103,183 materials
Style 7781 glass fabric (ECDE 75-1/0 yarn), an 8-harness satin weave that drapes readily over compound curvature, in a 506 phenolic matrix. Phenolic-matrix glass laminates are specified where fire, smoke and toxicity behaviour governs rather than strength. Phenolic chars instead of burning and releases little smoke, which is why it dominates commercial aircraft interiors — sidewalls, ceilings, galley and lavatory panels, ducting — and why it is also used in ablative and fire-barrier structure. The handbook characterises it from -65 °F to 500 °F, consistent with sustained high-temperature service. MatWorld carries 59 tensile, compressive and shear curves for this system, digitised from MIL-HDBK-17-2F Volume 2 (US Government work, public domain).
Engineered laminate of 5505, stacked [(0/90):2]S. Properties here are laminate-level effective values in the laminate's own axes — not the lamina constants, which live on the parent prepreg (5505 — boron fibre / epoxy). From MIL-HDBK-17-2F Volume 2 (US Government work, public domain).
Boron fibre in an epoxy matrix. Boron/epoxy has exceptional specific stiffness and compressive strength — boron filament is markedly stiffer than carbon and does not buckle under compression the way graphite does. Historically used for empennage skins and stiffeners on military aircraft, its enduring role is bonded composite repair: boron patches restore stiffness to cracked metallic structure without the galvanic problems carbon introduces against aluminium. The handbook characterises it from -67 °F to 375 °F, consistent with elevated-temperature service. MatWorld carries 44 tensile and compressive curves for this system, digitised from MIL-HDBK-17-2F Volume 2 (US Government work, public domain).
7781 E-glass Fabric (Clark-Schwebel) glass fibre in a PR 381 (3M) epoxy matrix. Glass/epoxy is the workhorse of secondary aircraft structure and tooling: far cheaper than carbon, electrically transparent, and tolerant of impact and handling damage. It is chosen where stiffness-per-pound is not the governing requirement — radomes and antenna windows, fairings and access panels, lay-up tooling, and marine and industrial laminates. per MIL-C-9084C Type Vlll B, Yarn DE-75, no surface treatment.
7781-glass (Hexcel/Burlington) glass fibre in an EA 9396 (Dexter-Hysol) epoxy matrix, supplied as 8 hs fabric. Glass/epoxy is the workhorse of secondary aircraft structure and tooling: far cheaper than carbon, electrically transparent, and tolerant of impact and handling damage. It is chosen where stiffness-per-pound is not the governing requirement — radomes and antenna windows, fairings and access panels, lay-up tooling, and marine and industrial laminates. The handbook characterises it from -65 °F to 200 °F, consistent with moderately elevated service. MatWorld carries 23 tensile, compressive and shear curves for this system, digitised from MIL-HDBK-17-2F Volume 2 (US Government work, public domain).
AS4 (Hercules) carbon fibre (6,000-filament tow) in a 3502 (Hercules) epoxy matrix, supplied as 5-harness satin weave. Carbon/epoxy is the primary structural composite of modern aerospace: the highest stiffness-to-weight of the common systems, with well-characterised and predictable behaviour. It is used for wing and empennage skins, spars and ribs, fuselage panels and control surfaces — anywhere weight is the governing cost. Surface-treated.
Astroquartz II (J. P. Stevens) quartz fibre in an F650 (Hexcel) bismaleimide matrix, supplied as 8-harness satin weave.
AS4 (Hercules) carbon fibre (12,000-filament tow) in a 3502 (Hercules) epoxy matrix, supplied as tape. Carbon/epoxy is the primary structural composite of modern aerospace: the highest stiffness-to-weight of the common systems, with well-characterised and predictable behaviour. It is used for wing and empennage skins, spars and ribs, fuselage panels and control surfaces — anywhere weight is the governing cost. Surface-treated.
AS4 12k (Hercules) carbon fibre (12,000-filament tow) in an E7K8 (U.S. Polymeric) epoxy matrix, supplied as tape. Carbon/epoxy is the primary structural composite of modern aerospace: the highest stiffness-to-weight of the common systems, with well-characterised and predictable behaviour. It is used for wing and empennage skins, spars and ribs, fuselage panels and control surfaces — anywhere weight is the governing cost.
