GCAP (Global Combat Air Program).

Technical Data

• Design

  The GCAP is being developed as a large, crewed, twin-engine stealth combat aircraft built around a broad blended centerbody and highly swept delta-type wing. Assessments of the 2024-2026 configuration place it at 19 to 21 m in length, with an estimated 16 to 17 m wingspan and a 110 to 120 m² wing area. One assessment of the Farnborough configuration gives roughly 20 m length, 16.5 m span and 111 m² wing area. These remain estimates rather than frozen production specifications, but they indicate an aircraft substantially larger in lifting area and internal volume than the Typhoon, F-35A or F-22.

  The large wing is particularly significant. A wing area near 110-120 m² would be roughly 2.6 to 2.8 times the F-35A's 42.7 m², 1.4-1.5 times the F-22's 78 m², and about twice the F-15C's 56.5 m². The broad delta and blended centerbody provide both lifting area and substantial internal volume, allowing fuel and weapons to remain inside the low-observable airframe rather than relying on external tanks and stores. This wing design reflects the GCAP's emphasis on long unrefuelled range, large internal payload, and sustained operations over Pacific-scale distances, rather than simply maximizing close-range maneuverability.

  The aircraft uses two engines buried within the rear centerbody, with diverterless supersonic inlet-type intakes intended to prevent a direct radar line-of-sight to the compressor faces. Work associated with the British demonstrator has involved intake ducts roughly 10 m long, illustrating the internal volume required by this low-observable arrangement. The GCAP faces the same fundamental constraint pioneered by stealth aircraft such as the F-117 Nighthawk, but on a much greater scale: its centerbody must simultaneously accommodate the engines, intake and exhaust structures, internal fuel, weapons bays, landing gear, sensors, computing hardware, electrical generation equipment and thermal management systems. This requirement helps explain why the GCAP has evolved into a considerably broader aircraft than the Eurofighter Typhoon rather than retaining the dimensions of a conventional European tactical fighter.

  Low observability also shapes the external geometry. The 2024-2026 configuration combines extensive planform alignment, blended surfaces, internal weapons carriage and unusually small canted vertical surfaces, reducing prominent radar-reflective discontinuities. However, this reduced tail area increases dependence on digital flight-control laws and the extensive trailing-edge control surfaces for pitch, roll and directional control. The final configuration is not frozen, however, and it remains uncertain whether the production aircraft will retain these small vertical surfaces, reduce them further or adopt another solution. No radar-cross-section figure has been disclosed, so numerical RCS estimates or claims that the GCAP will have a lower signature than the F-22 or the F-35 cannot currently be treated as specifications.

  Subsequently, internal volume is also being sized for unusually demanding fuel and weapons requirements. The British capability outline in 2025 indicated a target weapons load roughly twice that of an F-35A and sufficient fuel capacity for a potential transatlantic flight without aerial refuelling, compared with three or four refuellings cited for Typhoon under the same broad comparison. This does not establish a precise combat radius or ferry range because payload, flight profile, reserves, and routing were not specified. It nevertheless indicates that fuel fraction and internal payload are primary airframe-sizing requirements, particularly because carrying large external fuel tanks or weapons would compromise the aircraft's low-observable configuration.

  The GCAP is designed from the outset for a service life extending beyond 2070, making internal growth capacity part of the airframe architecture. Space, electrical generation capacity and thermal management margins are consequently intended to accommodate future processors, sensors, electronic warfare equipment and other high-power systems without requiring fundamental airframe redesign. An open and modular architecture should similarly allow computing hardware and software-defined functions to be replaced progressively during the aircraft's operational life. The large airframe therefore provides not only fuel and weapons volume but also physical, electrical and cooling reserves for equipment that may not exist when the fighter first enters service.

  No authoritative production dimensions or weights have yet been released. Estimates commonly place the current configuration at a maximum takeoff weight (MTOW) between 35 and 50 tonnes, which would put it above the Typhoon and F-35A, but this remains an estimated design envelope rather than a programme specification. Empty weight, maximum takeoff weight, internal fuel mass, definitive wing area, wing loading and final dimensions remain undisclosed. Figures such as a 39,000 kg MTOW, 28,000 kg normal takeoff weight or 12,000 kg internal fuel capacity are therefore too precise to present as established GCAP characteristics at this stage.

