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Additional Experiments With Flat-Top Wing- Body Combinations at High Supersonic Speeds

Description: Memorandum presenting an experimental study of the effects of several variations in configuration geometry on the aerodynamic characteristics of flat-top wing-body combinations. Generally, the configurations consist of one half of a body of revolution mounted beneath a wing of essentially arrow plan form. Results regarding the effect of trailing-edge sweep, effect of the addition of auxiliary bodies, effect of tip-flap deflection, effect of dihedral, effect of leading-edge sweep, effect of fuselage fineness ratio, effect of fuselage profile shape, and static longitudinal stability characteristics are provided.
Date: February 19, 1957
Creator: Syvertson, Clarence A.; Wong, Thomas J. & Gloria, Hermilo R.
Partner: UNT Libraries Government Documents Department

Additional facilities to handle PUREX tank farm vapor wastes. Project CG-719

Description: The liquid high-level radioactive wastes from the separations plant are stored in large underground tanks where radioactive decay of the fission products in storage gives off heat. In the case of the 241-A underground storage tank farm, for Purex wastes, advantage is taken of this heat to self-concentrate the wastes. The present practice is to permit boiling and concentration in the storage tanks. The vapors given off from the boiling wastes are collected in a vapor header and passed through a deentrainment vessel and on to two contact condensers where the vapors are condensed and intermixed with waste cooling water. Samples taken of the waste vapors have shown a considerable amount of cesium{sup 137} present as well as other types of radioactive material carry over from the waste tanks. For this reason the contact condenser effluent is discharged to an underground crib 216-A-8. Underground disposal of the increasing volume of condenser effluent as larger waste volumes are accumulated in the underground tanks presents a critical problem which is further complicated by the desirability to transfer the condensate waste to new disposal facilities near the 200 West area. The intent of this report is to present the scope of the facilities required to reduce the volume of potentially radioactive condensate waste from the 241-A tank farm and to dispose of this waste through supplemental cribbing. An analysis of the 216-A-8 crib capabilities in relation to the projected flows clearly indicates that if other facilities to reduce the contaminated waste stream volume are not provided, an extensive and costly crib system will be required. The economical solution to the problem is to provide surface condensers to permit segregation of the condensed waste vapors from the cooling water, condensate collection and transfer facilities, and a new condensate disposal crib near the 200 West ...
Date: January 7, 1957
Creator: Wood, V. W.
Partner: UNT Libraries Government Documents Department

Additional Measurements on the Army Package Power Reactor Zero Power Experiments: ZPE-1 and ZPE-2

Description: During the course of the ZPE-2 experimental program additional measurements were performed under the Alco Products Research and Development program. Included in this program were the evaluation of various absorber section compositions and reactivity studies designed to facilitate analytical techniques. The results of these measurements are presented. (auth)
Date: November 15, 1957
Creator: Giesler, H. W.
Partner: UNT Libraries Government Documents Department

[Advertising product at Cho's Grocery]

Description: Photograph of a man and a woman holding up a Cook Book Donuts box. They are standing in front of a Cook Book Cake display at Cho's Grocery in Port Arthur, Texas. Several products and an individual can be seen in the background.
Date: 1957
Creator: WBAP-TV (Television station : Fort Worth, Tex.)
Location Info:
Partner: UNT Libraries Special Collections

Aerodynamic and hydrodynamic characteristics of a proposed supersonic multijet water-based hydro-ski aircraft with a variable-incidence wing

Description: From Introduction: "The configuration described in this paper represents one approach to such an airplane and the results of the wind-tunnel and tank evaluations are presented. In the present investigation, the aerodynamic longitudinal characteristics over a Mach number range from 0.6 to 1.97 were obtained."
Date: October 23, 1957
Creator: Petynia, William W.; Hasson, Dennis F. & Spooner, Stanley H.
Partner: UNT Libraries Government Documents Department

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.
Partner: UNT Libraries Government Documents Department

Aerodynamic Characteristics of a 0.04956-Scale Model of the Convair TF-102A Airplane at Transonic Speeds, Coord. No. AF-120

