203 Matching Results

Search Results

Advanced search parameters have been applied.

Wind-tunnel investigation of effects of tail length on the longitudinal and lateral stability characteristics of a single-propeller airplane model

Description: Report presenting an investigation of a powered model of a single-propeller low-wing airplane with three values of tail length and three horizontal tails to determine the effects of tail length and tail volume on the longitudinal and lateral stability.
Date: December 1948
Creator: Johnson, Harold S.
Partner: UNT Libraries Government Documents Department

Horizontal tail loads in maneuvering flight

Description: From Summary: "A method is given for determining the horizontal tail loads in maneuvering flight. The method is based upon the assignment of a load-factor variation with time and the determination of a minimum time to reach peak load factor. The tail load is separated into various components. Examination of these components indicated that one of the components was so small that it could be neglected for most conventional airplanes; therefore, the number of aerodynamic parameters needed in this computation of tail loads was reduced to a minimum. In order to illustrate the method, as well as to show the effect of the main variables, a number of examples are given. Some discussion is given regarding the determination of maximum tail loads, maximum pitching accelerations, and maximum pitching velocities obtainable."
Date: February 9, 1950
Creator: Pearson, Henry A.; McGowan, William A. & Donegan, James J.
Partner: UNT Libraries Government Documents Department

Horizontal tail loads in maneuvering flight

Description: Report presenting a method for determining the horizontal tail loads in maneuvering flight. The method is based on the assignment of a load-factor variation with time and the determination of a minimum time to reach peak load factor. Consideration is given to the maximum tail loads, maximum pitching accelerations, and maximum pitching velocities obtainable.
Date: April 1950
Creator: Pearson, Henry A.; McGowan, William A. & Donegan, James J.
Partner: UNT Libraries Government Documents Department

Notes on the calculation of the minimum horizontal tail surface for airplanes equipped with wing flaps

Description: A method of calculating the horizontal tail area for an airplane equipped with flaps is presented. The general problem of tail design, the effects of flaps on the factors involved, and the manner in which the flaps change the requirements upon which the minimum horizontal tail area is based are discussed.
Date: April 1937
Creator: Soulé, Hartley A.
Partner: UNT Libraries Government Documents Department

A study of the effects of vertical tail area and dihedral on the lateral maneuverability of an airplane

Description: Report presenting a theoretical investigation of the influence of changes in vertical tail area and dihedral angle on the lateral flying characteristics of an airplane. Lateral motions were computed for nine different combinations of vertical tail area and dihedral. Results regarding the lateral motions due to applied rolling moment with different amounts of accompanying pawing moment and lateral motions due to applied yawing moment are provided.
Date: October 1941
Creator: Fehlner, Leo F.
Partner: UNT Libraries Government Documents Department

Low-speed longitudinal and wake air-flow characteristics at a Reynolds number of 5.5 x 10(exp 6) of a circular-arc 52 degrees sweptback wing with a fuselage and a horizontal tail at various vertical positions

Description: Report presenting an investigation in the 19-foot pressure tunnel to determine the effects of a fuselage and a horizontal tail located at various vertical positions on the low-speed longitudinal characteristics of a circular-arc 52 degree sweptback wing. Results regarding the effect of fuselage on longitudinal characteristics of the wing, effect of tail position on stability and tail effectiveness, and air-flow characteristics are provided.
Date: June 19, 1951
Creator: Foster, Gerald V. & Griner, Roland F.
Partner: UNT Libraries Government Documents Department

Calculation of tab characteristics for flight conditions from wind-tunnel data

Description: Report presenting tail-surface characteristics calculated from wind-tunnel data, which have been reported to not correspond with flight-test measurements. The primary problem under consideration is the calculation of the effect of tab deflection on the free-floating angle of the elevator, as in a servocontrol.
Date: April 1942
Creator: Sears, Richard I.
Partner: UNT Libraries Government Documents Department

A study of several factors affecting the stability contributed by a horizontal tail at various vertical positions on a sweptback-wing airplane model

Description: Report presenting a study in the 19-foot pressure tunnel to determine the effects of fuselage afterbody shape, split flaps, and variations in the span of the leading-edge flaps on the stability contributed by the horizontal tail to an airplane with the wing swept back 42 degrees.
Date: November 1956
Creator: Foster, Gerald V. & Griner, Roland F.
Partner: UNT Libraries Government Documents Department

