{"id":6548,"date":"2026-04-25T22:37:04","date_gmt":"2026-04-25T22:37:04","guid":{"rendered":"https:\/\/rapidcision.com\/?p=6548"},"modified":"2026-05-07T23:34:53","modified_gmt":"2026-05-07T23:34:53","slug":"blog-aerospace-aluminum-alloys-comparison","status":"publish","type":"post","link":"https:\/\/rapidcision.com\/fr\/blog-aerospace-aluminum-alloys-comparison\/","title":{"rendered":"Aerospace Aluminum Alloys Compared: 6061, 7075, 2024, and 2219"},"content":{"rendered":"

The four most-used aerospace aluminum alloys are 6061-T6 (general structural, weldable), 7075-T6\/T7351 (high-strength structural), 2024-T351 (fatigue-critical fuselage and wing skins), and 2219-T87 (high-temperature welded structures, fuel tanks, and launch vehicles). 7075 has the highest strength (yield 503 MPa); 6061 the best machinability and weldability; 2024 the best fatigue resistance; 2219 the best high-temperature performance. Choose by application: structural and general \u2192 6061; high-strength \u2192 7075; fatigue-critical airframe \u2192 2024; welded high-temp \u2192 2219.<\/p>\n


\nAerospace Aluminum Alloys at a Glance<\/b><\/h2>\n\n\n\n\n\n\n\n\n\n\n\n\n\n
Property<\/b><\/th>\n6061-T6<\/b><\/th>\n7075-T7351<\/b><\/th>\n2024-T351<\/b><\/th>\n2219-T87<\/b><\/th>\n<\/tr>\n<\/thead>\n
Yield strength<\/span><\/td>\n276 MPa<\/span><\/td>\n414 MPa<\/span><\/td>\n324 MPa<\/span><\/td>\n393 MPa<\/span><\/td>\n<\/tr>\n
Tensile strength<\/span><\/td>\n310 MPa<\/span><\/td>\n503 MPa<\/span><\/td>\n469 MPa<\/span><\/td>\n476 MPa<\/span><\/td>\n<\/tr>\n
Density<\/span><\/td>\n2.70 g\/cc<\/span><\/td>\n2.81 g\/cc<\/span><\/td>\n2.78 g\/cc<\/span><\/td>\n2.84 g\/cc<\/span><\/td>\n<\/tr>\n
Elongation<\/span><\/td>\n12%<\/span><\/td>\n11%<\/span><\/td>\n19%<\/span><\/td>\n10%<\/span><\/td>\n<\/tr>\n
Machinability<\/span><\/td>\nExcellent<\/span><\/td>\nGood<\/span><\/td>\nFair<\/span><\/td>\nFair<\/span><\/td>\n<\/tr>\n
Weldability<\/span><\/td>\nExcellent (TIG, MIG)<\/span><\/td>\nPoor (cracks)<\/span><\/td>\nPoor (cracks)<\/span><\/td>\nExcellent (TIG)<\/span><\/td>\n<\/tr>\n
Stress corrosion<\/span><\/td>\nExcellent<\/span><\/td>\nGood (T7351)<\/span><\/td>\nFair<\/span><\/td>\nExcellent<\/span><\/td>\n<\/tr>\n
AMS spec example<\/span><\/td>\nAMS-QQ-A-200\/8<\/span><\/td>\nAMS-QQ-A-250\/12<\/span><\/td>\nAMS-QQ-A-250\/4<\/span><\/td>\nAMS 4031<\/span><\/td>\n<\/tr>\n
Typical use<\/span><\/td>\nStructural, brackets<\/span><\/td>\nWing spars, frames<\/span><\/td>\nFuselage skins<\/span><\/td>\nFuel tanks, launchers<\/span><\/td>\n<\/tr>\n<\/tbody>\n<\/table>\n


\nWhy Aerospace Picks These Four Alloys<\/b><\/h2>\n

The aerospace aluminum landscape evolved over decades of fatigue analysis, fracture mechanics testing, and field service experience. Each of the four major alloys solves a different problem the engineering community ran into. Understanding why an alloy was developed clarifies when to use it.<\/span><\/p>\n

    \n
  • 6061 (Al-Mg-Si family): developed for general-purpose structural use where machinability, weldability, and corrosion resistance matter. Not the strongest, but the most workable. The default for non-flight-critical structural parts.<\/span><\/li>\n
  • 7075 (Al-Zn-Mg-Cu family): developed during WWII for highest available strength-to-weight ratio. Replaces 2024 where strength matters more than fatigue resistance. Standard for compression-loaded structural members like wing spars and frame longerons.<\/span><\/li>\n
  • 2024 (Al-Cu-Mg family): the original aerospace structural alloy, developed in the 1930s. Best fatigue resistance among aluminums. Standard for tension-loaded fuselage skins where fatigue cycling drives design.<\/span><\/li>\n
  • 2219 (Al-Cu family): developed for high-temperature welded structures. Retains strength up to 200 \u00b0C and welds without cracking. Saturn V, Space Shuttle external tank, and modern launch vehicles all use 2219 extensively.<\/span><\/li>\n<\/ul>\n


