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Characteristics of a canard-type missile configuration with an underslung scoop inlet at Mach numbers from 1.5 to 2.0

Description: Report presenting an experimental investigation of a canard-type missile configuration with an underslung scoop inlet in the 8 by 6-foot supersonic wind tunnel at a range of Mach numbers, angles of attack, control-surface deflection angles, boundary-layer-scoop heights, and inlet mass-flow ratios. Measurement of the external forces indicated that maximum lift-drag ratios were in excess of 5 at all test Mach numbers.
Date: January 30, 1953
Creator: Fradenburgh, Evan A. & Campbell, Robert C.
Partner: UNT Libraries Government Documents Department

A simulation study of a wingless missile

Description: Report presenting a preliminary study to determine the possibility of utilizing a wingless configuration as a guided missile. The results indicated that the maximum trimmed lift coefficient developed by the wingless missile was somewhat smaller than that of the winged missile at a Mach number of 2.4.
Date: February 8, 1956
Creator: Lessing, Henry C. & Reese, David E., Jr.
Partner: UNT Libraries Government Documents Department

Free-flight investigation of the full-scale Hughes Falcon missile, D configuration, to determine aileron effectiveness and damping in roll

Description: Report presenting a free-flight investigation over a range of Mach numbers near zero lift to determine the aileron effectiveness and damping in roll of the full-scale Hughes Falcon missile, D configuration.
Date: November 19, 1954
Creator: Lundstrom, Reginald R.
Partner: UNT Libraries Government Documents Department

Experimental static aerodynamic forces and moments at high subsonic speeds on a canard missile during simulated launching from the midsemispan location of a 45 degree sweptback wing-fuselage-pylon combination at zero sideslip

Description: Report presenting an investigation at high subsonic speeds to determine the static aerodynamic forces and moments on a canard missile model during simulated launching from the midsemispan location of a 45 degree sweptback wing-fuselage-pylon combination. Significant variations in all the aerodynamic components were noted with changes in chordwise location of the missile. Results regarding force and moment characteristics and effects of angle of attack and Mach number are provided.
Date: January 14, 1957
Creator: Alford, William J., Jr. & King, Thomas J., Jr.
Partner: UNT Libraries Government Documents Department

Experimental static aerodynamic forces and moments at low speed on a canard missle during simulated launching from the midsemispan and wing-tip locations of a 45 degree sweptback wing-fuselage combination

Description: Report presenting an investigation at low speed to determine the static aerodynamic forces and moments on a canard missile model during launching from the midsemispan and wing-tip locations of a wing-fuselage combination with a 45 degree sweptback wing. When the missile was mounted under the wing at the midsemispan location, changes in chordwise position produced large changes in missile forces and moments.
Date: April 6, 1955
Creator: Alford, William J., Jr.
Partner: UNT Libraries Government Documents Department

A wind tunnel investigation of several wingless missile configurations at supersonic speeds

Description: Report presenting an investigation of several wingless missile configurations for a range of Mach numbers to determine their lift, drag, and pitching-moment coefficients. Results for missiles having nose controls and missiles having tail controls are provided. The results were also compared to a conventional missile with wings.
Date: February 3, 1958
Creator: Reese, David E., Jr.
Partner: UNT Libraries Government Documents Department

Development of a piston-compressor type light-gas gun for the launching of free-flight models at high velocity

Description: Report presenting testing of missiles in which temperatures are approximated and aerodynamic heating of the model is representative of that experienced by the missile in high-velocity flight. The paper describes a piston compressor type of light-gas gun, which shows good agreement between predictions of performance charts and experimental data.
Date: November 1957
Creator: Charters, A. C.; Denardo, B. Pat & Rossow, Vernon J.
Partner: UNT Libraries Government Documents Department

Theoretical investigation of the effects of configuration changes on the center-of-pressure shift of a body-wing-tail combination due to angle of attack and mach number at transonic speeds

Description: Report presenting a theoretical investigation to study the effects of systematic changes in configuration of a representative airframe on the center-of-pressure travel due to changes in angle of attack and Mach number. The airframe was an unbanked canard missile configuration with low-aspect-ratio coplanar wing and tail surfaces of triangular plan form.
Date: May 1957
Creator: Spahr, J. Richard
Partner: UNT Libraries Government Documents Department

Paths of target-seeking missiles in two dimensions

Description: Report presenting a discussion of some of the parameters that enter into the equation of the path of a missile which is pursuing its target. The missile is assumed to be guided by a target seeker that might be employed in any one of several ways. Results regarding the normal-pursuit navigation, constant navigation, proportional navigation, line-of-sight navigation, and effect of angle of attack and sideslip are provided.
Date: July 1946
Creator: Watkins, Charles E.
Partner: UNT Libraries Government Documents Department