An approximate spin design criterion for monoplanes

Description: "A quantitative criterion of merit has been needed to assist airplane designers to incorporate satisfactory spinning characteristics into new designs. An approximate empirical criterion, based on the projected side area and the mass distribution of the airplane, has been formulated in a recent British report. In the present paper, the British results have been analyzed and applied to American designs. A simpler design criterion based solely on the type and the dimensions of the tail, has been developed: it is useful in a rapid estimation of whether a new design is likely to comply with the minimum requirements for safety in spinning" (p. 1).
Date: June 1939
Creator: Seidman, Oscar & Donlan, Charles J.
Partner: UNT Libraries Government Documents Department

Some theoretical considerations of longitudinal stability in power-on flight with special reference to wind-tunnel testing

Description: Report presenting a consideration of some problems related to longitudinal stability in power-on flight. The results indicated that the destabilizing effects of power are more pronounced when the horizontal tail is required to carry a down load to maintain flight equilibrium.
Date: November 1942
Creator: Donlan, Charles J.
Partner: UNT Libraries Government Documents Department

Effect of changes in tail arrangement upon the spinning of a low-wing monoplane model

Description: "A series of tests was made in the N.A.C.A. free spinning tunnel to find the effect upon spinning characteristics of systematic changes in tail arrangement. The tests were made with a 1/16-scale made of a low-wing monoplane of modern design. The changes consisted of: (1) variation of the fuselage length; (2) variation of the fore-and-aft location of the vertical surfaces; and (3) variation of the vertical location of the horizontal surfaces. The spinning characteristics of the model, including the number of turns required for recovery, were found to vary systematically and regularly with systematic changes in the tail arrangement" (p. 1).
Date: June 1936
Creator: Zimmerman, C. H.
Partner: UNT Libraries Government Documents Department

Collection and analysis of wind-tunnel data on the characteristics of isolated tail surfaces with and without end plates

Description: Report presenting the aerodynamic characteristics of 19 isolated tail surfaces, which have been determined by wind tunnel tests. Testing was also made of rectangular airfoils of various aspect ratios with and without double end plates of various shapes. The analysis indicated that the slope of the lift curve could be predicted within 10 percent for all models by use of lifting-surface-theory equations.
Date: May 1947
Creator: Bates, William R.
Partner: UNT Libraries Government Documents Department

Investigation at high subsonic speeds of the static lateral and directional stability and tail-loads characteristics of a model having a highly tapered swept wing of aspect ratio 3 and two horizontal-tail positions

Description: Report presenting an investigation made in the 7- by 10-foot tunnel of the static lateral and directional stability and some tail-load characteristics of a model with a highly tapered swept wing and two horizontal-tail positions. Testing were made with the horizontal tail located at the tip of the swept vertical tail and with the horizontal tail located in the wing-chord plane extended. Results regarding static lateral and directional stability and vertical-tail loads are provided.
Date: September 11, 1956
Creator: Few, Albert G., Jr.
Partner: UNT Libraries Government Documents Department

Lateral-control investigation at transonic speeds of differentially deflected horizontal-tail surfaces for a configuration having a 6-percent-thick 45 degree sweptback wing

Description: Report presenting an investigation in the 16-foot transonic tunnel to determine the lateral-control effectiveness of differentially deflected horizontal-tail surfaces mounted behind a 45 degree sweptback wing-fuselage combination. The effectiveness of the differentially deflected horizontal tail as a lateral-control device was found to be essentially independent of angle of attack and Mach number even in the transonic region. Results regarding the effects of differential deflection of horizontal-tail surfaces and effects of the vertical tail are provided.
Date: November 15, 1955
Creator: Critzos, Chris C.
Partner: UNT Libraries Government Documents Department

Wind-tunnel investigation of a section of the horizontal tail surface for the Bell XP-63 airplane

Description: Report presenting force tests conducted on a model of a section of the XP-63 horizontal tail surface in the 4- by 6-foot closed-throat vertical wing tunnel. The angle-of-attack range was from the negative to the positive stall for all flap deflections.
Date: August 1941
Creator: Ames, Milton B., Jr. & Hoggard, H. Page, Jr.
Partner: UNT Libraries Government Documents Department

