Technical Report Archive & Image Library (TRAIL) - 60 Matching Results

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Flight Investigation of the Transonic Longitudinal and Lateral Handling Qualities of the Douglas X-3 Research Airplane

Description: Memorandum presenting a flight investigation to determine the longitudinal and lateral handling qualities of the Douglas X-3 research airplane in the clean configuration. Static and dynamic stability and control characteristics were determined during trimmed and maneuvering flight at an average altitude of 30,000 feet and over a Mach number range from 0.7 to 1.16.
Date: December 5, 1957
Creator: Fischel, Jack; Holleman, Euclid C. & Tremant, Robert A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Aerodynamic characteristics at Mach number of 4.06 of a typical supersonic airplane model using body and vertical-tail wedges to improve directional stability

Description: Report presenting an investigation at Mach number 4.06 on a typical supersonic airplane model with a 40 degree sweptback wing. The purpose of the investigation was to determine the effectiveness of using wedges on the body and on the vertical tail to increase the static directional stability. Results regarding the longitudinal characteristics and lateral characteristics are provided.
Date: December 3, 1957
Creator: Dunning, Robert W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effects of string-support interference on the drag of an olgive-cylinder body with and without a boatail at 0.6 to 1.4 Mach number

Description: Report presenting tests to determine the effects of sting-support interference on the zero-lift drag of two bodies of revolution (with and without boattailing). The sting support consisted of a constant-diameter sting followed by a sting flare terminating in a cylindrical support. Results regarding the effect of sting length and sting diameter are provided.
Date: December 3, 1957
Creator: Lee, George & Summers, James L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Investigation at High Subsonic Speeds of the Static Longitudinal and Lateral Stability Characteristics of Two Canard Airplane Configurations

Description: "The present investigation was conducted in the Langley high-speed 7-by 10-foot tunnel to determine the static longitudinal and lateral stability characteristics at high subsonic speeds of two canard airplane configurations previously tested at supersonic speeds. The Mach number range of this investigation extended from 0.60 to 0.94 and a maximum angle-of-attack range of -2deg to 24deg was obtained at the lowest test Mach number. Two wing plan forms of equal area were studied in the present tes… more
Date: December 3, 1957
Creator: Sleeman, William C., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The effects of boundary-layer separation over bodies of revolution with conical tail flares

Description: The magnitude and the effects of boundary-layer separation on normal-force-curve slopes, centers of pressure, pressure distributions, and lift and drag coefficients were determined for various bodies of revolution with conical tail flares at Mach numbers from 3.0 to 6.3. Some of the experimental results are compared to theoretical predictions of the aerodynamic characteristics of the bodies.
Date: December 12, 1957
Creator: Dennis, David H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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In-flight gains realized by modifying a twin side-inlet induction system

Description: Report presenting the effects of modifying a twin side-inlet duct system on an interceptor airplane over a range of altitudes throughout the transonic speed range to Mach number 1.2. The primary modifications were redesigning the inlet lip, increasing the cross-sectional area of the inlet and diffuser, and adding a region of duct contraction ahead of the engine.
Date: December 12, 1957
Creator: Saltzman, Edwin J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Comparison and Evaluation of Two Model Techniques Used in Predicting Bomb-Release Motions

Description: "For the purpose of calculating bomb trajectories, forces and moments have been measured on bombs of three fineness ratio sin the presence of a swept-wing fighter bomber configuration at a Mach number of 1.61. Trajectories thus obtained have been compared with those from dynamic model tests and an analysis has been made to determine the source of errors and to suggest improvements in both techniques." (p. 1).
Date: December 27, 1957
Creator: Carlson, Harry W.; Geier, Douglas J. & Lee, John B.
Item Type: Refine your search to only Report
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.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Experimental Hinge Moments on Two Freely Oscillating Trailing-Edge Controls Hinged at 55 Percent Control Chord

Description: Memorandum presenting oscillatory hinge-moment characteristics obtained from free-flight tests of two rocket-powered models. Results indicate that the hinge-line location of 55 percent control chord did not prevent unstable control aerodynamic damping. The damping appeared to be more stabilizing as the amplitude of oscillation was increased.
Date: December 27, 1957
Creator: Martz, C. William
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Supplementary Investigation in the Langley 20-Foot Free-Spinning Tunnel of a 1/20-Scale Model of the Douglas F4D-1 Airplane With External Wing Fuel Tanks: TED No. NACA AD 3116