Engineered laminate of AS4/3501-6 unidirectional tape, stacked [0/45/90/-45]:s. Properties here are laminate-level effective values in the laminate's own axes — not the lamina constants, which live on the parent prepreg (AS4/3501-6 unidirectional tape). From MIL-HDBK-17-2F Volume 2 (US Government work, public domain).
AS4 (Hercules) carbon fibre (12,000-filament tow) in a 3502 (Hercules) epoxy matrix, supplied as tape. Carbon/epoxy is the primary structural composite of modern aerospace: the highest stiffness-to-weight of the common systems, with well-characterised and predictable behaviour. It is used for wing and empennage skins, spars and ribs, fuselage panels and control surfaces — anywhere weight is the governing cost. Surface-treated.
AS4 (Hercules) carbon fibre in a 5250-3 (Narmco) bismaleimide matrix, supplied as tape. Carbon/BMI extends carbon/epoxy to sustained service around 350-450 °F, well beyond epoxy's limit, while processing in broadly similar tooling. It is used for engine nacelles and nozzles, structure near exhaust, and supersonic-aircraft skins subject to aerodynamic heating. The handbook characterises it from -67 °F to 450 °F, consistent with elevated-temperature service. MatWorld carries 16 tensile, compressive and shear curves for this system, digitised from MIL-HDBK-17-2F Volume 2 (US Government work, public domain).
AS4 3k (Hercules) carbon fibre (3,000-filament tow) in an E7K8 (U.S. Polymeric) epoxy matrix, supplied as plain weave. Carbon/epoxy is the primary structural composite of modern aerospace: the highest stiffness-to-weight of the common systems, with well-characterised and predictable behaviour. It is used for wing and empennage skins, spars and ribs, fuselage panels and control surfaces — anywhere weight is the governing cost.
Engineered laminate of AW193P plain weave, stacked [0:f/90:f/+-45:f]:s. Properties here are laminate-level effective values in the laminate's own axes — not the lamina constants, which live on the parent prepreg (AW193P plain weave — AS4 carbon/3501-6). From MIL-HDBK-17-2F Volume 2 (US Government work, public domain).
AS4 (Hercules) carbon fibre (3,000-filament tow) in a 3501-6 (Hercules) epoxy matrix, supplied as plain weave. Carbon/epoxy is the primary structural composite of modern aerospace: the highest stiffness-to-weight of the common systems, with well-characterised and predictable behaviour. It is used for wing and empennage skins, spars and ribs, fuselage panels and control surfaces — anywhere weight is the governing cost. The handbook characterises it from -65 °F to 200 °F, consistent with moderately elevated service. MatWorld carries 4 tensile, compressive and shear curves for this system, digitised from MIL-HDBK-17-2F Volume 2 (US Government work, public domain).
Engineered laminate of AW280-5H/3501-6, stacked [(0/45/90/-45):f]:s. Properties here are laminate-level effective values in the laminate's own axes — not the lamina constants, which live on the parent prepreg (AW280-5H/3501-6 — AS4 carbon/3501-6). From MIL-HDBK-17-2F Volume 2 (US Government work, public domain).
Engineered laminate of AW280-5H/3501-6, stacked [(0/+-45/90):f]:s. Properties here are laminate-level effective values in the laminate's own axes — not the lamina constants, which live on the parent prepreg (AW280-5H/3501-6 — AS4 carbon/3501). From MIL-HDBK-17-2F Volume 2 (US Government work, public domain).
AS4 (Hercules) carbon fibre (3,000-filament tow) in a 3501-6 (Hercules) epoxy matrix, supplied as 5-harness satin weave. Carbon/epoxy is the primary structural composite of modern aerospace: the highest stiffness-to-weight of the common systems, with well-characterised and predictable behaviour. It is used for wing and empennage skins, spars and ribs, fuselage panels and control surfaces — anywhere weight is the governing cost. The handbook characterises it from -65 °F to 200 °F, consistent with moderately elevated service. MatWorld carries 4 tensile, compressive and shear curves for this system, digitised from MIL-HDBK-17-2F Volume 2 (US Government work, public domain).