• Armament

  The GCAP is being designed around internal weapon bays for missions requiring low observability, with the broad centerbody providing substantially greater potential weapons volume than a conventional Typhoon-sized fuselage. Keeping missiles and other effectors inside the aircraft avoids the additional radar reflections produced by external pylons and stores, while also allowing the airframe to retain its clean aerodynamic configuration. The number and dimensions of the weapons bays, number of internal stations, maximum individual weapon dimensions and maximum internal payload have not been disclosed. External carriage is expected to remain technically possible when low observability is not required, but no external hardpoint arrangement has been confirmed.

  One of the few quantitative indications is a programme objective for a weapons payload roughly twice that of the F-35A. This comparison cannot be converted directly into a specific mass because it has not been established whether it refers to maximum structural payload, weapons payload, internal carriage or a particular combat configuration. It nevertheless indicates that weapons capacity is a major airframe-sizing requirement rather than a secondary consideration. The large centerbody and estimated aircraft length also provide greater potential for carrying long weapons internally, an important consideration as future long-range air-to-air, anti-ship and stand-off missiles may require larger propulsion sections, seekers and datalink equipment.

  No confirmed internal missile capacity has been released. Figures of eight, ten or twelve internally carried air-to-air missiles therefore remain speculative, as does any direct comparison with the F-35A's internal missile magazine. The GCAP is nevertheless being sized for a larger weapons load and for missions in which the aircraft may have to conduct multiple engagements at considerable distance from its operating base. This depth is particularly relevant to the Japanese requirement for operations across the Pacific and against potentially numerically superior forces, where returning to base simply to replenish weapons imposes substantial time and distance penalties.

  Weapons integration is being incorporated into the GCAP development through Sovereign Effects Partners, bringing together MBDA UK, MBDA Italia, Mitsubishi Electric and Mitsubishi Heavy Industries. The companies signed their collaboration agreement at Farnborough on July 21, 2026, covering effects optimization, engineering support, digital integration and common interfaces. Developing the aircraft and its effectors concurrently allows weapon length, fin geometry, bay clearances, ejection mechanisms, electrical requirements, cooling and datalinks to influence the weapons bay design before the airframe configuration is frozen. It also supports later integration of British, Italian, Japanese and potentially export-customer weapons through common interfaces rather than requiring extensive aircraft modifications for each new effector.

  The intended weapons architecture covers long-, medium- and short-range air-to-air combat, precision air-to-surface attack, anti-ship missions and long-range stand-off strike. Existing weapons such as Meteor and SPEAR are relevant technological references, but neither has been definitively established as GCAP armament. No specific anti-ship missile, cruise missile, short-range air-to-air missile or air-to-surface weapon has yet been confirmed for the operational aircraft. The GCAP should therefore currently be described as having an internal multi-role guided-weapons capability with its definitive weapons inventory still under development.

  The GCAP is also intended to generate effects without relying exclusively on conventional missiles. The ISANKE architecture incorporates electronic warfare and electronic attack functions, potentially allowing RF effects to disrupt or suppress hostile sensors and communications as part of the aircraft's engagement sequence. Directed-energy weapons were also investigated during the preceding Tempest programme, and GCAP's electrical generation and thermal management requirements leave potential growth capacity for such high-power systems. However, no operational laser weapon, installation position, or power output has been confirmed, so directed-energy armament remains a potential future capability rather than part of the established GCAP weapons configuration.

• Engines

  The GCAP will use two new-generation turbofan engines jointly developed by Rolls-Royce, Avio Aero and IHI, rather than derivatives of the Eurofighter Typhoon's EJ200. The propulsion programme is also separate from the British Combat Air Flying Demonstrator, powered by the EJ200. Rolls-Royce, Avio Aero and IHI are developing an integrated power and propulsion system in parallel with the Edgewing airframe, with the three companies formalizing their evolved collaboration agreement on September 9, 2025. By July 2026, more than 100 subscale component tests had been completed, the centerline engine demonstrator had progressed through major trilateral design reviews toward final approval, demonstrator-component manufacturing was underway, and a new combustor design had successfully completed testing ahead of full-engine ground trials.

  The available estimate places each GCAP engine above the 35,000 lbf thrust class, equivalent to more than 155.7 kN, although this is not an officially released production-engine rating. With two engines, this would correspond to more than 311 kN of combined thrust if the estimate applies to maximum thrust. The available information does not specify whether the 35,000 lbf figure represents dry or afterburning thrust, so it should not be identified as either. Japan's IHI XF9-1 provides a useful technological reference rather than the GCAP engine itself: the XF9-1 was developed as a low-bypass afterburning turbofan engine with a maximum wet thrust of roughly 147.10 kN (33,069 lbf), and contributed technologies and experience from Japan's earlier F-X propulsion work to the trilateral programme.

