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Ternary Phase Equilibria in Transition Metal-Boron-Carbon-Silicon Systems. Part I. Related Binary Systems. Volume I. Mo-C System
Report Number: AFML TR 65-2 Part 1 Volume 1
Author(s): E. Rudy; ST. Windish; Y. A. Chang
Corporate Author: Aerojet-General Corporation
Laboratory: Air Force Materials Laboratory
Publication Date: 3/1/1965
Pages: 176
Contract: AF 33(615)-1249
Project: 7350
Task: 735001
AD Number: AD0463558
Photo Enhancement: Complete
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Ternary Phase Equilibria In Transition Metal-Boron-Carbon-Silicon Systems. Part I. Related Binary Systems. Volume V. Ta-C System. Partial Investigation In The Systems Nb-C And V-C.
Report Number: AFML TR 65-2 Part 1 Volume 5
Author(s): Rudy, E.; Harmon, D. P.
Corporate Author: Aerojet-General Corporation
Laboratory: Air Force Materials Laboratory
Publication Date: 12/1/1965
Pages: 90
Contract: AF 33(615)-1249
Project: 7350
Task: 735001
AD Number: AD0478182
Photo Enhancement: Complete
Abstract Text:
The alloy system tantalum-carbon was investigated by means of X-ray, DTA, and melting point techniques on heat-treated and chemically analyzed alloys; a complete phase diagram was established. Analogously to the findings in the Ta-C systems, a previously unknown phase reaction of the Nb2C phase was found to occur at high temperatures. The melting temperatures of the monocarbide phase and the NbC-C eutectic reaction isotherm were redetermined. The alpha- beta-Me2C-phase reaction could not be found in the vanadium-carbon system.
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Ternary Phase Equilibria In Transition Metal-Boron-Carbon-Silicon Systems. Part I. Related Binary Systems. Volume VI. W-C System: Supplemental Information On The Mo-C System
Report Number: AFML TR 65-2 Part 1 Volume 6
Author(s): Rudy, E.
Corporate Author: Aerojet-General Corp Sacramento CA Materials Research Lab
Laboratory: Air Force Materials Laboratory
Publication Date: 1/1/1966
Pages: 94
Contract: AF 33(615)-1249
Project: 7350
Task: 735001
AD Number: AD0480948
Photo Enhancement: Complete
Abstract Text:
The alloy system tungsten-carbon was investigated by means of X-ray, DTA, and melting point techniques on chemically analyzed alloys, and a complete phase diagram was established. Supplementary Investigations performed on the molybdenum-carbon system are in confirmation of our previous findings regarding the alpha-beta-Mo2C phase separation as well as the phase relations between eta - and alpha-MoC1-x. The results are discussed and compared with previously reported system data.
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Ternary Phase Equilibria In Transition Metal-Boron-Carbon-Silicon Systems. Part I. Related Binary Systems. Volume VII. Tib System
Report Number: AFML TR 65-2 Part 1 Volume 7
Author(s): Rudy, E.
Corporate Author: Aerojet-General Corp Sacramento CA Materials Research Lab
Laboratory: Air Force Materials Laboratory
Publication Date: 1/1/1966
Pages: 52
Contract: AF 33(615)-1249
Project: 7350
Task: 735001
AD Number: AD0480826
Photo Enhancement: Complete
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Ternary Phase Equilibria In Transition Metal-Boron-Carbon-Silicon Systems. Part I. Related Binary Systems. Volume VIII. Zr-B System
Report Number: AFML TR 65-2 Part 1 Volume 8
Author(s): Rudy, E.
Corporate Author: Aerojet-General Corp Sacramento CA Materials Research Lab
Laboratory: Air Force Materials Laboratory
Publication Date: 1/1/1966
Pages: 44
Contract: AF 33(615)-1249
Project: 7350
Task: 735001
AD Number: AD0480949
Photo Enhancement: Complete
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Ternary Phase Equilibria In Transition Metal-Boron-Carbon-Silicon Systems. Part I. Related Binary Systems. Volume IX. Hf-B System
Report Number: AFML TR 65-2 Part 1 Volume 9
Author(s): Rudy, E.