AS4 (Hercules) carbon fibre (3,000-filament tow) in a 3501-6s (Hercules) epoxy matrix, supplied as 5-harness satin weave. Carbon/epoxy is the primary structural composite of modern aerospace: the highest stiffness-to-weight of the common systems, with well-characterised and predictable behaviour. It is used for wing and empennage skins, spars and ribs, fuselage panels and control surfaces — anywhere weight is the governing cost.
Style 7781 glass fabric (ECDE 75-1/0 yarn), an 8-harness satin weave that drapes readily over compound curvature, in a BP911 epoxy matrix. Glass/epoxy is the workhorse of secondary aircraft structure and tooling: far cheaper than carbon, electrically transparent, and tolerant of impact and handling damage. It is chosen where stiffness-per-pound is not the governing requirement — radomes and antenna windows, fairings and access panels, lay-up tooling, and marine and industrial laminates. The handbook characterises it from -65 °F to 160 °F, consistent with ambient and mildly elevated service. MatWorld carries 51 tensile, compressive and shear curves for this system, digitised from MIL-HDBK-17-2F Volume 2 (US Government work, public domain).
Style 7781 glass fabric (ECDE 75-1/0 yarn), an 8-harness satin weave that drapes readily over compound curvature, in a BP915 epoxy matrix. Glass/epoxy is the workhorse of secondary aircraft structure and tooling: far cheaper than carbon, electrically transparent, and tolerant of impact and handling damage. It is chosen where stiffness-per-pound is not the governing requirement — radomes and antenna windows, fairings and access panels, lay-up tooling, and marine and industrial laminates. The handbook characterises it from -65 °F to 160 °F, consistent with ambient and mildly elevated service. MatWorld carries 46 tensile, compressive and shear curves for this system, digitised from MIL-HDBK-17-2F Volume 2 (US Government work, public domain).
Style 581 Astroquartz fabric, an 8-harness satin weave, in a BPI 373 polyimide matrix. Quartz (Astroquartz) reinforcement in a polyimide matrix combines very low dielectric loss with genuine high-temperature capability. This is a radome and antenna-window material first — it stays radar-transparent where glass does not — and is used where the structure must also survive sustained elevated temperature. The handbook characterises it from -65 °F to 550 °F, consistent with sustained high-temperature service. MatWorld carries 71 tensile, compressive and shear curves for this system, digitised from MIL-HDBK-17-2F Volume 2 (US Government work, public domain).
Celion 12k (Celanese) carbon fibre (12,000-filament tow) in an E7K8 (U.S. Polymeric) epoxy matrix, supplied as tape. Carbon/epoxy is the primary structural composite of modern aerospace: the highest stiffness-to-weight of the common systems, with well-characterised and predictable behaviour. It is used for wing and empennage skins, spars and ribs, fuselage panels and control surfaces — anywhere weight is the governing cost.
Celion 3000 (Celanese) carbon fibre (3,000-filament tow) in an E7K8 (U.S. Polymeric) epoxy matrix, supplied as plain weave. Carbon/epoxy is the primary structural composite of modern aerospace: the highest stiffness-to-weight of the common systems, with well-characterised and predictable behaviour. It is used for wing and empennage skins, spars and ribs, fuselage panels and control surfaces — anywhere weight is the governing cost. The handbook characterises it from -65 °F to 180 °F, consistent with ambient and mildly elevated service. MatWorld carries 11 tensile, compressive and shear curves for this system, digitised from MIL-HDBK-17-2F Volume 2 (US Government work, public domain).
