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The aerodynamic characteristics of a supersonic aircraft configuration with a 40 degree sweptback wing through a Mach number range from 0 to 2.4 obtained from various sources

Description: "A summary and analysis have been made of the results of various investigations to determine the aerodynamic characteristics of a supersonic aircraft configuration. The configuration has a wing with 40 degree sweepback at the quarter-chord line, aspect ratio 4, taper ratio 0.5, and 10-percent-thick circular-arc sections normal to the quarter-chord line. Experimental data were available for a Mach number range from 0.16 to 2.32. Results obtained from wing-flow, rocket-model, transonic-bump, and … more
Date: April 11, 1952
Creator: Spearman, M. Leroy & Robinson, Ross B.
Item Type: Refine your search to only Report
open access

Aerodynamic Characteristics of Three Deep-Step Planing-Tail Flying-Boat Hulls and a Transverse-Step Hull with Extended Afterbody

Description: From Summary: "An investigation was made to determine the aerodynamic characteristics in the presence of a wing of three-step planning-tail flying-boat hulls which differed only in the amount of step fairing. The purpose of comparison, tests were also made of a transverse-step hull with an extended afterbody."
Date: August 1952
Creator: Riebe, John M. & Naeseth, Rodger L.
Item Type: Refine your search to only Report
open access

Aerodynamic characteristics of two 25-percent-area trailing-edge flaps on an aspect ratio 2 triangular wing at subsonic and supersonic speeds

Description: Report presenting the results of an investigation of flap-type controls on a low-aspect-ratio triangular wing using NACA 0005-63 sections for a constant-chord and a constant-percent-chord control surface. Two flap profiles were investigated: one with a true contour and the other with a blunt trailing edge. Results regarding lift, drag, pitching moment, hinge moment, and rolling moments were obtained for several Mach numbers, a constant Reynolds number, and a range of angles of attack.
Date: July 22, 1952
Creator: Boyd, John W.
Item Type: Refine your search to only Report
open access

Aerodynamic Characteristics of Two Delta Wings at Mach Number 4.04 and Correlations of Lift and Minimum-Drag Data for Delta Wings at Mach Numbers From 1.62 to 6.9

Description: Report presenting tests of the aerodynamic characteristics of two delta wings of the same aspect ratio and airfoil sections at Mach number 4.04. The results indicated that the ratio of the experimental lift-curve slope to the theoretical two-dimensional lift-curve slope from previous testing is valid at this Mach number.
Date: December 23, 1952
Creator: Ulmann, Edward F. & Dunning, Robert W.
Item Type: Refine your search to only Report
open access

Aerodynamic characteristics of two-plane, unswept tapered wings of aspect ratio 3 and 3-percent thickness from tests on a transonic bump

Description: From Introduction: "The Ames Aeronautical Laboratory has in progress an experimental investigation of the aerodynamic characteristics of wings of interest in the design of high-speed fighter aircraft. This program included an investigation in the Ames 6-by 6-foot supersonic wind tunnel at both subsonic and supersonic Mach numbers of a wing-body combination having a 3-percent-thick, unswept, tapered wing with circular-arc sections and an aspect ratio of 3.1 (reference 1).
Date: May 2, 1952
Creator: Emerson, Horace F. & Gale, Bernard M.
Item Type: Refine your search to only Report
open access

The Aerodynamic Design of High Mach Number Nozzles Utilizing Axisymmetric Flow with Application to a Nozzle of Square Test Section

Description: From Introduction: "A method for the design of three-dimensional nozzles based on axi-symmetric flow is presented in this paper. The design method presented in this paper is general; however, as an illustrative example of the design of a Mach number 10 nozzle with square test section is included."
Date: June 1952
Creator: Beckwith, Ivan E.; Ridyard, Herbert W. & Cromer, Nancy
Item Type: Refine your search to only Report
open access

The Aerodynamic Design of Supersonic Propellers from Structural Considerations

Description: From Summary: "The aerodynamic design of propellers from considerations of centrifugal force is presented. By applying a constant minimum value of thickness ratio from root to tip and allowing the distribution of required area to appear in the blade plan form, propellers with good efficiency are realized at high Mach numbers by the method of this paper."
Date: December 1952
Creator: Hammack, Jerome B.
Item Type: Refine your search to only Report
open access

Aerodynamic Load Measurements Over a Leading-Edge Slat on a 40 Degree Sweptback Wing at Mach Numbers From 0.10 to 0.91

Description: Report presenting an investigation of the aerodynamic loads on a leading-edge slat on a 40 degree sweptback wing with NACA 64(sub 1)-112 airfoil sections in the low-turbulence pressure tunnel. Results regarding wing force data, slat force data, and slat pressure distributions are provided.
Date: September 23, 1952
Creator: Cahill, Jones F. & Nuber, Robert J.
Item Type: Refine your search to only Report
open access