Corporate Author: Aerojet-General Corp Sacramento CA Materials Research Lab
Laboratory: Air Force Materials Laboratory
Publication Date: 1/1/1966
Pages: 52
Contract: AF 33(615)-1249
Project: 7350
Task: 735001
AD Number: AD0480812
Photo Enhancement: Complete
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Ternary Phase Equilibrium In Transition Metal-Boron-Carbon-Silicon Systems. Part II. Ternary Systems. Volume XII. Ti-Zr-B System. Investigation Of Pseudo-Binary Systems Zrb2-Nbb2, Zrb2-Tab2, And Hfb2-Nbn2
Report Number: AFML TR 65-2 Part 2 Volume 12
Author(s): Eckert, T. E.
Corporate Author: Aerojet-General Corp Sacramento CA Materials Research Lab
Laboratory: Air Force Materials Laboratory
Publication Date: 1/1/1967
Pages: 62
Contract: AF 33(615)-1249
Project: 7350
Task: 735001
AD Number: AD0803913
Photo Enhancement: Complete
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Ternary Phase Equilibria In Transition Metal-Boron-Carbon-Silicon Systems. Part II. Ternary Systems. Volume XIII. Phase Diagrams Of The Systems Ti-B-C, Zr-B-C, And Hf-B-C.
Report Number: AFML TR 65-2 Part 2 Volume 13
Author(s): Rudy, E.
Corporate Author: Aerojet-General Corp Sacramento CA Materials Research Lab
Laboratory: Air Force Materials Laboratory
Publication Date: 12/1/1966
Pages: 232
Contract: AF 33(615)-1249
Project: 7350
Task: 735001
AD Number: AD0803270
Photo Enhancement: Complete
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Ternary Phase Equilibria In Transition Metal-Boron-Carbon-Silicon Systems. Part II. Ternary Systems. Volume XVII. Constitution Of Ternary Ta-Mo-C Alloys
Report Number: AFML TR 65-2 Part 2 Volume 17
Author(s): Rudy, E.; Windisch, St.; Brukl, C. E.
Corporate Author: Aerojet-General Corp Sacramento Calif Materials Research Lab
Laboratory: Air Force Materials Laboratory
Publication Date: 12/1/1967
Pages: 84
Contract: AF 33(615)-1249
Project: 7350
Task: 735001
AD Number: AD0664345
Photo Enhancement: Complete
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Ternary Phase Equilibria In Transition Metal-Boron-Carbon-Silicon Systems. Part IV. Thermochemical Calculations, Volume III. Computational Approach To The Calculation Of Ternary Phase Diagrams.
Report Number: AFML TR 65-2 Part 4 Volume 3
Author(s): Chang, Y. A.
Corporate Author: Aerojet-General Corporation
Laboratory: Materials Laboratory
Publication Date: 10/1/1966
Pages: 84
Contract: AF 33(615)-1249
Project: 7350
Task: 735001
AD Number: AD0803914
Photo Enhancement: Not Needed
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An Apparatus For Determination Of The Tensile Behavior Of Brittle Fibers
Report Number: AFML TR 65-47
Author(s): Dan B. Darden
Corporate Author: Southern Research Institute
Publication Date: 2/1/1965
Pages: 48
AD Number: AD0462837
Abstract Text:
An apparatus was built capable of obtaining a load-elongation curve of brittle fibers 0.005 to 0.0002 in. in diameter at temperatures to 2500 F. The apparatus is contained in three units, the tensile frame and extensometer, the control cabinet, and the furnace power supply. The tensile frame is a horizontal, screw-driven type with crosshead speeds from 0.004 to 2.0 in. per minute and full-scale load ranges from 100 to 10,000 grams. The major features are the specimen grips and the optical extensometer. Grips are selfenergizing tongs with deformable jaws set at a 4 degree angle. The extensometer tracks the silhouettes of two mu-shaped wire gage markers hung on the specimen. The load cell and the extensometer outputs are fed to an X-Y recorder that plots a complete, calibrated, load-elongation curve to failure. Excellent results have been obtained on trial runs. Noise of the extensometer is less than 0.00002 inch and nonlinearity is less than 1%.
