Date: December 8, 1950
Creator: Pasamanick, Jerome & Sellers, Thomas B.
Partner: UNT Libraries Government Documents Department

Aerodynamic loadings associated with swept and unswept spoilers on a flat-plate at Mach numbers of 1.61 and 2.01

Description: Report presenting an investigation at two Mach numbers to examine the flow, force, and moment characteristics associated with spoilers mounted on a flat plate at a range of sweep angles. Pressure measurements were obtained over the plate and spoiler faces. The pressures were integrated to determine the spoiler lift, pitching-moment, drag, and hinge-moment characteristics.
Date: March 12, 1956
Creator: Lord, Douglas R. & Czarnecki, K. R.
Partner: UNT Libraries Government Documents Department

Data on spoiler-type ailerons

Description: Report presenting information about spoiler-type ailerons, which are of interest because they give high reversal speeds for the thin, flexible wings now used. A bibliography on spoiler-type controls is also provided.
Date: October 28, 1953
Creator: Lowry, John G.
Partner: UNT Libraries Government Documents Department

Effects of spoiler on airfoil pressure distribution and effects of size and location of spoilers on the aerodynamic characteristics of a tapered unswept wing of aspect ratio 2.5 at a Mach number of 1.90

Description: Report presenting an investigation in the supersonic blowdown tunnel of spoilers on two unswept wing arrangements at Mach numbers of 1.90 and 1.96. The effect of pressure-distribution tests on an unswept airfoil in the presence of a fuselage but without tip effects indicated that spoilers could be oppositely deflected in a manner similar to flap-type ailerons to obtain roll effectiveness without loss in lift. Results regarding force and moment tests are also provided.
Date: January 24, 1951
Creator: Conner, D. William & Mitchell, Meade H., Jr.
Partner: UNT Libraries Government Documents Department

Wind-tunnel investigation at high subsonic speeds of spoilers of large projection on an NACA 65A006 wing with quarter-chord line swept back 32.6 degrees

Description: Report presenting an investigation in the high-speed tunnel for a range of Mach numbers to determine the effects of spoiler projection on the aerodynamic characteristics of a wing-fuselage a sweptback quarter-chord line. Lift, drag, rolling, pitching, and yawing moments of the model with a wing panel equipped with 50-percent-semispan inboard spoilers located at the 70-percent-chord line.
Date: January 17, 1952
Creator: Vogler, Raymond D.
Partner: UNT Libraries Government Documents Department

Low-speed tests of a model simulating the phenomenon of control-surface buzz

Description: Report presenting low-speed tests of an airfoil model with a freely hinged flap attached to spoilers which passed through slots in the airfoil ahead of the hinge line. Testing indicated that buzz is not caused simply by buffeting of a flap by separated flow. Results regarding the oscillations experienced with the spoiler and flap in several positions are provided.
Date: August 16, 1950
Creator: Phillips, William H. & Adams, James J.
Partner: UNT Libraries Government Documents Department

Low-subsonic investigation to determine the chordwise pressure distribution and effectiveness of spoilers on a thin, low-aspect-ratio, unswept, untapered, semispan wing and on the wing with leading and trailing-edge flaps

Description: Report presenting an investigation in the 300 mph 7- by 10-foot tunnel to determine the effect of spoilers on the static longitudinal and lateral aerodynamic characteristics and the chordwise pressure distribution on a thin, untapered, unswept, semispan wing with an aspect ratio of 3.33 and NACA 65A004 airfoil sections. Results are presented in the form of static longitudinal and lateral aerodynamic characteristics and tabulated pressure coefficients, section normal-force coefficients, and section pitching-moment coefficients.
Date: April 23, 1958
Creator: Croom, Delwin R.
Partner: UNT Libraries Government Documents Department

Experimental investigation of the oscillating forces and moments on a two-dimensional wing equipped with an oscillating circular-arc spoiler

Description: Report presenting an investigation in the flutter research tunnel to determine the oscillating forces and moments on a two-dimensional wing equipped with an oscillating circular-arc spoiler. The study indicated that force and moment coefficients and their phase angles are affected by Reynolds number, Mach number, and reduced frequency.
Date: January 12, 1954
Creator: Clevenson, Sherman A. & Tomassoni, John E.
Partner: UNT Libraries Government Documents Department

Rocket-model investigation of the rolling effectiveness of a fighter-type wing-control configuration at Mach numbers from 0.6 to 1.5

Description: Report presenting an investigation of the rolling effectiveness of spoiler and aileron aerodynamic controls on a fighter-type airplane from Mach numbers 0.6 to 1.5. No effects of mutual interference between the spoiler and aileron were detectable. Results regarding drag and the effect of gap upon spoiler performance are also provided.
Date: February 25, 1952
Creator: Strass, H. Kurt & Marley, Edward T.
Partner: UNT Libraries Government Documents Department

Wind-tunnel tests of spoilers on tail surfaces

Description: Report presenting wind-tunnel testing in two-dimensional and three-dimensional flow to investigate the aerodynamic characteristics of spoilers on tail surfaces for low-speed flight. Test results indicated that spoilers on tail surfaces showed little possibility of replacing conventional control surfaces. Results regarding a flap alone, rear spoiler alone, forward spoiler alone, forward spoiler and flap, and a combination of forward and rear spoilers on upper and lower surfaces in both types of flow are provided.
Date: August 1945
Creator: Liddell, Robert B.
Partner: UNT Libraries Government Documents Department