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Investigations of Lateral Stability of a Glide Bomb Using Automatic Control Having No Time Lag

Description: The investigation of the lateral stability of an automatically controlled glide bomb led also to the attempt of clarifying the influence of a phugoid oscillation or of any general longitudinal oscillation on the lateral stability of a glide bomb. Under the assumption that its period of oscillation considerably exceeds the rolling and yawing oscillation and that c(sub a) is, at least in sections, practically constant, the result of this test is quite simple. It becomes clear that the influence of the phugoid oscillation may be replaced by suitable variation of the rolling-yawing moment on a rectilinear flight path instead of the phugoid oscillation.
Date: August 1950
Creator: Sponder, E. W.
Partner: UNT Libraries Government Documents Department

Investigations on the Stability, Oscillation, and Stress Conditions of Airplanes with Tab Control: First Partial Report. Derivation of the Equations of Motion and their General Solutions

Description: "For the design and the construction of airplanes the control is of special significance, not only with regard to the flight mechanical properties but also for the proportional arrangement of wing unit, fuselage, and tail unit. Whereas these problems may be regarded as solved for direct control of airplane motions, that is, for immediate operation of the control surfaces, they are not clarified as to oscillations, stability, and stress phenomena occurring in flight motions with Indirect control, as realized for instance in tab control" (p. 1).
Date: September 1949
Creator: Filzek, B.
Partner: UNT Libraries Government Documents Department

Experimental Investigation of a Preloaded Spring-Tab Flutter Model

Description: "An experimental investigation was made of a preloaded spring-tab flutter model to determine the effects on flutter speed of aspect ratio, tab frequency, and preloaded spring constant. The rudder was mass-balanced, and the flutter mode studied was essentially one of three degrees of freedom (fin bending coupled with rudder and tab oscillations). Inasmuch as the spring was preloaded, the tab-spring system was a nonlinear one" (p. 1).
Date: December 15, 1947
Creator: Smith, N. H.; Clevenson, S. A. & Barmby, J. G.
Partner: UNT Libraries Government Documents Department

Wind-Tunnel Investigation at Low Speed of the Yawing Stability Derivatives of a 1/9-Scale Powered Model of the Convair XFY-1 Vertically Rising Airplane, TED No. NACA DE 373

Description: An experimental investigation has been conducted in the Langley stability tunnel at low speed to deter+nine the yawing stability derivatives of a 1/9-scale powered model of the Convair XFY-1 vertically rising airplane. Effects of thrust coefficient were investigated for the complete model and for certain components of the model. Effects of control deflections and of propeller blade angle were investigated for the complete model. Most of the tests were made through an angle-of-attack range from about -4deg to 29deg, and the thrust coefficient range was from 0 to 0.7. In order to expedite distribution of these data, no analysis of the data has been prepared for this.
Date: March 31, 1953
Creator: Queijo, M. J.; Wolhart, W. D. & Fletcher, H. S.
Partner: UNT Libraries Government Documents Department

Effects of Direction of Propeller Rotation on the Longitudinal Stability of the 1/10-Scale Model of the North American XB-28 Airplane With Flaps Neutral

Description: "The effects of direction of propeller rotation on factors affecting the longitudinal stability of the XB-28 airplane were measured on a 1/10-scale model in the 7- by 10-foot tunnel of the Ames Aeronautical Laboratory. The main effect observed was that caused by regions of high downwash behind the nacelles (power off as well as power on with flaps neutral). The optimum direction of propeller rotation, both propellers rotating up toward the fuselage, shifted this region off the horizontal tail and thus removed its destabilizing effect" (p. 1).
Date: June 1942
Creator: Delany, Noel K.
Partner: UNT Libraries Government Documents Department

Data Obtained in the Flight Measurements to Determine the Stability and Control Characteristics of a C-54D Airplane (AAF No. 42-72713) and a Summary of the Test Program

Description: "The flight investigation of the C-54D airplane was initiated to determine the necessity of changes or additions to existing handling-qualities requirements to cove the case of instrument approaches with large airplanes. This paper gives a brief synopsis of the results and presents the measured data of tests to determine the stability and control characteristics. It was found that no new requirements were necessary to cover the problems of instrument approaches" (p. 1).
Date: December 29, 1947
Creator: Talmage, Donald B. & Reeder, John P.
Partner: UNT Libraries Government Documents Department

High-Speed Longitudinal-Stability and Control Characteristics of the Consolidated Vultee Lark Missile as Predicted from Wind-Tunnel Tests (TED No. NACA 2391)

Description: "A high-speed wind-tunnel investigation of the aerodynamic characteristics of a full-scale model of the Consolidated Vultee Lark indicates that the missile possesses satisfactory longitudinal-stability and-control characteristics throughout the Mach number range from 0.2 to 0.85, but that the maximum lift coefficients developed are not high enough to insure interception of the target at high altitudes. A reduction in wing loading appears advisable. Although the static longitudinal stability at zero angle of attack changes with Mach number and with lift coefficient, satisfactory control should be possible at all times as the tails retain their relatively large effectiveness throughout the range of Mach numbers and lift coefficients tested" (p. 1).
Date: November 19, 1946
Creator: Axelson, John A. & Martin, Andrew
Partner: UNT Libraries Government Documents Department