Aerodynamic characteristics in pitch of a series of cruciform-wing missiles with canard controls at a Mach number of 2.01

Description: From Introduction: "This paper presents the results of tests made at a Mach number of 2.01 to determine the effect of body length on the longitudinal characteristics (zero roll angle) for five complete configurations as well as for the bodies alone, the bodies plus wings, and the bodies plus canard surfaces. The experimental results are compared with some simple theoretical estimates."
Date: October 30, 1953
Creator: Spearman, M. Leroy
Partner: UNT Libraries Government Documents Department

Preliminary Low-Speed Wind-Tunnel Investigation of Some Aspects of the Aerodynamic Problems Associated with Missiles Carried Externally in Positions Near Airplane Wings

Description: A low-speed wind-tunnel investigation has been made of some aspects of the aerodynamic problems associated with the use of air-to-air missiles when carried externally on aircraft. Measurements of the forces and moments on a missile model for a range of positions under the mid-semispan location of a 45deg sweptback wing indicated longitudinal and lateral forces with regard to both carriage and release of the missiles. Surveys of the characteristics of the flow field in the region likely to be traversed by the missiles showed abrupt gradients in both flow angularity and in local dynamic pressure. Through the use of aerodynamic data on the isolated missile and the measured flow-field characteristics, the longitudinal forces and moments acting on the missile while in the presence of the wing-fuselage combination could be estimated with fair accuracy. Although the lateral forces and moments predicted were qualitatively correct, there existed some large discrepancies in absolute magnitude.
Date: December 27, 1954
Creator: Alford, William J., Jr.; Silvers, H. Norman & King, Thomas J., Jr.
Partner: UNT Libraries Government Documents Department

Hydrodynamic Characteristics of Missiles Launched Under Water

Description: Report presenting some of the hydrodynamic problems associated with launching an air missile from underwater. The results of an experiment with models are also provided, including deviation angle, effect of forward speed of the submarine, curved path of the missile, and potential environmental disruptions.
Date: June 27, 1958
Creator: Dawson, John R.
Partner: UNT Libraries Government Documents Department

Longitudinal aerodynamic characteristics to large angles of attack of a cruciform missile configuration at a Mach number of 2

Description: Report presenting the lift, pitching-moment, and drag characteristics of a missile configuration with a body of fineness ratio 9.33 and a cruciform triangular wing and tail of aspect ratio 4 at Mach number 1.99 and Reynolds number 6.0 million. Testing occurred over a range of angles of attack and to investigate the effects on the aerodynamic characteristics of roll angle, wing-tail interdigitation, wing deflection, and interference among the components.
Date: December 6, 1954
Creator: Spahr, J. Richard
Partner: UNT Libraries Government Documents Department

Investigation in the Ames Supersonic Free-Flight Wind Tunnel of the Static Longitudinal Stability of the Hermes A-3B Missile at a Mach Number of 5.0

Description: Models of the Hermes A-3B missile were tested in the Ames supersonic free-flight wind tunnel to determine the static-longitudinal-stability characteristics at a Mach number of 5.0 and a Reynolds number based on body length of 10 million. The results indicated that the model center of pressure was 45.3 percent of the body length aft of the nose and the lift-curve slope based on body frontal area was 0.064 per degree. Estimates indicated that the effect on these characteristics of aeroelastic twisting of the model fins was small but important if a precise location of center of pressure is required. A comparison of the test results with predictions based on available theory showed that the theory was useful only for rough estimates, The drag coefficient at zero lift, based on body frontal area, was found to be 0.155.
Date: March 10, 1952
Creator: Canning, Thomas N. & Denardo, Billy Pat
Partner: UNT Libraries Government Documents Department

Heat-transfer and pressure measurements from a flight test of a 1/18-scale model of the Titan intercontinental ballistic missile up to a Mach number of 3.95 and Reynolds number per foot of 23 x 10(exp 6): COORD. No. AF-AM-70

Description: From Summary: "Boundary-layer transition and heat-transfer measurements were obtained from a flight test of a 1/18-scale model of the Titan intercontinental ballistic missile up to a Mach number of 3.95 and a Reynolds number per foot of 23 x 10(exp 6). Boundary-layer transition was observed on the nose of the model. Available theories predicted heat-transfer coefficients reasonably well for the fully laminar or turbulent flow conditions. The drag coefficient of the configuration was also obtained for a Mach number range of 1.25 to 3.75."
Date: December 19, 1957
Creator: Graham, John B., Jr.; Chauvin, Leo T. & Speegle, Katherine C.
Partner: UNT Libraries Government Documents Department