    \n6061-T6 \u2014 The Workhorse<\/b><\/h2>\n

    6061-T6 is the aluminum alloy that gets specified when nothing else specifically calls for one of the other three. AMS-QQ-A-200\/8 (extruded) and AMS-QQ-A-250\/11 (plate). Yield strength 276 MPa, tensile 310 MPa. Excellent machinability \u2014 chips well at 250\u2013400 m\/min cutting speed in CNC, doesn’t gum up endmills. Excellent weldability with both TIG and MIG processes using 4043 or 5356 filler.<\/span><\/p>\n

    Common 6061 applications:<\/span><\/p>\n

      \n
    • Aircraft mounting brackets and fittings<\/span><\/li>\n
    • Cabin interior structural components<\/span><\/li>\n
    • Hydraulic manifold blocks<\/span><\/li>\n
    • Ground support equipment (GSE) frames<\/span><\/li>\n
    • Avionics enclosures and rack components<\/span><\/li>\n
    • UAV and small aircraft airframe parts<\/span><\/li>\n<\/ul>\n

      6061’s weakness is strength. For compression-loaded parts above moderate load levels, 7075’s 50% strength advantage justifies its higher cost and harder machining.<\/span><\/p>\n


      \n7075-T6 and T7351 \u2014 Maximum Strength<\/b><\/h2>\n

      7075 is the high-strength aerospace structural alloy. Two heat treatments dominate: T6 (peak strength, lower stress-corrosion resistance) and T7351 (slightly lower strength, much better stress-corrosion resistance). T7351 is preferred for parts in corrosive service or with sustained tensile stress.<\/span><\/p>\n

      AMS specifications: AMS-QQ-A-250\/12 for plate, AMS-QQ-A-200\/15 for extruded shapes, AMS 4045 for sheet, AMS 4202 for forgings. 7075-T6 yield 503 MPa, tensile 572 MPa. T7351 yield 414 MPa, tensile 503 MPa. Density 2.81 g\/cc \u2014 slightly higher than 6061 but more than offset by the strength advantage.<\/span><\/p>\n

      Common 7075 applications:<\/span><\/p>\n

        \n
      • Wing spars and ribs<\/span><\/li>\n
      • Fuselage frame longerons and stringers<\/span><\/li>\n
      • Landing gear structural components (non-shaft, where 4340 steel typically wins)<\/span><\/li>\n
      • Missile and rocket structural sections<\/span><\/li>\n
      • Robotics and motion-control structural parts<\/span><\/li>\n
      • Bicycle frames and high-performance sporting goods<\/span><\/li>\n<\/ul>\n

        7075’s weaknesses are weldability (cracks badly without specialized procedures) and corrosion resistance in T6 temper. Don’t weld 7075 unless absolutely necessary; mechanical fasteners (rivets, bolts) are the standard joining method. Anodize Type II clear or Type III hardcoat for outdoor\/corrosive service.<\/span><\/p>\n


        \n2024-T351 \u2014 Fatigue-Critical Skins<\/b><\/h2>\n

        2024 is the original aerospace structural alloy. AMS-QQ-A-250\/4 for plate, AMS-QQ-A-200\/3 for extruded. Yield 324 MPa, tensile 469 MPa. Density 2.78 g\/cc. The standout property is fatigue performance \u2014 2024 retains strength under cyclic loading better than 7075, making it the standard for tension-loaded fuselage skins that see millions of cycles over an aircraft’s service life.<\/span><\/p>\n

        Common 2024 applications:<\/span><\/p>\n

          \n
        • Fuselage skin panels (typically clad 2024 \u2014 Alclad \u2014 for corrosion protection)<\/span><\/li>\n
        • Wing skin panels in tension regions<\/span><\/li>\n
        • Cargo door structures<\/span><\/li>\n
        • High-cycle-fatigue mechanical components<\/span><\/li>\n
        • Aircraft hardware where fatigue dominates<\/span><\/li>\n<\/ul>\n

          2024 doesn’t weld well (similar cracking issues to 7075) and has fair stress-corrosion resistance. The standard joining method is rivets, with Alclad cladding providing corrosion protection on the cladded faces. Modern aircraft increasingly use 2024-T351 with bonded composite reinforcement for fatigue-critical zones.<\/span><\/p>\n