Style 7781 glass fabric (550 yarn), an 8-harness satin weave that drapes readily over compound curvature, in a CP1304 polyester matrix. Glass/polyester is the low-cost commercial laminate: easy to process at room temperature, forgiving in open moulds, and adequate where loads are modest. It is the standard for marine hulls, tanks and pipework, and industrial panels, rather than for weight-critical aerospace structure. The handbook characterises it from -65 °F to 300 °F, consistent with moderately elevated service. MatWorld carries 66 tensile, compressive and shear curves for this system, digitised from MIL-HDBK-17-2F Volume 2 (US Government work, public domain).
Style 7781 glass fabric (ECDE 75-1/0 yarn), an 8-harness satin weave that drapes readily over compound curvature, in an E293 epoxy matrix. Glass/epoxy is the workhorse of secondary aircraft structure and tooling: far cheaper than carbon, electrically transparent, and tolerant of impact and handling damage. It is chosen where stiffness-per-pound is not the governing requirement — radomes and antenna windows, fairings and access panels, lay-up tooling, and marine and industrial laminates. The handbook characterises it from -65 °F to 160 °F, consistent with ambient and mildly elevated service. MatWorld carries 53 tensile, compressive and shear curves for this system, digitised from MIL-HDBK-17-2F Volume 2 (US Government work, public domain).
Style 7781 glass fabric (ECDE 75-1/0 yarn), an 8-harness satin weave that drapes readily over compound curvature, in an E-720E epoxy matrix. Glass/epoxy is the workhorse of secondary aircraft structure and tooling: far cheaper than carbon, electrically transparent, and tolerant of impact and handling damage. It is chosen where stiffness-per-pound is not the governing requirement — radomes and antenna windows, fairings and access panels, lay-up tooling, and marine and industrial laminates. The handbook characterises it from -65 °F to 450 °F, consistent with elevated-temperature service. MatWorld carries 75 tensile, compressive and shear curves for this system, digitised from MIL-HDBK-17-2F Volume 2 (US Government work, public domain).
Style 7743 glass fabric (ECDE 75-1/0 yarn) in an E-779 epoxy matrix. Glass/epoxy is the workhorse of secondary aircraft structure and tooling: far cheaper than carbon, electrically transparent, and tolerant of impact and handling damage. It is chosen where stiffness-per-pound is not the governing requirement — radomes and antenna windows, fairings and access panels, lay-up tooling, and marine and industrial laminates. The handbook characterises it from -65 °F to 160 °F, consistent with ambient and mildly elevated service. MatWorld carries 37 tensile, compressive and shear curves for this system, digitised from MIL-HDBK-17-2F Volume 2 (US Government work, public domain).
Style 7781 glass fabric (550 yarn), an 8-harness satin weave that drapes readily over compound curvature, in an F141 polyester matrix. Glass/polyester is the low-cost commercial laminate: easy to process at room temperature, forgiving in open moulds, and adequate where loads are modest. It is the standard for marine hulls, tanks and pipework, and industrial panels, rather than for weight-critical aerospace structure. The handbook characterises it from -65 °F to 300 °F, consistent with moderately elevated service. MatWorld carries 66 tensile, compressive and shear curves for this system, digitised from MIL-HDBK-17-2F Volume 2 (US Government work, public domain).
Style 3405 glass fabric (S1014 yarn) in an F-161 epoxy matrix. Glass/epoxy is the workhorse of secondary aircraft structure and tooling: far cheaper than carbon, electrically transparent, and tolerant of impact and handling damage. It is chosen where stiffness-per-pound is not the governing requirement — radomes and antenna windows, fairings and access panels, lay-up tooling, and marine and industrial laminates. The handbook characterises it from -65 °F to 450 °F, consistent with elevated-temperature service. MatWorld carries 65 tensile, compressive and shear curves for this system, digitised from MIL-HDBK-17-2F Volume 2 (US Government work, public domain).
Style 7743 glass fabric (ECDE 75-1/0 yarn) in an F-161 epoxy matrix. Glass/epoxy is the workhorse of secondary aircraft structure and tooling: far cheaper than carbon, electrically transparent, and tolerant of impact and handling damage. It is chosen where stiffness-per-pound is not the governing requirement — radomes and antenna windows, fairings and access panels, lay-up tooling, and marine and industrial laminates. The handbook characterises it from -65 °F to 450 °F, consistent with elevated-temperature service. MatWorld carries 46 tensile, compressive and shear curves for this system, digitised from MIL-HDBK-17-2F Volume 2 (US Government work, public domain).
