471 Matching Results

Search Results

Advanced search parameters have been applied.

A Theoretical Investigation of the Rolling Oscillations of an Airplane With Ailerons Free

Description: "An analysis is made of the stability of an airplane with ailerons free, with particular attention to the motions when the ailerons have a tendency to float against the wind. The present analysis supersedes the aileron investigation contained in NACA Technical Report no. 709. The equations of motion are first written to include yawing and sideslipping, and it is demonstrated that the principal effects of freeing the ailerons can be determined without regard to these motions" (p. 255).
Date: November 19, 1943
Creator: Cohen, Doris
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 Induction Factor Used for Computing the Rolling Moment Due to the Ailerons

Description: In the following note, prepared for the National Advisory Committee for Aeronautics, this induction factor is determined from the result of a model test, and compared with a formula recently developed by the author. The two results are found to be in substantial agreement.
Date: April 1924
Creator: Munk, Max M.
Partner: UNT Libraries Government Documents Department

Determination of the Effect of Wing Flexibility on Lateral Maneuverability and a Comparison of Calculated Rolling Effectiveness With Flight Results

Description: Report presenting an analysis which shows that, when account is taken of sideslip and wing flexibility, the calculated rolling maneuverability of an airplane is in good agreement with the results obtained from flight tests. The method used avoids the complications of successive approximations but is nevertheless believed to be more nearly accurate than other methods based on semirigid-wing assumptions. The method is applied to a wing of tubular shell construction and the procedure is illustrated for a modern pursuit airplane.
Date: January 1944
Creator: Harmon, Sidney M.
Partner: UNT Libraries Government Documents Department

Free-flight investigation at Mach numbers between 0.5 and 1.7 of the zero-lift rolling effectiveness and drag of various surface, spoiler, and jet controls on an 80 degree delta-wing missile

Description: Report presenting a free-flight investigation of the zero-lift rolling effectiveness and drag of 18 roll-control arrangements on a cruciform 80 degree delta-wing missile-like configuration over a range of Mach numbers. Testing was made of deflected surfaces, spoilers, and inlet-air-jet devices to give evidence to simple theory for deflected surfaces and to determine some effects of chordwise location for spoilers and blowing direction and spanwise location for jets near the wing trailing edge. All controls were found to be satisfactory roll-producing devices except canards located immediately forward of the main wings and spoilers.
Date: November 29, 1956
Creator: Schult, Eugene D.
Partner: UNT Libraries Government Documents Department

Some characteristics of roll controls having possible application to fin-stabilized ammunition

Description: Report presenting a discussion of the rolling effectiveness of deflected fins, flaps, spoilers, and jet devices that can be used on fin-stabilized ammunition. The possible applications and some of the significant factors affecting the performance of each device are described. The selection of one control over another appears to be mostly designer's choice with some exceptions depending on the roll requirements in a given situation.
Date: March 27, 1957
Creator: Schult, Eugene D.
Partner: UNT Libraries Government Documents Department

Aerodynamic characteristics of the X-15/B-52 combination

Description: Report presenting an investigation to determine the carry loads and mutual aerodynamic interference effects from high-speed wind-tunnel tests and the drop characteristics of the X-15 through the B-52 flow field from low-speed dynamic-model drop tests and six-degree-of-freedom calculations. The X-15 installation was found to increase drag at cruise conditions by approximately 15 percent.
Date: 1948
Creator: Alford, William J., Jr. & Taylor, Robert T.
Partner: UNT Libraries Government Documents Department

Free-flight investigation at transonic and supersonic speeds of the rolling effectiveness of a partial-span aileron on an inversely tapered sweptback wing

Description: Report presenting an investigation of the rolling effectiveness at transonic and supersonic speeds of an inversely tapered sweptback wing with a 10-percent-thick cambered airfoil section and outboard partial-span controls made by means of rocket-propelled test vehicles.
Date: May 1, 1950
Creator: Strass, H. Kurt; Fields, E. M. & Schult, E. D.
Partner: UNT Libraries Government Documents Department

Low-speed yawed-rolling characteristics and other elastic properties of a pair of 40-inch-diameter, 14-ply-rating, type VII aircraft tires

Description: Report presenting the low-speed yawed-rolling characteristics of two 40 x 12, 14-ply-rating, type VII aircraft under straight-yawed rolling over a range of inflation pressures and yaw angles for two vertical loadings. Static testing was performed to determine the vertical, lateral, torsional, and fore-and-aft elastic characteristics of tires. Measured lateral and torsional spring constants appeared to decrease with increasing amplitude of tire lateral distortion or twist.
Date: January 1958
Creator: Horne, Walter B. & Smiley, Robert F.
Partner: UNT Libraries Government Documents Department