Aerodynamic Loading Characteristics of a Wing-Fuselage Combination Having a Wing of 45 Degrees Sweepback Measured in the Langley 8-Foot Transonic Tunnel

Description: Report presenting an investigation of the aerodynamic loading characteristics of a wing-fuselage combination in the slotted test section of the transonic tunnel. The test was part of a systematic investigation of the effects of varying the amount of sweepback on wings in order to determine their suitability for transonic flight. Results regarding span load characteristics, normal-force characteristics, wing-tip angle of twist, spanwise distribution of section pitching-moment coefficient, pitchi… more
Date: May 19, 1952
Creator: Loving, Donald L. & Williams, Claude V.
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) 2: aerodynamic load distributions of series of five bodies having conical noses and cylindrical afterbodies

Description: Report presenting an experimental investigation to determine the aerodynamic load distributions of a series of five bodies with conical or slightly blunted noses and cylindrical afterbodies in the 1- by 1-foot supersonic wind tunnel. Pressure distributions and viscous drags were measured at Mach number 3.12 for a range of Reynolds numbers and angles of attack.
Date: May 8, 1952
Creator: Jack, John R. & Gould, Lawrence I.
Item Type: Refine your search to only Report
open access

Aeronautical Characteristics of a 45 Degree Sweptback Wing-Fuselage Combination and the Fuselage Alone Obtained in the Langley 8-Foot Transonic Tunnel

Description: Report presenting a fuselage and wing-fuselage combination with a wing of 45 degrees sweepback of the 0.25-chord line, aspect ratio 4, taper ratio 0.6, and NACA 65A006 airfoil sections in the slotted test section of a transonic tunnel for a range of Mach numbers and angles of attack. Results regarding lift characteristics, drag characteristics, lift-drag ratios, pitching-moment characteristics, a comparison with other test results, and base-pressure characteristics are provided.
Date: September 16, 1952
Creator: Osborne, Robert S. & Mugler, John P., Jr.
Item Type: Refine your search to only Report
open access

Aeronautical interference effects on normal and axial force coefficients of several engine-strut-body configurations at Mach numbers of 1.8 and 2.0

Description: Report presenting an investigation of the aerodynamic interference effects associated with a missile configuration, consisting of a pointed body of revolution with one or two ramjet engines strut-mounted in a vertical plane through the center line of the body, at several engine locations relative to the body and a range of angles of attack. The experimental data indicated increases in slope of the normal force curve with outward movement of the engines. Results regarding the characteristics of … more
Date: April 28, 1952
Creator: Kremzier, Emil J. & Dryer, Murray
Item Type: Refine your search to only Report
open access

Air Sampling Chamber for S.I.R.

Description: Abstract: An ionization chamber to monitor air for beta activity is described. Operating curves are given, as well as results of shock and vibration tests. Recommendation for improved design are included.
Date: August 8, 1952
Creator: Dewes, R. A. & Goodale, E. E.
Item Type: Refine your search to only Report
open access

Airborne Radioactivity Survey of Part of the Navajo Indian Reservation of Utah and Arizona

Description: From introduction: The purpose of an airborne radioactivity survey is to locate ground areas of higher than normal radioactivity which might lead to discovery of uranium mineralization. For this type of survey, gamma-ray detection equipment employing either a geiger counter or a scintillation counter can be mounted in a fixed wing aircraft or a helicopter.
Date: February 29, 1952
Creator: Cummings, Winthrop L.
Item Type: Refine your search to only Report
open access

Airborne Radioactivity Surveys in the Mojave Desert Region, Kern, Riverside, and San Bernardino Counties, California

Description: From abstract: Airborne radioactivity surveys in the Mojave Desert region, Kern, Riverside, and San Bernardino counties were made in five areas recommended as favorable for the occurrence of radioactive raw materials: (1) Rock Corral area, San Bernardino County. (2) Searles Station area, Kern County. (3) Soledad area, Kern County, (4) White Tank area, Riverside and San Bernardino counties. (5) Harvard Hills area, San Bernardino County. Anomalous radiation was detected in all but the Harvard Hil… more
Date: July 1952
Creator: Moxham, Robert Morgan
Item Type: Refine your search to only Report
open access

Airborne Radiometric Survey of the East Flank of the Big Horn Mountains, Wyoming and Montana

Description: Abstract: An airborne radiometric survey of parts of the east flank of the Big Horn Mountains was begun on June 23, and completed on August 27, 1952. An area of approximately 250 square miles was covered, and only two anomalies were found in the entire area. Flight lines were arranged in accordance with the geology of the area, particular attention being given to formations the stratigraphic equivalents of which are known to be uranium bearing in other areas. Two additional zones of radioactivi… more
Date: September 26, 1952
Creator: Jones, E. E.
Item Type: Refine your search to only Report
open access