Style 7781 glass fabric (ECDE 75-1/0 yarn), an 8-harness satin weave that drapes readily over compound curvature, in an F-161 epoxy matrix. Glass/epoxy is the workhorse of secondary aircraft structure and tooling: far cheaper than carbon, electrically transparent, and tolerant of impact and handling damage. It is chosen where stiffness-per-pound is not the governing requirement — radomes and antenna windows, fairings and access panels, lay-up tooling, and marine and industrial laminates. The handbook characterises it from -65 °F to 450 °F, consistent with elevated-temperature service. MatWorld carries 223 tensile, compressive and shear curves for this system, digitised from MIL-HDBK-17-2F Volume 2 (US Government work, public domain).
Style 81 glass fabric (S994 yarn) in an F-161 epoxy matrix. Glass/epoxy is the workhorse of secondary aircraft structure and tooling: far cheaper than carbon, electrically transparent, and tolerant of impact and handling damage. It is chosen where stiffness-per-pound is not the governing requirement — radomes and antenna windows, fairings and access panels, lay-up tooling, and marine and industrial laminates. The handbook characterises it from -65 °F to 450 °F, consistent with elevated-temperature service. MatWorld carries 66 tensile, compressive and shear curves for this system, digitised from MIL-HDBK-17-2F Volume 2 (US Government work, public domain).
Thornel T-300 (Amoco) carbon fibre (3,000-filament tow) in an F652 (Hexcel) bismaleimide matrix, supplied as 8-harness satin weave. Carbon/BMI extends carbon/epoxy to sustained service around 350-450 °F, well beyond epoxy's limit, while processing in broadly similar tooling. It is used for engine nacelles and nozzles, structure near exhaust, and supersonic-aircraft skins subject to aerodynamic heating.
Celion 3000 (Celanese) carbon fibre (3,000-filament tow) in an F670 (PMR-15) (Hexcel) polyimide matrix, supplied as 8-harness satin weave. Carbon/polyimide serves the highest sustained temperatures of the common structural composites, above what BMI will tolerate. It is reserved for engine and exhaust-adjacent structure where the thermal requirement justifies its difficult processing.
Thornel T-300 (Toray) carbon fibre (3,000-filament tow) in an F650 (Hexcel) bismaleimide matrix, supplied as 8-harness satin weave. Carbon/BMI extends carbon/epoxy to sustained service around 350-450 °F, well beyond epoxy's limit, while processing in broadly similar tooling. It is used for engine nacelles and nozzles, structure near exhaust, and supersonic-aircraft skins subject to aerodynamic heating. The handbook characterises it from 75 °F to 450 °F, consistent with elevated-temperature service. MatWorld carries 1 shear curve for this system, digitised from MIL-HDBK-17-2F Volume 2 (US Government work, public domain).
AS4 6k (Hercules) carbon fibre in a PR 500 RTM (3M) epoxy matrix. Carbon/epoxy is the primary structural composite of modern aerospace: the highest stiffness-to-weight of the common systems, with well-characterised and predictable behaviour. It is used for wing and empennage skins, spars and ribs, fuselage panels and control surfaces — anywhere weight is the governing cost. The handbook characterises it from -75 °F to 350 °F, consistent with elevated-temperature service. MatWorld carries 21 tensile, compressive and shear curves for this system, digitised from MIL-HDBK-17-2F Volume 2 (US Government work, public domain).
AS4 12k (Hexcel) carbon fibre (12,000-filament tow) in a 997 (Fiberite) epoxy matrix, supplied as tape. Carbon/epoxy is the primary structural composite of modern aerospace: the highest stiffness-to-weight of the common systems, with well-characterised and predictable behaviour. It is used for wing and empennage skins, spars and ribs, fuselage panels and control surfaces — anywhere weight is the governing cost. The handbook characterises it from -65 °F to 180 °F, consistent with ambient and mildly elevated service. MatWorld carries 3 tensile, compressive, shear and bearing curves for this system, digitised from MIL-HDBK-17-2F Volume 2 (US Government work, public domain).