Description: Memorandum presenting an investigation in the 20-foot free-spinning tunnel on a scale model to determine the spin and recovery characteristics of the Douglas F4D-1 airplane with external wing fuel tanks installed. The results indicated that any fully developed erect spin obtained on the airplane with tanks installed will be satisfactorily terminated by rudder reversal accompanied by moving the ailerons to full with the spin.
Date: December 27, 1957
Creator: Bowman, James S., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Aerodynamic Characteristics of a Model of an Escape Capsule for a Supersonic Bomber-Type Airplane at a Mach Number of 2.49

Description: Report discussing an investigation of the aerodynamic characteristics of a model of an escape capsule with and without stabilizing fins for a supersonic bomber-type airplane. Lift, drag, longitudinal and lateral stability characteristics, and photographs of the capsule model are presented.
Date: December 3, 1957
Creator: Presnell, John G., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Theoretical and Experimental Investigation of Arbitrary Aspect Ratio, Supercavitating Hydrofoils Operating Near the Free Water Surface

Description: Report presents a comparison of the theoretical and experimental expressions of lift, drag, and center of pressure of supercavitating hydrofoils. The results obtained from both methods appear to agree well with one another. The application of cavitation number to a variety of situations and speeds is also provided.
Date: December 12, 1957
Creator: Johnson, Virgil E., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Normal-force and hinge-moment characteristics at transonic speeds of flap-type ailerons at three spanwise locations on a 4-percent-thick sweptback-wing-body model and pressure distribution measurements on an inboard aileron

Description: Report presenting an investigation conducted at the 16-foot transonic tunnel to determine the loading characteristics of flap-type ailerons located at inboard, midspan, and outboard positions on a 45 degree sweptback-wing-body combination. Results indicated that the loading over the ailerons was established by the wing-flow characteristics and the loading shapes were irregular in the transonic speed range.
Date: December 5, 1957
Creator: Runckel, Jack F. & Hieser, Gerald
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Investigation at High Subsonic Speeds of the Use of Low Auxiliary Tail Surfaces Having Dihedral to Improve the Longitudinal and Directional Stability of a T-Tail Model at High Lift

Description: Memorandum presenting an investigation of the use of low auxiliary horizontal-tail surfaces to alleviate the pitch-up tendency at high lift of an airplane configuration with a T-tail. The basic model had a wing with an aspect ratio of 3, a taper ratio of 0.143, and an unswept 80-percent chord line.
Date: December 5, 1957
Creator: Sleeman, William C., Jr.
Item Type: Refine your search to only Report
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.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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An Investigation of the Control Effectiveness of Tip Ailerons and Spoilers on a Low-Aspect-Ratio Trapezoidal-Wing Airplane Model at Mach Numbers From 1.55 to 2.35

Description: Memorandum presenting a wind-tunnel investigation of the three types of lateral control devices on a low-aspect-ratio trapezoidal wing. Tip ailerons, a plain spoiler, and a vented spoiler were investigated to ascertain the relative characteristics of each system. The results indicated the superiority in roll power of the tip ailerons over the plain and vented ailerons.
Date: December 12, 1957
Creator: Wong, Norman D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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A laboratory Ivestigation of the Fluorination of Crude Uranium Tertrafluoride

Description: Ore concentrates have been converted directly to crude uranium tetrafluoride by hydrogen reduction and hydrofluorination in fluidized-bed reactors. Small-scale laboratory experiments demonstrated that this process can be extended to the production of crude uranium hexafluoride through fluorination of the uranium tetrafluoride in a fluidized bed. The satisfactory temperature range for the reaction lies between 300°C and 600°C. At 450°C the fluorine utilization is between 50 and 80 per cent. With… more
Date: December 1957
Creator: Sandus, O. & Steunenberg, R. K.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Drying of Charcoal Used for Adsorption of Gaseous Fission Products from Homogeneous Reactors

Description: In homogeneous nuclear reactors significant quantities of radioactive inert gaseous fission products must be separated from the fuel solution for disposal. The present disposal scheme, which is employed on the HRT, is to pass the mixture of fission product gases and oxygen through a charcoal adsorption bed. the oxygen passes through the bed relatively un-adsorbed, but the radioactive inert gases are adsorbed and are displaced from the bed bed very slowly giving the gases a much greater residenc… more
Date: December 20, 1957
Creator: Funderburg, J. M. & Moss, L. I.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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