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1706-KER Coolant Test Facility Operations Manual

Description: This procedure is intended to be used as: 1. An instruction and guide for operation of the KER loops. 2. To aid in familiarization and understanding of the general operation of the loops. 3. To prevent lost time due to errors in loop operation. The procedure is not meant to be completely comprehensive in all details of loop operation.
Date: January 23, 1958
Creator: Dulin, R. V.
Item Type: Refine your search to only Report
open access

An Abrasive Cutoff Machine for Metallurgical Research on Radioactive Materials

Description: An abrasive cutoff machine design, based upon a previous model, (1) was undertaken to provide for the sampling of radioactive material. the design objective was; first, to provide samples for metallographic examination, second, to provide samples for physical and mechanical property testing, and, third, to meet the following design requirements: 1. Remote operation. 2. Airborne contamination control. 3. Radioactive waste collection. 4. Remote maintenance.
Date: January 5, 1957
Creator: Boyd, C. L.
Item Type: Refine your search to only Report
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Additional experimental heat-transfer and durability data on several forced-convection, air-cooled, strut-supported turbine blades of improved design

Description: Report presenting an investigation at the Lewis laboratory to develop air-cooled, strut-supported turbine blades. Six blades were investigated in a full-scale turbojet engine to obtain data on blade durability and blade-cooling effectiveness and strut temperature. Results regarding the heat-transfer investigation and blade-durability investigation are provided.
Date: January 19, 1955
Creator: Schum, Eugene F.
Item Type: Refine your search to only Report
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Aerodynamic characteristics at supersonic speeds of a series of wing-body combinations having cambered wings with an aspect ratio of 3.5 and a taper ratio of 0.2: Effects of sweep angle and thickness ratio on the aerodynamic characteristics in pitch

Description: Report presenting an investigation in the 4- by 4-foot supersonic pressure tunnel at Mach number 1.60 to determine the effects of sweep and thickness on the longitudinal characteristics of a series of wing-body combinations with cambered wings with an aspect ratio of 3.5 and taper ratio of 0.2. The results show the effects of sweep, thickness, and the horizontal canard surface on the lift, drag, and pitching-moment coefficients and lift-drag ratios. The lift-curve slope, aerodynamic-center loca… more
Date: January 10, 1952
Creator: Robinson, Ross B. & Driver, Cornelius
Item Type: Refine your search to only Report
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Aerodynamic Characteristics at Transonic Speeds of a Tapered 45 Degree Sweptback Wing of Aspect Ratio 3 Having a Full-Span Flap Type of Control With Overhang Balance: Transonic-Bump Method

Description: From Introduction: "This paper presents the aerodynamic characteristics of low-aspect-ratio sweptback wing having a full-span flap type of control employing an overhanging balance of 50 percent of the flap chord.The main purpose of this investigation was to determine if overhang balances are an effective means of reducing the hinge moments of flap type of controls at transonic speeds."
Date: January 25, 1952
Creator: Lockwood, Vernard E. & Hagerman, John R.
Item Type: Refine your search to only Report
open access

Aerodynamic characteristics at transonic speeds of a wing having a 45 degree sweep, aspect ratio 8, taper ratio 0.45, and airfoil sections varying from the NACA 63A010 section at the root to the NACA 63A006 section at the tip.

Description: Report presenting an investigation in the 7- by 10-foot tunnel to determine the transonic aerodynamic characteristics of a wing with a spanwise variation in thickness ratio. The wings investigated had 45 degrees of sweepback, aspect ratio 8, taper ratio 0.45, and airfoil sections tapered from an NACA 63A010 section at the root chord to an NACA 63A006 section at the tip chord. Results regarding lift characteristics, drag characteristics, and pitching-moment characteristics are provided.
Date: January 15, 1952
Creator: Morrison, William D., Jr. & Fournier, Paul G.
Item Type: Refine your search to only Report
open access

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 coefficien… more
Date: January 1957
Creator: Penland, Jim A.
Item Type: Refine your search to only Report
open access

Aerodynamic Characteristics of a Flying-Boat Hull Having a Length-Beam Ratio of 15, TED No. NACA 2206

Description: "An investigation was made in the Langley 300 MPH 7- by 10-foot tunnel to determine the aerodynamic characteristics of a flying-boat hull of a length-beam ratio of 15 in the presence of a wing. The investigation was an extension of previous tests made on hulls of length-beam ratios of 6, 9, and 12; these hulls were designed to have approximately the same hydrodynamic performance with respect to spray and resistance characteristics. Comparison with the previous investigation at lower length-beam… more
Date: January 23, 1951
Creator: Riebe, John M. & Naeseth, Rodger L.
Item Type: Refine your search to only Report
open access

Aerodynamic characteristics of a two-blade NACA 10-(3)(062)-045 propeller and of a two-blade NACA 10-(3)(08)-045 propeller

Description: Report discussing characteristics are given for the two-blade NACA 10-(3)(062)-045 propeller and for the two-blade NACA 10-(3)(08)-045 propeller over a range of advance ratio from 0.5 to 3.8, through a blade-angle range from 20 degrees to 55 degrees measured at the 0.75 radius. Maximum efficiencies of the order of 91.5 to 92 percent were obtained for the propellers. The propeller with the thinner airfoil sections over the outboard portion of the blades, the NACA 10-(3)(062)-045 propeller, had l… more
Date: January 1953
Creator: Solomon, William
Item Type: Refine your search to only Report
open access