M55J 6k (Toray) carbon fibre (6,000-filament tow) in a 954-3 (Hexcel) cyanate ester matrix, supplied as tape. Carbon/cyanate-ester is chosen for dimensional stability and very low moisture absorption: it outgasses little and resists microcracking through thermal cycling. That makes it a spacecraft-structure and precision-optics material — benches, reflectors, and instrument support — more than an airframe one.
HITEX 33 (Hitco) carbon fibre (6,000-filament tow) in an E7K8 (U.S. Polymeric) epoxy matrix, supplied as plain weave. Carbon/epoxy is the primary structural composite of modern aerospace: the highest stiffness-to-weight of the common systems, with well-characterised and predictable behaviour. It is used for wing and empennage skins, spars and ribs, fuselage panels and control surfaces — anywhere weight is the governing cost. The handbook characterises it from -65 °F to 180 °F, consistent with ambient and mildly elevated service. MatWorld carries 12 tensile, compressive and shear curves for this system, digitised from MIL-HDBK-17-2F Volume 2 (US Government work, public domain).
HITEX 33 (Hitco) carbon fibre (6,000-filament tow) in an E7K8 (U.S. Polymeric) epoxy matrix, supplied as tape. Carbon/epoxy is the primary structural composite of modern aerospace: the highest stiffness-to-weight of the common systems, with well-characterised and predictable behaviour. It is used for wing and empennage skins, spars and ribs, fuselage panels and control surfaces — anywhere weight is the governing cost.
Thornel T-300 (Toray) carbon fibre (3,000-filament tow) in a 934 (Fiberite) epoxy matrix, supplied as plain weave. Carbon/epoxy is the primary structural composite of modern aerospace: the highest stiffness-to-weight of the common systems, with well-characterised and predictable behaviour. It is used for wing and empennage skins, spars and ribs, fuselage panels and control surfaces — anywhere weight is the governing cost. The handbook characterises it from -65 °F to 250 °F, consistent with moderately elevated service. MatWorld carries 18 tensile, compressive and shear curves for this system, digitised from MIL-HDBK-17-2F Volume 2 (US Government work, public domain).
AS4 12k (Hercules) carbon fibre (12,000-filament tow) in a 938 (Fiberite) epoxy matrix, supplied as tape. Carbon/epoxy is the primary structural composite of modern aerospace: the highest stiffness-to-weight of the common systems, with well-characterised and predictable behaviour. It is used for wing and empennage skins, spars and ribs, fuselage panels and control surfaces — anywhere weight is the governing cost. The handbook characterises it from -65 °F to 200 °F, consistent with moderately elevated service. MatWorld carries 2 tensile, compressive and shear curves for this system, digitised from MIL-HDBK-17-2F Volume 2 (US Government work, public domain).
Celion 12k (Celanese) carbon fibre (12,000-filament tow) in a 938 (Fiberite) epoxy matrix, supplied as tape. Carbon/epoxy is the primary structural composite of modern aerospace: the highest stiffness-to-weight of the common systems, with well-characterised and predictable behaviour. It is used for wing and empennage skins, spars and ribs, fuselage panels and control surfaces — anywhere weight is the governing cost. The handbook characterises it from -67 °F to 250 °F, consistent with moderately elevated service. MatWorld carries 14 tensile, compressive and shear curves for this system, digitised from MIL-HDBK-17-2F Volume 2 (US Government work, public domain).
Thornel T-500 (Union Carbide) carbon fibre in a 976 (Fiberite) epoxy matrix, supplied as tape. Carbon/epoxy is the primary structural composite of modern aerospace: the highest stiffness-to-weight of the common systems, with well-characterised and predictable behaviour. It is used for wing and empennage skins, spars and ribs, fuselage panels and control surfaces — anywhere weight is the governing cost. The handbook characterises it from -65 °F to 250 °F, consistent with moderately elevated service. MatWorld carries 8 tensile curves for this system, digitised from MIL-HDBK-17-2F Volume 2 (US Government work, public domain).