          \n2219-T87 \u2014 Welded High-Temperature Structures<\/b><\/h2>\n

          2219 is the welded high-temperature aerospace alloy. AMS 4031 for sheet, AMS 4144 for plate. Yield 393 MPa, tensile 476 MPa. Density 2.84 g\/cc \u2014 the heaviest of the four major aerospace alloys. The standout properties are weldability without cracking (using filler 2319) and strength retention up to 200 \u00b0C operating temperature. 2219 is the alloy of choice when you need to weld a strong aluminum structure that operates hot.<\/span><\/p>\n

          Common 2219 applications:<\/span><\/p>\n

            \n
          • Launch vehicle propellant tanks (Saturn V, Space Shuttle ET, Falcon 9, SLS Core Stage)<\/span><\/li>\n
          • Cryogenic fuel tanks (LH2, LOX) where weldability matters<\/span><\/li>\n
          • High-speed aircraft skin in friction-heated zones<\/span><\/li>\n
          • Aerospace pressure vessels operating above 100 \u00b0C<\/span><\/li>\n
          • Welded engine support structures<\/span><\/li>\n<\/ul>\n

            2219’s weaknesses are mediocre fatigue performance versus 2024 and less strength than 7075. It’s specified specifically when welding is required and operating temperatures exceed what 6061 can handle.<\/span><\/p>\n


            \nMachinability Differences<\/b><\/h2>\n

            All four alloys cut on standard CNC equipment, but with significant differences in chip behavior and surface finish:<\/span><\/p>\n

              \n
            • 6061: cuts beautifully. Long stringy chips on continuous cuts, breaks on interrupted cuts. Surface finish Ra 0.8 \u00b5m achievable directly with sharp tools. Wears tools slowly. Excellent finish on anodize-prep cuts.<\/span><\/li>\n
            • 7075: cuts well but harder than 6061. Heavier cutting forces, faster tool wear (use carbide, not HSS). Tendency toward built-up edge if speeds and feeds aren’t optimized. Surface finish Ra 0.8\u20131.6 \u00b5m achievable. Strong work-hardening response means light finishing cuts are essential to prevent surface tears.<\/span><\/li>\n
            • 2024: cuts similarly to 7075 but with slightly higher tool wear. Built-up edge is a more persistent issue; aggressive coolant flow helps. Surface finish requires care to avoid micro-tearing of the surface.<\/span><\/li>\n
            • 2219: machines like 2024 but with even higher work-hardening sensitivity. Use sharp tools, climb-mill where possible, and avoid dwell. Acceptable surface finish requires patience and proper coolant strategy.<\/span><\/li>\n<\/ul>\n


              \nCost and Availability<\/b><\/h2>\n

              Indicative material cost ranges (mid-2025, US distributor pricing for standard plate stock):<\/span><\/p>\n

                \n
              • 6061-T6 plate: $9\u2013$14 per kg.<\/span><\/li>\n
              • 7075-T7351 plate: $14\u2013$22 per kg.<\/span><\/li>\n
              • 2024-T351 plate (Alclad): $16\u2013$24 per kg.<\/span><\/li>\n
              • 2219-T87 plate: $22\u2013$36 per kg.<\/span><\/li>\n<\/ul>\n

                AMS-spec material with full mill certification adds 20\u201335% to standard distribution pricing. Lead times for AMS material at common sizes (50 \u00d7 200 \u00d7 1,000 mm plate, common round bar diameters) typically run 2\u20138 weeks from major aerospace material distributors. Custom sizes or non-stock alloys can stretch to 16+ weeks.<\/span><\/p>\n


                \nConclusion<\/b><\/h2>\n

                Aerospace aluminum alloy selection isn’t a free choice \u2014 it’s driven by the dominant loading mode, operating environment, joining method, and historical precedent in the application class. 6061 wins where workability matters; 7075 wins where strength dominates; 2024 wins where fatigue dominates; 2219 wins where welded high-temperature service is required. Getting the alloy choice wrong creates problems that show up months or years downstream \u2014 fatigue cracks, stress-corrosion failures, weld defects. Getting it right is mostly a matter of matching the alloy to the historical use case the application falls into.<\/span><\/p>\n

                Need help selecting the right aerospace aluminum alloy for your part? <\/b>Upload your STEP file at rapidcision.com \u2014 our patented quoting engine identifies optimal alloy options based on geometry, loading hints, and AS9100 documentation requirements.<\/span><\/p>\n


                \nFrequently Asked Questions<\/b><\/h2>\n

                Why is 7075 so much stronger than 6061?<\/b><\/h3>\n

                Different alloying systems. 6061 uses magnesium-silicon precipitates that strengthen the aluminum matrix moderately. 7075 uses zinc-magnesium precipitates that strengthen far more aggressively. The trade-off is corrosion resistance and weldability \u2014 7075’s stronger precipitates make it more susceptible to stress corrosion and more prone to weld cracking.<\/span><\/p>\n

