SEARCH · Search NASA
Search indexed NASA NTRS and DOE OSTI research on propulsion, heat transfer, battery materials and energy systems. Follow report and document links to the original sources.
Quote a phrase for an exact phrase match. Source license links do not imply unrestricted reuse.
High subsonic wind tunnel study of stability and control characteristics of antitank missile with ram-pressure jet controls on ring tail
A brief investigation of the longitudinal stability and control effectiveness at supersonic speeds of a model of a low-wing missile with interdigitated tail surfaces was made in the Langley Unitary Plan wind tunnel. The data were obtained at Mach numbers M of 2.29, 2.97, and 3.51 for Reynolds number (based on the mean geometric chord of the wing) of 1.15 x 10(exp 6), 1.14 x 10(exp 6), and 1.11 x 10(exp 6), respectively. Data were obtained for three settings of the longitudinal control surfaces: with deflection of all surfaces, with deflection of the lower surfaces only, and with all surfaces undeflected. Directional stability data were obtained at M=3.51 for angles of attack of approximately 0 deg and 10 deg. These data, with summary data and typical schlieren photographs, are presented with only a brief analysis. The data indicate that the controls are effective throughout the Mach number range and lift-coefficient range (CL = -0.15 to 0.7, approximately) of the tests. There is a severe break in the pitching-moment curve at M=2.29 which might result in a pitch-up condition in flight, and also a large forward movement of the aerodynamic center with increasing Mach number that produces neutral longitudinal stability at M=3.51 for the moment center used in this investigation. The model was directionally unstable at M=3.51; however, the level of directional stability was about the same for 0 deg and 10 deg angles of attack.
Wind tunnel investigation of transonic and supersonic flutter of air to surface missile vertical tail surfaces
Swept wing-fuselage flow fields on missile loads at subsonic speeds
Water landing characteristics of winged missile scale model
Jet-stream interaction effects on rocket engine studied with simulated ballistic missile using liquid oxygen and JP-4 fuel mixture
Impact craters produced by missiles with large kinetic energy
Missiles and aerospace vehicles sciences - AAS CONFERENCE, Huntsville, Alabama, December 1966, Volume 1
Missiles and aerospace vehicles sciences - Conference, Huntsville, Alabama, December 1966, Volume 2
A missile research model was flown at supersonic speed to determine the quality of automatic roll stabilization at varying angles of attack. Aerodynamic rolling and pitching derivatives were determined from the flight record. It was concluded that the combination of the gyro-actuated automatic pilot with wing-tip ailerons provided adequate roll stabilization under conditions encountered in flight.
Experimental investigation of aerodynamic forces acting on body of revolution (NACA RM-10 missile) with and without stabilizing fins was conducted at Mach numbers from 1.49 to 1.98 at angles of attack from 0 to 9 degrees and at Reynolds number of approximately 30,000,000. Comparison of experimental lift, drag, and pitching-moment coefficients and center of pressure location for body alone is made with linearized potential theory and a semiempirical method. Results indicate that aerodynamic characteristics were predicted more accurately by semiempirical method than by potential theory. Breakdown of measured drag coefficients into components of friction, pressure, and base-pressure drag is presented for body alone at zero angle of attack.
Missile and space vehicle electrical systems - space science
Launching pad operations for missiles - statistical probability and prelaunch problems
Missile data storage system for obtaining reentry heating data, employing ferrite memory and digital and analog circuitry
Mathematical models of simultaneous countdown but nonsimultaneous missile launching program
Wind tunnel investigation of aerodynamic characteristics of cone-cylinder-flare multistage missile configurations at supersonic speed
Miniature data storage system for missile reentry heat data