Preliminary Results of Stability and Control Investigation of the Bell X-5 Research Airplane

Description: "During the acceptance tests of the Bell X-5 airplane, measurements of the static stability and control characteristics and horizontal-tail loads were obtained by the NACA High-Speed Flight Research Station. The results of the stability and control measurements are presented in this paper. A change in sweep angle between 20 deg and 59 deg had a minor effect on the longitudinal trim, with a maximum change of about 2.5 deg in elevator deflection being required at a Mach number near 0.85; however, sweeping the wings produced a total stick-force change of about 40 pounds" (p. 1).
Date: February 11, 1953
Creator: Finch, Thomas W. & Briggs, Donald W.
Partner: UNT Libraries Government Documents Department

Systematic Wind-Tunnel Measurements on Missiles

Description: Wind-tunnel measurements on projectiles are discussed. Tests at the Gottingen Tunnel are described. The tunnel operates on the Prandtl principle, that is, a brief stationary air stream produced in an evacuated tank by induction of atmospheric air.
Date: March 1947
Creator: Walchner, O.
Partner: UNT Libraries Government Documents Department

A Transonic Wind-Tunnel Investigation of the Static Lateral, Directional, and Longitudinal Stability Characteristics of the Martin B-61A Missile (Matador)

Description: The static lateral, directional, and longitudinal stability characteristics of a 0.06-scale model of the Martin B-61A missile (Matador) were investigated in the Langley 8-foot transonic tunnel at Mach numbers from 0.80 t o 1.12. Six-component force and moment data were obtained from strain-gage measurements. The characteristics of a spoiler and of wing-tip end plates were also investigated. The Reynolds number of the tests based on the mean aerodynamic chord of the wing was approximately 1.6 X 106. The longitudinal and directional stability appeared satisfactory, except for a loss in directional stability near sonic velocity at small angles of yaw. Spoiler power appeared adequate. End plates were ineffective in reducing the dihedral effect at Mach numbers near 0.96 but were effective at the other Mach numbers. At such Mach numbers, the effectiveness was approximately proportional to the area of the plates. Langley and Wright Air Development Center results on this model showed good agreement for the most part.
Date: April 9, 1954
Creator: Luoma, Arvo A.
Partner: UNT Libraries Government Documents Department

Longitudinal Trim and Tumble Characteristics of a 0.057-Scale Model of the Chance Vought XF7U-1 Airplane, TED NO. NACA DE311

Description: Based on results of longitudinal trim and tumble tests of a 0.057-scale model of the Chance Vought XF7U-1 airplane, the following conclusions regarding the trim and tumble characteristics of the airplane have been drawn: 1. The airplane will not trim at any unusual or uncontrolled angles of attack. 2. The airplane will not tumble with the center of gravity located forward of 24 percent of the mean aerodynamic chord. When the center of gravity is located at 24 percent of the mean aerodynamic chord and slats are extended and elevators are deflected full up, the airplane may tumble if given an external positive pitching moment.
Date: July 20, 1948
Creator: Bryant, Robert L.
Partner: UNT Libraries Government Documents Department

Hydrodynamic Qualities of a 1/10-Size Powered Dynamic Model of the XP5Y-1 Flying Boat in Smooth Water: Langley Tank Model 246, TED No. NACA DE 320

Description: "The hydrodynamic characteristics of a 1/10-size powered dynamic model of the XP5Y-1 flying boat were determined in Langley tank no. 1. Stable take-offs were possible at all practicable positions of the center of gravity and flap deflections. An increase in gross load from 123.5 to 150.0 pounds (21.5 percent) had only a slight effect on the stable range for take-off" (p. 1).
Date: November 15, 1949
Creator: Woodward, David R.; Weinstein, Irving & Whitaker, Walter E., Jr.
Partner: UNT Libraries Government Documents Department

Effect of an Auxiliary Belly Fuel Tank on the Low-Speed Static Stability Characteristics of a 1/5-Scale Model of the Grumman XF8F-1 Airplane, TED No. NACA 2384

Description: "In order to determine the aerodynamic effects of an auxiliary belly fuel tank on the Grumman F8F-1 airplane, a wind-tunnel investigation was made on a 1/5 - scale model of the Grumman XF8F-1 airplane. Pitch and yaw tests were made with the model in the cruising and landing configurations for windmilling and take-off power conditions. Tuft studies and static-pressure measurements were also made to determine the flow characteristics in the region of the fuel tank" (p. 1).
Date: November 5, 1946
Creator: Cook, Charles B.
Partner: UNT Libraries Government Documents Department