                What’s the difference between 7075-T6 and 7075-T7351?<\/b><\/h3>\n

                Heat treatment temper. T6 is peak-aged for maximum strength; T7351 is over-aged with stretched stress relief, sacrificing 17% strength for substantially better stress-corrosion resistance. For aerospace structural parts in service, T7351 is almost always specified because field stress-corrosion failures cost more than the strength margin saved.<\/span><\/p>\n

                Can I substitute 7075 for 2024 in fatigue-critical applications?<\/b><\/h3>\n

                Generally no. 2024’s fatigue resistance under high-cycle loading is materially better than 7075. Aircraft fuselage skins specifically use 2024 (typically Alclad 2024-T3 sheet) because fatigue testing showed substantial life advantages over 7075 at equivalent stress levels. Modern designs using composite skins are an exception, but for traditional aluminum airframe construction, the 2024-vs-7075 choice tracks the loading mode (tension-fatigue vs compression).<\/span><\/p>\n

                Is 2219 still relevant in modern aerospace?<\/b><\/h3>\n

                Yes. 2219 remains the standard launch vehicle propellant tank alloy. SpaceX Falcon 9 and Falcon Heavy use 2219; SLS uses 2219 plus Al-Li 2195. The combination of weldability, cryogenic toughness, and high-temperature strength is hard to beat with newer alloys at the cost point. For non-launch aerospace, 2219 is rarer but still appears in welded engine cowlings and high-speed aircraft skins.<\/span><\/p>\n

                What’s the right alloy for a generic aerospace bracket?<\/b><\/h3>\n

                6061-T6 unless there’s a specific reason to upgrade. For load-critical brackets with margin issues, 7075-T7351. The decision flows from stress analysis: if the calculated margin on 6061 is comfortable (>1.5x), use 6061. If margin is tight, evaluate 7075 versus geometry changes that recover margin. Material upgrade is often the cheaper option.<\/span><\/p>\n

                Does Rapid Precision stock all four alloys?<\/b><\/h3>\n

                Yes. Rapid Precision maintains AMS-spec stock of 6061-T6 (plate and bar), 7075-T7351 (plate, bar, and forgings), 2024-T351 (plate, including Alclad), and 2219-T87 (plate). Material certifications include heat-lot traceability and full chemical and mechanical property reports. Custom sizes and other alloys (2014, 7050, Al-Li 2195) on request with extended lead time.<\/span><\/p>\n

                \u00a0<\/span><\/p>","protected":false},"excerpt":{"rendered":"

                The four most-used aerospace aluminum alloys are 6061-T6 (general structural, weldable), 7075-T6\/T7351 (high-strength structural), 2024-T351 (fatigue-critical fuselage and wing skins), and 2219-T87 (high-temperature welded structures, fuel tanks, and launch vehicles). 7075 has the highest strength (yield 503 MPa); 6061 the best machinability and weldability; 2024 the best fatigue resistance; 2219 the best high-temperature performance. Choose […]<\/p>\n","protected":false},"author":2,"featured_media":6549,"comment_status":"open","ping_status":"open","sticky":false,"template":"","format":"standard","meta":{"footnotes":""},"categories":[11],"tags":[],"class_list":["post-6548","post","type-post","status-publish","format-standard","has-post-thumbnail","hentry","category-cnc-machining"],"_links":{"self":[{"href":"https:\/\/rapidcision.com\/fr\/wp-json\/wp\/v2\/posts\/6548","targetHints":{"allow":["GET"]}}],"collection":[{"href":"https:\/\/rapidcision.com\/fr\/wp-json\/wp\/v2\/posts"}],"about":[{"href":"https:\/\/rapidcision.com\/fr\/wp-json\/wp\/v2\/types\/post"}],"author":[{"embeddable":true,"href":"https:\/\/rapidcision.com\/fr\/wp-json\/wp\/v2\/users\/2"}],"replies":[{"embeddable":true,"href":"https:\/\/rapidcision.com\/fr\/wp-json\/wp\/v2\/comments?post=6548"}],"version-history":[{"count":0,"href":"https:\/\/rapidcision.com\/fr\/wp-json\/wp\/v2\/posts\/6548\/revisions"}],"wp:featuredmedia":[{"embeddable":true,"href":"https:\/\/rapidcision.com\/fr\/wp-json\/wp\/v2\/media\/6549"}],"wp:attachment":[{"href":"https:\/\/rapidcision.com\/fr\/wp-json\/wp\/v2\/media?parent=6548"}],"wp:term":[{"taxonomy":"category","embeddable":true,"href":"https:\/\/rapidcision.com\/fr\/wp-json\/wp\/v2\/categories?post=6548"},{"taxonomy":"post_tag","embeddable":true,"href":"https:\/\/rapidcision.com\/fr\/wp-json\/wp\/v2\/tags?post=6548"}],"curies":[{"name":"wp","href":"https:\/\/api.w.org\/{rel}","templated":true}]}}