IM-6 (Hercules) carbon fibre (12,000-filament tow) in an APC-2 (Fiberite) PEEK matrix, supplied as tape. Carbon/PEEK is a thermoplastic composite: it can be melted and re-formed, which permits welding, rapid stamping and reprocessing that a thermoset cannot. It absorbs almost no moisture, resists solvents, and has markedly better damage tolerance and interlaminar toughness than epoxy systems — at higher processing temperature and cost. Typical uses are clips, brackets and leading edges where impact and fluid exposure govern. The handbook characterises it from -67 °F to 250 °F, consistent with moderately elevated service. MatWorld carries 16 tensile, compressive and shear curves for this system, digitised from MIL-HDBK-17-2F Volume 2 (US Government work, public domain).
Style 7781 glass fabric (ECDE 75-1/0 yarn), an 8-harness satin weave that drapes readily over compound curvature, in an N588 epoxy matrix. Glass/epoxy is the workhorse of secondary aircraft structure and tooling: far cheaper than carbon, electrically transparent, and tolerant of impact and handling damage. It is chosen where stiffness-per-pound is not the governing requirement — radomes and antenna windows, fairings and access panels, lay-up tooling, and marine and industrial laminates. The handbook characterises it from -65 °F to 400 °F, consistent with elevated-temperature service. MatWorld carries 65 tensile, compressive and shear curves for this system, digitised from MIL-HDBK-17-2F Volume 2 (US Government work, public domain).
S2-449 (Owens Corning) s-glass fibre in a PR 381 (3M) epoxy matrix, supplied as tape. S-glass carries roughly a third more strength and stiffness than E-glass at similar density, at higher cost. It is specified where glass is wanted for its impact tolerance or transparency but E-glass is not strong enough — ballistic and containment structure, rotor components, and high-load fairings. The handbook characterises it from -65 °F to 180 °F, consistent with ambient and mildly elevated service. MatWorld carries 15 tensile, compressive and shear curves for this system, digitised from MIL-HDBK-17-2F Volume 2 (US Government work, public domain).
Engineered laminate of S2-449/PR 381 Tape, stacked [+-45/0/+-45]:s. Properties here are laminate-level effective values in the laminate's own axes — not the lamina constants, which live on the parent prepreg (S2-449/PR 381 Tape). From MIL-HDBK-17-2F Volume 2 (US Government work, public domain).
Engineered laminate of S2-449/PR 381 Tape, stacked [+-45/90/+-45]:s. Properties here are laminate-level effective values in the laminate's own axes — not the lamina constants, which live on the parent prepreg (S2-449/PR 381 Tape). From MIL-HDBK-17-2F Volume 2 (US Government work, public domain).
Style 1581 glass fabric (ECG 150-1/2 yarn), an 8-harness satin weave, in an S-860 silicone matrix. Silicone-matrix glass laminates trade mechanical performance for thermal and electrical endurance. They retain useful properties far above the range of epoxy or polyester and are used for high-temperature electrical insulation, ducting and thermal barriers rather than as load-bearing structure. The handbook characterises it from -65 °F to 650 °F, consistent with sustained high-temperature service. MatWorld carries 27 tensile curves for this system, digitised from MIL-HDBK-17-2F Volume 2 (US Government work, public domain).
Engineered laminate of Scotchply SP 381 Uni S29 111BW 33RC, stacked [+-45/0/+-45]:2s. Properties here are laminate-level effective values in the laminate's own axes — not the lamina constants, which live on the parent prepreg (Scotchply SP 381 Uni S29 111BW 33RC — S2-449/PR 381). From MIL-HDBK-17-2F Volume 2 (US Government work, public domain).
Engineered laminate of Scotchply SP 381 Uni S29 111BW 33RC, stacked [+-45/90/+-45]:2s. Properties here are laminate-level effective values in the laminate's own axes — not the lamina constants, which live on the parent prepreg (Scotchply SP 381 Uni S29 111BW 33RC — S2-449/PR 381). From MIL-HDBK-17-2F Volume 2 (US Government work, public domain).