Description: "The basic aerodynamic characteristics of a 0.04956-scale model of the Convair TF-102A airplane with controls undeflected have been determined at Mach numbers from 0.60 to 1.135 for angles of attack up to approximately 22 deg in the Langley 8-foot transonic tunnel. In addition, comparisons have been made with data obtained from a previous investigation of a 0.04956-scale model of the Convair F-102A airplane. The results indicated the TF-102A airplane was longitudinally stable for all conditions tested" (p. 1).
Date: 1957~
Creator: Osborne, Robert S.
Partner: UNT Libraries Government Documents Department

Aerodynamic Characteristics of a Circular Cylinder at Mach Number 6.86 and Angles of Attack Up to 90 Degrees

Description: "Pressure-distribution and force tests of a circular cylinder have been made in the Langley 11-inch hypersonic tunnel at a Mach number of 6.88, a Reynolds number of 129,000, and angles of attack up to 90 degrees. The results are compared with the hypersonic approximation of Grimminger, Williams, and Young and a simple modification of the Newtonian flow theory. An evaluation of the crossflow theory is made through comparison of present results with available crossflow Mach number drag coefficients" (p. 1).
Date: January 1957
Creator: Penland, Jim A.
Partner: UNT Libraries Government Documents Department

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.
Partner: UNT Libraries Government Documents Department

Aerodynamic Characteristics of Missile Configurations With Wings of Low Aspect Ratio for Various Combinations of Forebodies, Afterbodies, and Nose Shapes for Combined Angles of Attack and Sideslip at a Mach Number of 2.01

Description: "An investigation has been made in the Langley 4-by-4-foot supersonic pressure tunnel to determine the aerodynamic characteristics of a series of missile configurations having low-aspect-ratio wings at a Mach number of 2.01. The effects of wing plan form and size, length-diameter ratio, forebody and afterbody length, boattailed and flared afterbodies, and component force and moment data are presented for combined angles of attack and sideslip to about 28 degrees. No analysis of the data was made in this report" (p. 1).
Date: June 25, 1957
Creator: Robinson, Ross B.
Partner: UNT Libraries Government Documents Department

Aerodynamic Forces and Moments on a Large Ogive-Cylinder Store at Various Locations Below the Fuselage Center Line of a Swept-Wing Bomber Configuration at a Mach Number of 1.61

Description: "A supersonic wind-tunnel investigation on store interference has been conducted in the Langley 4- by 4-foot supersonic pressure tunnel at a Mach number of 1.61. Forces and moments were measured on a large ogive-cylinder store in the presence of a 45 degree swept-wing-fuselage bomber configuration for a number of store locations below the fuselage center line. Results of the investigation show that large variations of store lift, drag, and pitch occur with changes in store or airplane angle of attack, store vertical location, and store horizontal location" (p. 1).
Date: January 14, 1957
Creator: Morris, Odell A.
Partner: UNT Libraries Government Documents Department

Aerodynamic Heating and Boundary-Layer Transition on a 1/10-Power Nose Shape in Free Flight at Mach Numbers Up to 6.7 and Free-Stream Reynolds Numbers Up To 16 x 10(Exp 6)

Description: Report presenting testing of a modified 1/10-power nose shape in free flight at Mach numbers up to 6.7. Measured heating rates were presented and compared with calculated values. Results regarding transition and comparison with previous investigations are provided.
Date: June 17, 1957
Creator: Garland, Benjamine J.; Swanson, Andrew G. & Speegle, Katherine C.
Partner: UNT Libraries Government Documents Department

Aerodynamic heating of a thin, unswept, untapered, multiweb, aluminum-alloy wing at Mach numbers up to 2.67 as determined from a free-flight investigation of a rocket-propelled model