Aircraft Nuclear Propulsion Project Quarterly Progress Report: Period Ending December 10, 1951

Description: This quarterly progress report details the ongoing research and experiments at the Oak Ridge National Laboratory as part of the Aircraft Nuclear Propulsion Project. The first part of this report discusses reactor theory and design. The second part of this report is not included. The third part of this report discusses materials research. The fourth part of this report includes appendixes
Date: March 6, 1952
Creator: Briant, R. C. & Cottrell, W. B.
Item Type: Refine your search to only Report
open access

Aircraft Nuclear Propulsion Project Quarterly Progress Report for Period Ending June 10, 1952

Description: This quarterly progress report details ongoing work at the Oak Ridge National Laboratory as part of the Aircraft Nuclear Propulsion Project. Topics of discussion include reactor theory and design, shielding research, materials research, appendixes with information on ongoing analytical chemical studies.
Date: August 5, 1952
Creator: Briant, R. C.; Buck, J. H.; Miller, A. J. & Cottrell, W. B.
Item Type: Refine your search to only Report
open access

Aircraft Nuclear Propulsion Project Quarterly Progress Report for Period Ending June 10, 1952

Description: This quarterly progress details ongoing research at the Oak Ridge National Laboratory as a part of the Aircraft Nuclear Propulsion Project. Topics discussed include reactor theory and design, [part two is not included], materials research, and appendixes with information on analytical chemical studies.
Date: October 23, 1952
Creator: Briant, R. C.; Buck, J. H.; Miller, A. J. & Cottrell, William B.
Item Type: Refine your search to only Report
open access

Aircraft Nuclear Propulsion Project Quarterly Progress Report for Period Ending March 10, 1952

Description: This quarterly progress discusses the ongoing work at the Oak Ridge National Laboratory for the quarter ending in March 10, 1952. Topics discussed include reactor theory and design, shielding research, materials research, and includes appendixes with supplemental information.
Date: May 7, 1952
Creator: Briant, R. C.; Miller, A. J. & Cottrell, William B.
Item Type: Refine your search to only Report
open access

Aircraft Nuclear Propulsion Project Quarterly Progress Report: Period Ending September 10, 1951

Description: The first part of this quarterly progress report details reactor theory and design, discussing the aircraft reactor experiment, experimental reactor engineering, reactor physics, and critical experiments. The second part of this report is not included. The third part of this quarterly progress report details materials research, discussing corrosion research, physical properties and heat-transfer research, metallurgy and ceramics, chemistry of high-temperature liquids, and radiation damage. The … more
Date: January 9, 1952
Creator: Briant, R. C.; Ellis, C. B. & Cottrell, William B.
Item Type: Refine your search to only Report
open access

Airfoil profiles for minimum pressure drag at supersonic velocities: Application of shock-expansion theory, including consideration of hypersonic range

Description: From Summary: "A comparison of optimum profiles determined by the shock-expansion method of this report with corresponding profiles determined by the linearized-theory method of a previous report shows only small differences in shape at Mach numbers up to infinity even though the linearized theory at high supersonic Mach numbers breaks down completely insofar as the drag of the profile is concerned. Curves are presented which show that for thin airfoils the use of a trailing-edge thickness cons… more
Date: September 17, 1952
Creator: Chapman, Dean R.
Item Type: Refine your search to only Report
open access

Airfoil profiles for minimum pressure drag at supersonic velocities -- general analysis with application to linearized supersonic flow

Description: From Summary: "A theoretical investigation is made of the airfoil profile for minimum pressure drag at zero lift in supersonic flow. In the first part of the report a general method is developed for calculating the profile having the least pressure drag for a given auxiliary condition, such as a given structural requirement or a given thickness ratio. To illustrate the general method, the optimum airfoil, defined as the airfoil having minimum pressure drag for a given auxiliary condition, is ca… more
Date: 1952
Creator: Chapman, Dean R.
Item Type: Refine your search to only Report
open access

Alloys of Uranium with Zirconium, Chromium, Columbium, Vanadium, and Molybdenum

Description: Abstract: Information on five uranium binary alloy systems has been surveyed. These systems are the alloys of uranium with zirconium, chromium, columbium, vanadium, and molybdenum. The equilibrium diagrams are discussed, and where available, data have been included on diffusion studies, cladding experiments, and mechanical properties.
Date: June 19, 1952
Creator: Saller, Henry A. & Rough, Frank A.
Item Type: Refine your search to only Report
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