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An Investigation of Several Supersonic Missile Configurations Directed Toward Minimizing Center-of-Pressure Travel

Description: Memorandum presenting an investigation in the 9-inch supersonic tunnel of several missiles with low-aspect-ratio, cruciform, tandem lifting surfaces with a view toward developing a missile with small variations of center-of-pressure location at various angles of attack and roll. The investigation centered about a basic configuration with equal-span wings and tails.
Date: September 23, 1952
Creator: Rainey, Robert W.
Partner: UNT Libraries Government Documents Department
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Experimental Investigation of the Static Aerodynamic and Dynamic Damping-in-Roll Characteristics of an 8-Cm Aircraft Rocket With Solid and Slotted Fins

Description: Memorandum presenting an investigation of the static aerodynamic and dynamic damping-in-roll characteristics of an aircraft rocket with cruciform fins of trapezoidal plan form as determined experimentally at a range of Mach numbers. The fins had tow holes cut through each fin panel, and the effects of the holes or slots were investigated by testing with both solid and slotted fins.
Date: June 2, 1952
Creator: Chubb, Robert S.
Partner: UNT Libraries Government Documents Department
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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
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Flight Investigation at Low Angles of Attack to Determine the Longitudinal Stability and Control Characteristics of the Sidewinder Missile at Mach Numbers from 1.2 to 2.1

Description: At the request of the Bureau of Ordnance, Department of the Navy, the Langley Pilotless Aircraft Research Division has initiated a program to investigate the general aerodynamic characteristics of the Naval Ordnance Test Station's SIDEWINDER missile. The model used in the flight test presented herein was a full-scale, rocket-propelled test vehicle. This paper presents the results from a flight test investigation using the pulsed-control technique to determine the static and dynamic longitudinal… more
Date: November 25, 1955
Creator: Brown, Clarence A., Jr.
Partner: UNT Libraries Government Documents Department
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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
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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
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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
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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
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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
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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
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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
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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
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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
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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 … more
Date: August 4, 1958
Creator: Robinson, Ross B. & Bernot, Peter T.
Partner: UNT Libraries Government Documents Department
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Free-flight Investigation at Transonic Speeds of the Stability Characteristics of a Tailless Missile Configuration Having a 45 Deg Sweptback Wing of Aspect Ratio 4

Description: Free flight test of tailless missile configuration with 45-deg sweptback wing of aspect ratio 4 - stability at transonic speeds. The longitudinal flexible-wing results indicated a gradual transonic trim change a lift-curve slope comparable with that for the same configuration with a wing of aspect ratio 5.5. Results regarding trim characteristics, lift and longitudinal stability, and side-force and lateral stability are provided.
Date: August 28, 1956
Creator: Arbic, Richard G.
Partner: UNT Libraries Government Documents Department
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A Study of Several Parameters Controlling the Trajectories of a Supersonic Antiaircraft Missile Powered With Solid- or Liquid-Fuel Rockets

Description: Memorandum presenting a calculation of the trajectories for a supersonic antiaircraft missile by a step-by-step integration method for a number of different conditions. The effects of changing drag, initial thrust ratio, and weight ratio, which are the principal variables controlling the trajectory for a fixed launching angle, were investigated.
Date: April 24, 1947
Creator: Huntsberger, Ralph F.
Partner: UNT Libraries Government Documents Department
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Experimental Investigation of the Stability, Control, and Induced Rolling Moments of a Canard Missile Airframe at a Mach Number of 1.7

Description: Memorandum presenting the results of an investigation of the stability, control, and induced rolling moments of a canard missile with cruciform wings of rectangular plan form at Mach number 1.7. All of the data obtained, including the measured hinge moments of the canard control surfaces, axial forces on the complete missile, and forces and moments on the various combinations of missile components are presented in tabular form.
Date: September 23, 1952
Creator: Chubb, Robert S.
Partner: UNT Libraries Government Documents Department
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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
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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
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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
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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: "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 … more
Date: December 19, 1957
Creator: Graham, John B., Jr.; Chauvin, Leo T. & Speegle, Katherine C.
Partner: UNT Libraries Government Documents Department
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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
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