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Ultrasonic Studies Of The Nonlinear Properties And Of The Deformation Of Solids. Part II
Report Number: AFML TR 65-56 Part 2
Author(s): Hikata, Akira; Sewell, Frank A., Jr.; Chick, Bruce B.; Elbaum, Charles
Corporate Author: Brown Univ Providence RI Metals Research Lab
Laboratory: Air Force Materials Laboratory
Publication Date: 6/1/1966
Pages: 82
Contract: AF 33(657)-8324
Project: 7360
Task: 736002
AD Number: AD0802089
Photo Enhancement: Not Needed
Notes: Due to a printing error, pages 6, 7, 66 & 67 are blank
Abstract Text:
The report covers research on the nonlinear properties of solids, with special emphasis on the role of dislocations in harmonic generation, the effects of plastic deformation and dislocation interactions with point defects. Dislocation breakaway from pinning points was considered as a possible source of harmonic generation; this contribution is of the same sign as that from screw dislocations. Experiments were carried out on aluminum single crystals with several different impurity contents, as measured by electrical resistivity ratios R(300 K)/R(4.2 K) ranging from 270 to 3100. Amplitudes of the third harmonic, as well as the attenuation of the fundamental wave, were measured as a function of bias stress, amplitude of the fundamental wave and amount of plastic deformation. The results of these experiments are consistent with the qualitative predictions of the theory presented.
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Final Report on Manufacturing Method for Foamed Metallic and Ceramic Heat Shielding Materials
Report Number: AFML TR 65-126
Author(s): Don W. Bissell; James B. Cloud
Corporate Author: Ipsen Industries, Inc.
Laboratory: Air Force Materials Laboratory
Publication Date: 6/1/1965
Pages: 278
Contract: AF 33(657)-11286
Project: 8117
Task: 811751
AD Number: AD0472142
Photo Enhancement: Incomplete
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Mechanisms Of Fatigue In 1100-0 And 2024-T4 Aluminum
Report Number: AFML TR 65-127
Author(s): Grosskreutz, J. C.; Shaw, G. G.
Corporate Author: Midwest Research Institute
Laboratory: Air Force Materials Laboratory
Publication Date: 7/1/1965
Pages: 48
Features:
Contract: AF 33(657)-10883
Project: 7353
Task: 735301
AD Number: AD0470299
Photo Enhancement: Complete
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Nonlinear Effects Of Large Deflections And Material Damping On The Steady Tate Vibrations Of Beams
Report Number: AFML TR 65-167
Author(s): Chow, Shuh-Ture ; Sethna, P. R.
Corporate Author: University of Minnesota
Laboratory: Air Force Materials Laboratory
Publication Date: 7/1/1965
Pages: 102
Contract: Laboratory Research - No Contract
Project: 7351
Task: 735106
AD Number: AD0470724
Photo Enhancement: Not Needed
Abstract Text:
Nonlinear forced oscillations of slender beams are studied. The analysis takes into account both the nonlinear effects arising from large deflections of the beam and those arising from nonlinear material behavior. A hysteretic stress-strain law of the Davidenkov type is used in the analysis. Detailed results are given for large amplitude oscillations of beams with hinged ends. Theoretical results for a simply-supported beam are compared with experimental results.
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Aerospace Ceramics - Characteristics and Design Principles
Report Number: AFML TR 65-171
Author(s): Boland, Paul; Walton Jr., J. D.