Survey of some preliminary investigations of supersonic diffusers at high Mach numbers

Description: From Introduction: "Design studies of long-range supersonic missiles indicate the Mach number range of 3 to 4 to be of considerable promise. Accordingly, the NACA is conducting research on the performance of a wide variety of supersonic diffusers in this range. The initial phase of this research is concerned primarily with the characteristics of conventional axially symmetric diffusers operating at design values of flight Mach number."
Date: July 10, 1952
Creator: Cortright, Edgar M., Jr. & Connors, James F.
Partner: UNT Libraries Government Documents Department

A comparison of the calculated maximum-maneuver response characteristics of three air-to-air, beam-rider, guided missiles having different lift ratios

Description: Report presenting a comparison of the calculated response characteristics corresponding to the maximum maneuver of a variable-incidence, a canard, and a conventional tail-aft-control, beam-rider, guided missile. All the configurations were designed to be the same except for the effects of changes in lift ratio. Results regarding limited control-surface deflection, limited angle of attack of the critical surface, servo energy, surface-deflection interference, and size of surfaces are provided.
Date: September 25, 1951
Creator: Matthews, Howard F. & Stewart, Elwood C.
Partner: UNT Libraries Government Documents Department

A wind-tunnel investigation of several wingless missile configurations at supersonic speeds

Description: Report presenting a wind-tunnel investigation of several wingless missile configurations. Lift, drag, and pitching-moment coefficients were measured for a range of Mach numbers. Results regarding the missiles with nose controls and missiles with tail controls are provided.
Date: February 3, 1958
Creator: Reese, David E., Jr.
Partner: UNT Libraries Government Documents Department

Aerodynamic characteristics at a Mach Number of 6.8 of two hypersonic missile configurations, one with low-aspect-ratio cruciform fins and trailing-edge flaps and one with a flared afterbody and all-movable controls

Description: Report presenting an investigation to determine the aerodynamic characteristics in pitch at a Mach number of 6.8 of hypersonic missile configurations with cruciform trailing-edge flaps and all-movable control surfaces. Testing indicated that all-movable controls on the flared-afterbody model should be capable of producing much larger values of trim lift and of normal acceleration than the trailing-edge-flap configuration. Some of the configurations tested include body alone, body with 5 degree fins and trailing-edge flaps, and body with 10 degree flare and all-movable controls.
Date: August 4, 1958
Creator: Robinson, Ross B. & Bernot, Peter T.
Partner: UNT Libraries Government Documents Department

An experimental investigation of the unsteady lift induced on a wing in the downwash field of an oscillating canard control surface

Description: Report presenting the results of an experimental investigation of the unsteady lift induced on a wing in the downwash field of an oscillating canard control surface. The results indicated that existing theories provide a reliable guide for the estimation of the magnitude of the lift derivatives and centers of pressure at low values of reduced frequency and low angles of attack.
Date: August 15, 1955
Creator: Reese, David E., Jr.
Partner: UNT Libraries Government Documents Department

Experimental investigation of the simulation of atmospheric entry of ballistic missiles

Description: Report presenting a small-scale apparatus for simulating the motion and heating of ballistic missiles and its elements of design and operation. Experiments demonstrate that conditions for simulation are fulfilled according to theoretical requirements. Results regarding the application to full-scale missiles, shadowgraph observations, observations of recovered models, and spectroscopic observations are provided.
Date: December 12, 1957
Creator: Neice, Stanford E.; Carson, James A. & Cunningham, Bernard E.
Partner: UNT Libraries Government Documents Department

National Missile Defense and Early Warning Radars: Background and Issues

Description: The Clinton Administration is scheduled to decide by Fall 2000 whether the United States should begin deploying a National Missile Defense (NMD) system.This system could achieve initial operational capability by 2005 and would be designed to protect the United States from a limited attack by intercontinental ballistic missiles (ICBMs). As currently envisioned, the NMD system would operate as an integrated system that would rely on a variety of sensors to detect and track incoming missiles. One key program element is to upgrade the existing Early Warning Radars (EWR) so that they can detect and track the incoming missiles sooner. This report provides background information and technical details of these planned upgrades as well as their cost and schedule.
Date: August 25, 2000
Creator: Chasteen, Larry
Partner: UNT Libraries Government Documents Department