Aerodynamic Characteristics of Damping Screens

Description: From Summary: "The experimental investigation of damping screens described herein was undertaken primarily to test theories of the effects of damping screens and to obtain information on the performance of screens in oblique flow. The characteristics investigated include the damping of longitudinal and lateral components of turbulence, the effect of screens on scale, the conditions for the production of turbulence and eddies by screens, and the damping of spatial variations of mean speed."
Date: January 1950
Creator: Schubauer, G. B.; Spangenberg, W. G. & Klebanoff, P. S.
Item Type: Refine your search to only Report
open access

Aerodynamic characteristics of NACA 0012 airfoil section at angles of attack from 0 degrees to 180 degrees

Description: Report presenting the aerodynamic characteristics of the NACA 0012 airfoil section at a range of angles of attack from 0 to 180 degrees. Data were obtained at two different Reynolds numbers depending on whether the airfoil surfaces were smooth or had roughness applied at the leading and trailing edges. After the stall with the rounded edge of the airfoil foremost, a second lift-coefficient peak was obtained at an angle of attack of about 45 degrees.
Date: January 1955
Creator: Critzos, Chris C.; Heyson, Harry H. & Boswinkle, Robert W., Jr.
Item Type: Refine your search to only Report
open access

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… more
Date: January 14, 1957
Creator: Morris, Odell A.
Item Type: Refine your search to only Report
open access

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.
Item Type: Refine your search to only Report
open access

Aerodynamic Loading Characteristics in Sideslip of a 45 Degree Sweptback Wing With and Without a Fence at High Subsonic Speeds

Description: Report presenting an investigation of the effects of sideslip on the aerodynamic loading characteristics of a 45 degree sweptback wing of aspect ratio 4 for a range of angles of attack, angles of sideslip, and Mach numbers. The load distributions, root bending-moment coefficient, and rolling moment due to sidestep were explored.
Date: January 28, 1955
Creator: Kuhn, Richard E.
Item Type: Refine your search to only Report
open access

Aerodynamic study of a wing-fuselage combination employing a wing swept back 63 degrees : effectiveness at supersonic speeds of a 30-percent chord, 50-percent semispan elevon as a lateral control device

Description: Report presenting the effectiveness of a 50-percent-semispan, constant-percent-chord elevon, and of upper-space spoilers as lateral control surfaces for a wing-fuselage combination with a wing swept back 63 degrees over a range of Mach numbers. For the elevon, results indicated that only about half of the predicted rolling-moment effectiveness was realized. The spoilers were found to be inferior to the elevons for lateral control because of a rapid loss of effectivness above an angle of attack … more
Date: January 18, 1951
Creator: Olson, Robert N. & Mead, Merrill H.
Item Type: Refine your search to only Report
open access

Aerodynamics of slender bodies at Mach number of 3.12 and Reynolds numbers from 2 x 10(exp 6) to 15 x 10(exp 6) 4: aerodynamic characteristics of series of four bodies having near-parabolic noses and cylindrical afterbodies

Description: Pressure distributions and forces for a series of four bodies of revolution having nose-fineness ratios varying from 4 to 10 have been obtained and compared with theory for a Mach number of 3.12, a Reynolds number range of 2x10(sup)6 to 14x10(sup)6, and angles of attack from zero to 9 degrees. In general, a comparison of the experimental data with a second-order theory showed good agreement for the range of variables investigated.
Date: January 25, 1954
Creator: Jack, John R. & Moskowitz, Barry
Item Type: Refine your search to only Report
open access

Aeronautical study of a wing-fuselage combination employing a wing swept back 63 degrees: Characteristics at supersonic speeds of a model with the wing twisted and cambered for uniform load

Description: Report presenting the lift, drag, and pitching-moment characteristics of a wing-fuselage combination employing a wing with the leading edge swept back 63 degrees and cambered and twisted for a uniform load at a lift coefficient of 0.25 and Mach number 1.53. The experimental results are compared to those from other investigations. A maximum lift-drag ratio of 8.9 and a minimum drag coefficient of 0.0145 was obtained.
Date: January 9, 1950
Creator: Hall, Charles F. & Heitmeyer, John C.
Item Type: Refine your search to only Report
open access

Aging of Al-Li Alloys - Part I

Description: Technical report outlining experiments on aluminum-lithium alloys. From Abstract: "Aluminum-lithium alloys are subject to precipitation from solid solution, and may be age hardened by the same techniques used for more common aluminum alloys. Spherical particles of precipitate were observed with the electron microscope in 1.5% and 2.8% Al-Li alloys after aging for times comparable to those required to produce maximum hardness. Rod-shaped particles that were oriented parallel to either the (110) … more
Date: January 1959
Creator: Angerman, C. L.
Item Type: Refine your search to only Report
open access

An Air Concentrator for Very Low Grade Colorado Plateau Uranium Ores

Description: Report discussing the use of an air concentrator on uraniferous sandstones for producing concentrates with over ten times the amount of uranium as original sandstone. A description of the concentrator, information regarding its operation, results of the concentration, information on the concentrator's applications, and a general summary are included.
Date: January 1953
Creator: Stieff, L. R. & Erickson, E. S., Jr.
Item Type: Refine your search to only Report
open access

Airborne Reconnaissance Project, Green River Basin, Wyoming

Description: Abstract: A part of the Green River Basin airborne reconnaissance project, re: memo to Phillip L. Merritt, March 12, 1954, Proposed Airborne Reconnaissance Project, Green River Basin, Wyoming, was completed during the months from July though October 1954. No uranium mineralization of commercial value was found.
Date: January 1955
Creator: Magleby, Dan N. & Meehan, R. J.
Item Type: Refine your search to only Report
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