Corporate Author: Georgia Institute of Technology
Laboratory: Air Force Materials Laboratory
Publication Date: 6/1/1965
Pages: 202
Contract: AF 33(615)-1308
Project: 7381
Task: 738105
AD Number: AD0469154
Photo Enhancement: Not Needed
Abstract Text:
The purpose of this research was to compile into a single volume present knowledge which will be useful to a designer applying ceramic materials in aerospace structural applications. All efforts were directed toward the collection of information to acquaint designers with the properties, fundamental principles, characteristics, limitations, utilization and performance of high-temperature, load-bearing ceramic products and with the characteristics, limitations and utilization of ceramic processes. The information provided in this manual was obtained by means of intensive literature surveys and through contacts with various government agencies, industrial concerns, and academic institutions. The case-history approach was used for the compilation of information on the behavior of ceramic products and material systems subjected to thermal loads to provide the background for a possible correlation between known thermal shock theories and brittle materials behavior.
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Mechanisms Associated With Long Time Creep Phenomena. Part II: Evaluation Of Long Time Creep Results.
Report Number: AFML TR 65-181 Part 2
Author(s): Widmer, R.; Dhosi, J. M.; Grant, N. J.
Corporate Author: New England Materials laboratory, Inc.
Laboratory: Air Force Materials Laboratory
Publication Date: 3/1/1967
Pages: 132
Contract: AF 33(615)-2452
Project: 7351
Task: 735106
AD Number: AD0815679
Photo Enhancement: Complete
Abstract Text:
A creep-rupture investigation was conducted on two (2) high temperature alloys: a nickel-base age hardened alloy, Udimet 500, and a cobalt-base alloy, L-605. Creep-rupture tests were conducted over a range of rupture lives from 1 - 35,000 hours at 1200, 1350, 1500, 1650 at 1800 degrees F. Some long time tests are in progress and lives of approximately 50,000 hours are expected. The microstructure of all broken specimens was examined with various techniques and an attempt was made to correlate specific structural changes with the mechanical properties. Several different parameter techniques were examined to determine their utility in correlating and extrapolating creep and rupture data. The strength and the limitations of parametric extrapolation was extensively discussed with the example of the Manson-Haford parameter for which a computer program was available.
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Surface And Interfacial Effects In Relation To Brittleness In Refractory Metals
Report Number: AFML TR 65-226
Author(s): Fourdeux, A.; Rueda, F.; Votava, E.; Wronski, A.
Corporate Author: Union Carbide European Research Associates
Laboratory: Air Force Materials Laboratory
Publication Date: 4/1/1966
Pages: 154
Features: + Diagram(s) + Drawing(s) + Graph(s) + Photo(s) + Table(s)
Contract: AF 61(052)-774
Project: 7351
Task: 735101
AD Number: AD0486445
Photo Enhancement: Complete
Abstract Text:
An experimental program was conducted to compare the mechanical properties of high purity and impure niobium and the mechanical properties of high purity tungsten, both in polycrystalline and single crystal forms. Slip in high purity niobium takes place on the (110) planes in the (111) directions and yielding is governed by the conservative motion of jogs in screw dislocations, rather than by the unlocking of dislocations from the interstitial impurity cloud. Between the upper and lower yield points there is a sudden generation of a large number of dislocations by double cross-slip mechanism. High purity niobium has greater ductility, higher uniform elongation, increased work hardening, but lower strength than impure niobium. Further, it has a yield point in the temperature range 20 C to 800 C. Appreciable ductility can be achieved at room temperature in commercially pure tungsten, but the mechanical properties are strongly orientation dependent. The ductile-to-brittle transition temperature is about 100 C higher sintered material than in melted material which is of coarser gran size and probably higher purity. Very high purity polycrystalline tungsten was found to show some ductility down to -196 C in the recrystallization condition. However, the fracture process is controlled to a considerable extent by grain boundaries in the temperature range +200 C to -196 C.