Transient effects of the wing wake on the horizontal tail

Description: "An investigation was made of the effect of the wing wake on the lift of the horizontal tail surfaces. In the development of expressions for this effect, the growth of wing circulation and wing wake, the time interval represented by the tail length, and the development of lift by the rail were considered. The theory has been applied to a specific case to show the magnitude of the effect to be expected. It is shown that, for motions below a certain frequency, the development of lift by the tail may be represented by a simple lag function. The lag is, however, somewhat greater than that indicated by the rail length" (p. 1).
Date: August 1940
Creator: Jones, Robert T. & Fehlner, Leo F.
Partner: UNT Libraries Government Documents Department

Pressure-distribution measurements on a full-scale horizontal tail surface for a Mach number range of 0.20 to 0.70

Description: Report presenting testing of a full-scale, semispan, horizontal tail surface for a jet-propelled fighter airplane in the 16-foot high-speed tunnel to determine the variation of the chordwise and spanwise pressure distributions with Mach number. Surface irregularities were found to cause appreciable distortion of the pressure distribution. Results regarding chordwise distributions, spanwise distribution, effect of Mach number on root bending moment, and estimated critical Mach numbers are provided.
Date: June 25, 1947
Creator: Schueller, Carl F.
Partner: UNT Libraries Government Documents Department

A theoretical investigation of the aerodynamics of wing-tail combinations performing time-dependent motions at supersonic speeds

Description: Report presenting a theoretical investigation of the contribution of horizontal tails to the lift and pitching moment due to angle of attack, a constant rate of pitch, and a constant vertical acceleration. Methods for calculating the flow fields behind wings with constant vertical acceleration are developed.
Date: May 1954
Creator: Martin, John C.; Diederich, Margaret S. & Bobbitt, Percy J.
Partner: UNT Libraries Government Documents Department

An experimental study of the zero-angle-of attack transonic drag associated with the vertical position of a horizontal tail at zero incidence

Description: Report presenting a study of the transonic drag associated with varying the vertical location of the horizontal tail of a representative tail-body combination. Factors which significantly influenced the results were flow separation in the horizontal tail-body juncture, afterbody-tail-interference pressure drag, and a downwash over the horizontal tail which resulted from the boundary conditions of the converging afterbody.
Date: October 25, 1956
Creator: Howell, Robert R.
Partner: UNT Libraries Government Documents Department

Characteristics of beveled-trailing-edge elevators on a typical pursuit fuselage at altitudes simulating-normal flight and spin conditions

Description: Report presenting lift and elevator hinge-moment characteristics were measured on horizontal tail provided with elevators having three different beveled trailing edges. Results regarding fuselage alone and fuselage interference, lift characteristics of fuselage-tail combination, elevator hinge-moment characteristics, drag, and comparison with data from two-dimensional-flow tests are provided.
Date: December 1942
Creator: Gillis, Clarence L.
Partner: UNT Libraries Government Documents Department

Two practical methods for the calculation of the horizontal tail area necessary for a statically stable airplane

Description: From Summary: "This report is concerned with the problem of calculation of the horizontal tail area necessary to give a statically stable airplane. Two entirely different methods are developed, and reduced to simple formulas easily applied to any design combination. Detailed instructions are given for use of the formulas, and all calculations are illustrated by examples. The relative importance of the factors influencing stability is also shown."
Date: 1929
Creator: Diehl, Walter S.
Partner: UNT Libraries Government Documents Department

Calculated subsonic span loads and resulting stability derivatives of unswept and 45 degrees sweptback tail surfaces in sideslip and in steady roll

Description: Report presenting a calculation of subsonic span loads and the resulting stability derivatives for a systematic series of vertical- and horizontal-tail combinations in sideslip and in steady roll in order to provide information embracing a wide range of probable tail configurations. The results of this investigation, which had a wide range of geometric variables than previous studies, showed trends which were in general agreement with the results of previous investigations.
Date: October 1954
Creator: Queijo, M. J. & Riley, Donald R.
Partner: UNT Libraries Government Documents Department

Effects of vertical fins near the nose of the fuselage on the directional and damping-in-yaw stability derivatives of an airplane model under steady-state and oscillatory conditions

Description: A wind-tunnel investigation has been made at low speed to determine the effects of vertical fins placed ahead of the vertical tail on the directional stability and damping-in-yaw characteristics of a swept-wing model under steady-state oscillatory conditions. Various sizes of fins were used above and below the fuselage center line. The vertical-tail size also was varied.
Date: December 1956
Creator: Queijo, M. J. & Wells, Evalyn G.
Partner: UNT Libraries Government Documents Department