S2-449 (Owens Corning) s-glass fibre in a PR 381 (3M) epoxy matrix, supplied as tape. S-glass carries roughly a third more strength and stiffness than E-glass at similar density, at higher cost. It is specified where glass is wanted for its impact tolerance or transparency but E-glass is not strong enough — ballistic and containment structure, rotor components, and high-load fairings. The handbook characterises it from -65 °F to 180 °F, consistent with ambient and mildly elevated service. MatWorld carries 15 tensile, compressive and shear curves for this system, digitised from MIL-HDBK-17-2F Volume 2 (US Government work, public domain).
Engineered laminate of SP272, stacked [(0/90):2]S. Properties here are laminate-level effective values in the laminate's own axes — not the lamina constants, which live on the parent prepreg (SP272 — boron fibre / epoxy). From MIL-HDBK-17-2F Volume 2 (US Government work, public domain).
Boron fibre in an epoxy matrix. Boron/epoxy has exceptional specific stiffness and compressive strength — boron filament is markedly stiffer than carbon and does not buckle under compression the way graphite does. Historically used for empennage skins and stiffeners on military aircraft, its enduring role is bonded composite repair: boron patches restore stiffness to cracked metallic structure without the galvanic problems carbon introduces against aluminium. The handbook characterises it from -67 °F to 375 °F, consistent with elevated-temperature service. MatWorld carries 52 tensile, compressive and shear curves for this system, digitised from MIL-HDBK-17-2F Volume 2 (US Government work, public domain).
Thornel T-300 (Union Carbide) carbon fibre (15,000-filament tow) in a 976 (Fiberite) epoxy matrix, supplied as tape. Carbon/epoxy is the primary structural composite of modern aerospace: the highest stiffness-to-weight of the common systems, with well-characterised and predictable behaviour. It is used for wing and empennage skins, spars and ribs, fuselage panels and control surfaces — anywhere weight is the governing cost. The handbook characterises it from -67 °F to 350 °F, consistent with elevated-temperature service. MatWorld carries 20 tensile, compressive and shear curves for this system, digitised from MIL-HDBK-17-2F Volume 2 (US Government work, public domain).
T300 (Toray) carbon fibre (3,000-filament tow) in an EA 9396 (Dexter-Hysol) epoxy matrix. Carbon/epoxy is the primary structural composite of modern aerospace: the highest stiffness-to-weight of the common systems, with well-characterised and predictable behaviour. It is used for wing and empennage skins, spars and ribs, fuselage panels and control surfaces — anywhere weight is the governing cost. The handbook characterises it from -65 °F to 200 °F, consistent with moderately elevated service. Dry carbon fabric impregnated with epoxy resin in a wet lay-up impregnation process. MatWorld carries 26 tensile, compressive and shear curves for this system, digitised from MIL-HDBK-17-2F Volume 2 (US Government work, public domain).
Thornel T-300 (Toray) carbon fibre (3,000-filament tow) in an F650 (Hexcel) bismaleimide matrix, supplied as tape. Carbon/BMI extends carbon/epoxy to sustained service around 350-450 °F, well beyond epoxy's limit, while processing in broadly similar tooling. It is used for engine nacelles and nozzles, structure near exhaust, and supersonic-aircraft skins subject to aerodynamic heating. The handbook characterises it from -67 °F to 400 °F, consistent with elevated-temperature service. MatWorld carries 2 tensile and shear curves for this system, digitised from MIL-HDBK-17-2F Volume 2 (US Government work, public domain).
T650-35 (ICI Fiberite) carbon fibre (12,000-filament tow) in a 976 (ICI Fiberite) epoxy matrix. Carbon/epoxy is the primary structural composite of modern aerospace: the highest stiffness-to-weight of the common systems, with well-characterised and predictable behaviour. It is used for wing and empennage skins, spars and ribs, fuselage panels and control surfaces — anywhere weight is the governing cost.