Free-flight measurements of some effects of aileron span, chord, and deflection and of wing flexibility on the rolling effectiveness of ailerons on sweptback wings at Mach numbers between 0.8 and 1.6

Description: Report presenting a free-flight investigation to determine some effects of aileron span and deflection on the rolling effectiveness of plain, sealed, 15-percent- and 30-percent-chord flap-type ailerons through a range of Mach numbers. Wings of different degrees of torsional flexibility were tested and the results were extended to estimate rigid-wing rolling-effectiveness of all aileron configurations tested.
Date: January 24, 1952
Creator: Schult, Eugene D.; Strass, H. Kurt & Fields, E. M.
Partner: UNT Libraries Government Documents Department

Summary of some rocket-model investigations of effects of wing aspect ratio and thickness on aileron rolling effectiveness including some effects of spanwise aileron location for sweptback wings with aspect ratio of 8

Description: Report presenting the rolling effectiveness of 0.2-chord, trailing-edge ailerons on high-aspect-ratio sweptback wings over a range of Mach numbers. Some effects of spanwise aileron location on rolling effectiveness were measured by testing ailerons on the inboard half, the outboard half, and the full length of the exposed wings.
Date: February 17, 1954
Creator: Strass, H. Kurt
Partner: UNT Libraries Government Documents Department

Low-speed static lateral and rolling stability characteristics of a series of configuration composed of intersecting triangular plan-form surfaces

Description: Report presenting the static lateral and rolling stability derivatives of a series of cruciform, inverted T-, V-, and Y-configurations composed of low-aspect-ratio triangular surfaces at low speed in the rolling-flow test section. Comparisons have been made to indicate the extent of agreement between experiment and existing theory. Results regarding sideslip characteristics and steady rolling characteristics are provided.
Date: October 1955
Creator: Thomas, David F., Jr.
Partner: UNT Libraries Government Documents Department

Approximate method for calculating motions in angles of attack and sideslip due to step pitching- and yawing-moment inputs during steady roll

Description: Report presenting an extension of a method for calculating motions in angles of attack and sideslip resulting from a trim angle of attack and steady rolling velocity to the condition of pitching- and yawing-moment inputs. The resulting formulas are intended primarily for rolling-velocity conditions in which rolling divergence is not encountered.
Date: September 1958
Creator: Moul, Martin T. & Brennan, Teresa R.
Partner: UNT Libraries Government Documents Department

Effect of taper ratio on the low-speed rolling stability derivatives of swept and unswept wings of aspect ratio 2.61

Description: Results of tests conducted in the 6-foot-diameter rolling-flow test section of the Langley stability tunnel to determine the effects of varying taper ratio on the rolling and static stability characteristics of a swept wing are presented; results are also given for the effects of varying taper ratio on an unswept wing and for the effects of sweep on a tapered wing. All the models were of aspect ratio 2.61 and had NACA 0012 sections normal to the quarter-chord line. Taper ratios of 1.00, 0.50, and 0.25 and sweep angles of 0 degrees and 45 degrees were investigated.
Date: November 1951
Creator: Brewer, Jack D. & Fisher, Lewis R.
Partner: UNT Libraries Government Documents Department

Free-flight investigation to determine some effects of tail damping and wing-tail interference on the rolling effectiveness of ailerons and a spoiler on a modified-delta wing at Mach numbers from 0.6 to 1.5

Description: Report presenting an investigation to determine some effects of tail damping and wing-tail interference on the rolling effectiveness of ailerons and a spoiler on a modified-delta wing. Results regarding the effect of adding fixed tail surfaces, effect of moving the horizontal tail out of the plane of the wing, and a comparison with theory are provided.
Date: May 10, 1957
Creator: English, Roland D.
Partner: UNT Libraries Government Documents Department

A Simplified Method for Assessing the Effect of Steady Rolling on Angle of Attack and Sideslip

Description: Report presenting a method for analyzing the effects of inertia and aerodynamic cross-coupling on the response of airplanes in rolling maneuvers. The method is based on the concept that variations in the calculated steady-state angle of attack and sideslip with roll rate give a measure of the onset and degree of roll coupling. An evaluation of this concept from several different perspectives is also provided.
Date: January 17, 1957
Creator: Schmidt, Stanley F.; Bergrun, Norman R.; Merrick, Robert B. & Matthews, Howard F.
Partner: UNT Libraries Government Documents Department

The effect of torsional flexibility on the rolling characteristics at supersonic speeds of tapered unswept wings