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A Review of the Air Force Materials Research and Development Program
Report Number: AFML TR 65-228
Author(s):
Corporate Author: Materials Laboratory
Laboratory: Materials Laboratory
Publication Date: 7/1/1965
Pages: 165
AD Number: AD0470223
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A Review of the Air Force Materials Research and Development Program
Report Number: AFML TR 65-228 Supplement 1
Author(s):
Corporate Author: Materials Laboratory
Laboratory: Materials Laboratory
Publication Date: 1/1/1966
Pages: 197
AD Number: ADD432463
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Micromechanics Of Fiber-Reinforced Composites
Report Number: AFML TR 65-283
Author(s): Alexander, E. L.; Caputo, A. A.; Prado, M. E.; Hilzinger, J. E.
Corporate Author: Rocketdyne Canoga Park Calif Research Dept
Laboratory: Air Force Materials Laboratory
Publication Date: 11/1/1965
Pages: 168
Features: + Graph(s) + Photo(s) + Table(s)
Contract: AF 33(615)-1627
Project: None Given
Task: None Given
AD Number: AD0623644
Photo Enhancement: Complete
Abstract Text:
Research on the micromechanical behavior of composites reinforced with boron and other fibers is reported. A wide variety of reinforcing elements were used in photoelastic matrix materials to form beams, plates, and three-dimensional microspecimens of varied configurations. The effects of reinforcing element modulus and elongation were investigated in beams in four- and three-point loading. The degree of stiffening derived from various filament reinforcing materials was defined, and different failure mechanisms were investigated. Reinforced plates were biaxially tested, and fiber unbonding, buckling, and the subsequent stress redistribution were observed photoelastically. Significant advances in microphotoelasticity are reported. Very small specimens were loaded, and sharp microscopic photoelastic stress patterns (including induced flaw points) were photographed. The filament configurations represent typical laminate geometries, and small flaws were seen to have a remarkably wide field of influence.
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The Effect of Certain Damping Treatments on the Response of Idealized Aeroplane Structures Excited by Noise
Report Number: AFML TR 65-284
Author(s): D. J. Mead
Corporate Author: University of Southampton
Laboratory: Air Force Materials Laboratory
Publication Date: 8/1/1965
Pages: 203
Contract: AF 61(052)-627
Project: 7351
Task: 735106
AD Number: AD0473768
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Precracked Charpy Impact Fracture Toughness Properties Of Backup Flux-Welded Ti-5al-2.5 Sn Alloy Plate From -320 F To 550 F
Report Number: AFML TR 65-304
Author(s): Davis, Sidney O.; Niemi, Roger M.
Corporate Author: Air Force Materials Laboratory
Laboratory: Air Force Materials Laboratory
Publication Date: 1/1/1966
Pages: 28
Contract: Laboratory Research - No Contract
Project: 7381
Task: 738106
AD Number: AD0481554
Photo Enhancement: Complete
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Shielded Ceramic Composite Structure
Report Number: AFML TR 65-331
Author(s): Kummer, Donald L.; Rosenthal, Jerome J.; Lum, David W.
Corporate Author: McDonnell Aircraft Corp St Louis MO
Laboratory: Air Force Materials Laboratory
Publication Date: 10/1/1965
Pages: 412
Features: + Diagram(s) + Drawing(s) + Graph(s) + Photo(s) + Table(s)
Contract: AF 33(657)-10996
Project: 7997
Task: None Given
AD Number: AD0475002
Photo Enhancement: Complete
Abstract Text:
Alumina, zirconia, and thoria were selected for use in composite ceramic heat shields for the leading surfaces of lifting orbital re-entry vehicles. Coated columbium and molybdenum were selected for substructure materials. Commercially available low and high density alumina, zirconia, and thoria ceramics were evaluated for thermal shock resistance; and many high density, but no low density ceramics were found to be satisfactory. A sintered low density (95 lb/ft^3) thermal shock resistace zirconia was developed, but it was difficult to reproducibly manufacture. A sintered low density (125 lb/ft^3) thoria was developed that had low thermal shock resistance but could be reproducibly manufactured. Chemically bonded low and high density thermal shock resistant varieties of alumina, zirconia, and thoria were developed. Thermophysical properties were determined to temperatures as high as 4500 F for the ceramics utilized in this project. Analytical techniques were derived for predicting the thermal stress behavior of ceramics. Twenty-two subscale heat shield modules and three full size components were designed, fabricated and environmentally tested. The full size components were a 3.0 inch radius, 3400F leading edge; a 1.5 inch radius, 4000F leading edge; anda 6.0 radius, 5000F nose cap. The ceramic phase densities for these components were 57 lb/ft^, 97 lb/ft^3, and 166 lb/ft^3 respectively. Satisfactory techniques were developed for processing, fabricating, and assembling ceramic heat shields. Typical launch vibration and acoustical environmental conditions were not found to be critical, but re-entry thermal environment was found to be very critical. A MAPP-0X thermal test facility was developed for full scale testing. The 1.5 inch radius leading edge survived thermal testing although testing was prematurely terminated due to a test fixture failure. During thermal testing, the 3.0 inch readius leading edge cracked but remained intact and did not spall; and the 6.0 inch radius nose cap underwent severe surface erosion. These two failures were attributed to a combination of design and material shortcomings and the severity of the MAPP-0X thermal test environment.