Description: From Introduction: "The heat-transfer data calculated from measured temperatures are compared with values calculated by the theory of Van Driest for a flat plate with laminar and turbulent boundary layers. In addition, the heat-transfer data from the flight tests are compared with data obtained from the Langley Structures Research Division of ground tests of an identical wing at a Mach number approximately equal to 1.99 in the pre-flight jet of the Langley Pilotless Aircraft Research Station at Wallops Island, Va. The stream static pressure is maintained at about 1 atmosphere, the free-stream temperature at about 75^o F, and the stagnation temperature at approximately 500 ^o F (ref.1)."
Date: August 6, 1957
Creator: Strass, H. Kurt & Stephens, Emily W.
Partner: UNT Libraries Government Documents Department

Aerodynamic interference of slender wing-tail combinations

Description: From Introduction: "In the present paper, the emphasis is placed on calculating the variations of total forces and moments with angles of attack and sideslip for a number of slender plane and cruciform wing-tail combinations and for some airplane-type arrangements of a plane wing and a horizontal and vertical tail."
Date: January 1957
Creator: Sacks, Alvin H.
Partner: UNT Libraries Government Documents Department

Aerodynamic load distribution over a 45 degree swept wing having a spoiler-slot-deflector aileron and other spoiler ailerons for Mach numbers from 0.60 to 1.03

Description: Report discussing an investigation of a 45 degree swept-back-wing-body combination with flap spoiler ailerons, deflector ailerons, and a spoiler-slot-deflector aileron. The pressures were measured from Mach numbers 0.60 to 1.03 and at various angles of attack.
Date: December 5, 1957
Creator: West, F. E., Jr.; Whitcomb, Charles F. & Schmeer, James W.
Partner: UNT Libraries Government Documents Department

Aerodynamic Loads on Tails at High Angles of Attack and Sideslip

Description: "Results are presented for the loads and moments acting on the individual tail surfaces of a body-tail combination over a wide range of angles of attack and sideslip. The effects of forebody length and panel-panel interference on the characteristics are included. It is shown that large nonlinear variations in these loads and moments, which occur at some combinations of angle of attack and sideslip, cannot be predicted by low-angle theory" (p. 1).
Date: July 23, 1957
Creator: Spahr, J. Richard & Polhamus, Edward C.
Partner: UNT Libraries Government Documents Department

Aerodynamic Performance of Several Techniques for Spike-Position Control of a Blunt-Lip Nose Inlet Having Internal Contraction; Mach Numbers of 0.63 and 1.5 to 2.0

Description: Memorandum presenting a study to determine locations of pressure sensors for controlling the spike position of a blunt-lip, axisymmetric inlet with internal contraction. The inlet performance was determined at Mach numbers of 0.63 and 1.5 to 2.0 for airflow schedules corresponding to those of a given turbojet engine over a wide range of ambient temperatures. The use of the ratio of a throat static pressure to either a local total or the spike-tip total pressure provided a signal that could set nearly maximum pressure recoveries at Mach numbers of 1.7 to 2.0 and within 6 percent of maximum recovery at Mach 1.5.
Date: September 17, 1957
Creator: Anderson, Arthur A. & Weinstein, Maynard I.
Partner: UNT Libraries Government Documents Department

Aerodynamics of Oscillating Control Surfaces at Transonic Speeds

Description: Memorandum presenting a discussion of oscillating flap-type and all-movable controls with particular emphasis on the aerodynamic forces and moments at transonic speeds. Hinge-moment results from recent wind-tunnel and rocket-powered-model tests are summarized for trailing-edge flap-type controls to illustrate the effects of control hinge-line position and profile shape on one-degree-of-freedom flutter of this type of control.
Date: June 17, 1957
Creator: Thompson, Robert F. & Clevenson, Sherman A.
Partner: UNT Libraries Government Documents Department

Aging Characteristics of Hastelloy B

Description: Report issued by the Oak Ridge National Laboratory discussing the aging characteristics of the alloy Hastelloy B. Materials, equipment, experimental procedures, and results used to determine the characteristics of the alloy are presented. This report includes tables, illustrations, and photographs.
Date: August 12, 1957
Creator: Clausing, Robert E.; Patriarca, P. & Manly, W. D.
Partner: UNT Libraries Government Documents Department