Description: From Summary: "An analysis is presented of the effect of torsional flexibility on the rolling characteristics at supersonic speeds of tapered unswept wings with partial-span constant-percent-chord ailerons extending inboard from the wing tip. The geometric variables considered are aspect ratio, taper ratio, aileron span, and aileron chord. The shape of the wing-torsional-stiffness curve is assumed and the twisting moment is considered to result solely from the pressure distribution caused by aileron deflection, so that the necessity of using a successive-approximation method is avoided."
Date: March 8, 1949
Creator: Tucker, Warren A. & Nelson, Robert L.
Partner: UNT Libraries Government Documents Department

Wing-tunnel investigation at low transonic speeds of the effects of number of wings on the lateral-control effectiveness of an RM-5 test vehicle

Description: Report presenting an investigation to determine the effects of number of wings on the aileron rolling effectiveness of an RM-5 test vehicle using the free-rolling wind-tunnel testing technique through a speed range to Mach number 0.9. The wings tested had neither taper nor sweepback and were equipped with full-span 20-percent-chord sealed and faired ailerons. Results indicated that increasing the number of wings resulted in a decrease in rolling effectiveness so that results obtained from the test of the three-wing model were closer to conventional-airplane-configuration results than the four-wing data.
Date: November 29, 1949
Creator: Johnson, Harold S.
Partner: UNT Libraries Government Documents Department

Preliminary Free-Flight Investigation of the Effect of Airfoil Section on Aileron Rolling Effectiveness at Transonic and Supersonic Speeds

Description: "Results have been obtained by means of a free-flight technique utilizing rocket propulsion which indicate that aileron-rolling-effectiveness characteristics are affected adversely by variations in airfoil section which procedure large increases in the trailing-edge angle" (p. 1).
Date: June 25, 1948
Creator: Sandahl, Carl A.
Partner: UNT Libraries Government Documents Department

A System for Measuring the Dynamic Lateral Stability Derivatives in High-Speed Wind Tunnels

Description: Report presenting a description of a two-degree-of-freedom system that forces rolling oscillations. Details of the system, the theory, and the method of operation are discussed. Results indicated that the quantities related to the primary mode of operation of the system could be obtained satisfactorily.
Date: December 1954
Creator: Lessing, Henry C.; Fryer, Thomas B. & Mead, Merrill H.
Partner: UNT Libraries Government Documents Department

Rolling Effectiveness of a Thin Tapered Wing Having Partial-Span Ailerons as Determined by Rocket-Powered Test Vehicles

Description: "The rolling effectiveness of a thin, tapered, and essentially unswept wing having outboard partial-span plain ailerons has been determined by means of rocket-powered test vehicles. The rolling power decreased abruptly in the Mach number range from 0.85 to 0.95 and more gradually at higher speeds. At the maximum Mach number of the tests (1.95), the rolling effectiveness was only 20 percent of that at a Mach number of 0.85" (p. 1).
Date: May 23, 1950
Creator: Sandahl, Carl A. & Strass, H. Kurt
Partner: UNT Libraries Government Documents Department

Wind-Tunnel Investigation to Determine the Aerodynamic Characteristics in Steady Roll of a Model at High Subsonic Speeds

Description: Report presenting aerodynamic characteristics in steady roll on a complete model and its component parts. The model consisted of a wing and horizontal tail with a 45 degree sweepback at the quarter-chord line, a taper ratio of 0.6, an aspect ratio of 4, and NACA 65A006 airfoil sections parallel to the plane of symmetry. Results regarding rolling moment due to rolling, yawing moment due to rolling, and lateral force due to rolling are provided.
Date: January 21, 1953
Creator: Kuhn, Richard E. & Wiggins, James W.
Partner: UNT Libraries Government Documents Department

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

Description: "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 the rotating wings up to large angles of attack" (p. 301).
Date: August 19, 1930
Creator: Knight, Montgomery & Wenzinger, Carl J.
Partner: UNT Libraries Government Documents Department

Low-Speed Roll Effectiveness of a Differentially Deflected Horizontal-Tail Surface on a 42 Degree Swept-Wing Model

Description: Memorandum presenting an investigation to determine the roll effectiveness of a differentially deflected horizontal tail of a 42 degree swept-wing model. The model was tested through an angle-of-attack range of 0 degrees through the stall in the clean and landing configurations with the horizontal tail in a low position. Results regarding the longitudinal characteristics and lateral characteristics are provided.
Date: June 19, 1956
Creator: Boisseau, Peter C.
Partner: UNT Libraries Government Documents Department