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Exploratory Evaluation Of Filament-Wound Composites For Tankage Of Rocket Oxidizers And Fuels
Report Number: AFML TR 65-381
Author(s): Sanger, M. J.; Molho, R.; Howard, W. W.
Corporate Author: Aerojet-General Corporation
Laboratory: Air Force Materials Laboratory
Publication Date: 1/1/1966
Pages: 194
Features: + Diagram(s) + Drawing(s) + Foldout(s) + Graph(s) + Photo(s) + Table(s)
Contract: AF 33(615)-1671
Project: 7381
Task: 738101
AD Number: AD0477455
Photo Enhancement: Complete
Abstract Text:
This work was undertaken to provide information on materials and fabrication techniques for the design of filament-wound tankage for storable propellants, and to define a space experiment for validating the recommended materials and techniques. Resins and liner materials were studied, under accelerated exposure conditions, in the unreinforced form and as composites. Fabrication techniques were evaluated, and dynamic tests of subscale tankage were conducted. The environmental tests indicated that the materials and fabrication techniques selected for the tankage produced satisfactory filament-wound containers for storable propellants. A technique developed for bonding a metallic liner to the filament-wound chamber provided a solution to the problem of strain compatibility under pressure cycling at optimum strain levels for glass-filament-reinforced structures. Designs were developed for a prototype tank, and analysis showed that a spheroidal configuration with a length-to-diameter ratio of 1.0 was acceptable from the standpoint of space limitations and weight economy. A space experiment was defined for use in determining the efficiency of a filament-wound storable propellant tank over a period of 1 year in an earth-orbit environment.
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Evaluation Of High Strength Tungsten-Base Alloys
Report Number: AFML TR 65-397
Author(s): Cook, Charles R.
Corporate Author: TRW Inc.
Laboratory: Air Force Materials Laboratory
Publication Date: 11/1/1965
Pages: 115
Contract: AF 33(657)-11239
Project: 7351
Task: None Given
AD Number: AD0478443
Photo Enhancement: Incomplete
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Strengthening Mechanisms In Steel
Report Number: AFML TR 65-406
Author(s): Cohen, Morris; Moss, S. C.; Hoffman, D. W.; MacDonald, B. A.; Langford, G.
Corporate Author: Massachusetts Institute of Technology
Laboratory: Air Force Materials Laboratory
Publication Date: 6/1/1966
Pages: 139
Contract: AF 33(657)-8285
Project: 7351
Task: 735105
AD Number: AD0488350
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Compatibility Of Structural Materials With High Performance O-F Liquid Oxidizers
Report Number: AFML TR 65-414
Author(s): Tiner, N. A.; English, W. D.; Toy, S. M.
Corporate Author: Douglas Aircraft Co Inc Newport Beach Ca Astropower Lab
Publication Date: 11/1/1965
Pages: 137
Project: 0
Task: 0
AD Number: AD0477002
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