  Electrical generation and thermal management are being developed as integral parts of the propulsion system rather than secondary aircraft subsystems. The GCAP must supply large RF sensor arrays, electronic warfare transmitters, communications equipment, mission computers and other high-power electronics while removing the heat they generate. Figures near the 2 MW class have been associated with the GCAP electrical architecture, but the available information does not establish 2 MW per engine as a confirmed specification. The more defensible characterization is therefore megawatt-class electrical generation, with figures near 2 MW cited for the power architecture. This substantial power and cooling margin is also intended to accommodate more demanding sensors, processors, electronic warfare equipment and potentially high-power weapons during an operational life expected to extend beyond 2070.

  The GCAP's large airframe is also intended to carry a substantial quantity of fuel internally. No official fuel capacity has been disclosed, but one aerodynamic assessment estimated that an aircraft of this size and centerbody volume could accommodate 30,000 lb, or 13.6 tonnes, or more of internal fuel, potentially corresponding to a fuel fraction near 0.40. This remains an estimate rather than a programme specification, but it helps explain the unusually broad centerbody and large delta wing. Internal fuel volume is particularly important for a stealth aircraft because relying on external tanks would increase drag and radar signature and would therefore compromise the configuration intended for penetrating missions.

  The GCAP is confirmed as supersonic, but no authoritative maximum Mach number or supercruise speed has been released. Values such as Mach 1.8, Mach 2.0 or Mach 2.5 therefore cannot currently be treated as official specifications. The aircraft's large wing, substantial estimated fuel volume and approximately 50-degree sweep indicate that propulsion and aerodynamic requirements are being balanced around long-range cruise, payload and electrical generation rather than maximum speed alone. Likewise, no confirmed service ceiling, climb rate, acceleration performance, takeoff distance or thrust-to-weight ratio is available because aircraft weight and final engine thrust remain unresolved.

  Range is better constrained by the programme's operational objective than by a published numerical specification. A British capability outline indicated that the GCAP could have sufficient internal fuel for an unrefuelled transatlantic flight, as the Typhoon requires three or four aerial refuellings for a comparable mission. A UK-to-U.S. East Coast geographical distance can exceed 5,500 km, indicating the scale of the internal fuel endurance being pursued, but this should not be entered directly as the GCAP's confirmed ferry range because endpoints, routing, altitude, reserves and flight profile were not specified. Likewise, estimates placing combat radius in the 1,500-2,000+ km class remain engineering assessments rather than programme figures.

  The GCAP will additionally incorporate a Universal Aerial Refuelling Receptacle Slipway Installation (UARRSI), providing compatibility with boom-equipped tanker aircraft. This allows the fighter to receive fuel from aircraft such as the KC-46A and improves interoperability with U.S. and allied tanker fleets, particularly for long-range operations in the Indo-Pacific. Aerial refuelling therefore supplements an aircraft already being designed around unusually large internal fuel capacity rather than compensating for a short basic range. Exact internal fuel mass, ferry range, combat radius, endurance, and aerial refuelling limits remain undisclosed to date.

• Avionics and Onboard Equipment

  The GCAP's mission systems are centered on the ISANKE & ICS (Integrated Sensing and Non-Kinetic Effects & Integrated Communications Systems). Rather than installing radar, electronic warfare, self-protection and communications as largely independent systems, the ISANKE & ICS combines sensing, data fusion, electronic effects, communications and mission processing within a common architecture. Development is conducted by GCAP Electronics Evolution, bringing together Leonardo UK, Leonardo, ELT Group and Mitsubishi Electric. The ISANKE covers the aircraft's sensing and non-kinetic combat functions, while the ICS provides the communications architecture connecting the GCAP with other crewed and uncrewed aircraft and with air, land, sea and space-based nodes.

  The principal RF sensor is being developed around the Multi-Function Radio Frequency System (MRFS), rather than a conventional fighter architecture dependent exclusively on one nose-mounted radar. The GCAP is intended to incorporate multiple distributed RF apertures across the airframe, allowing the electronics architecture to combine active radar, passive RF surveillance, electronic support, electronic attack, and communications functions. Distributed apertures also provide greater angular coverage than a single forward-facing array and contribute to the requirement for near-360-degree situational awareness. Exact aperture locations, array dimensions, transmit/receive module numbers, operating frequencies, detection ranges and simultaneous target capacity have not been disclosed.

  The ISANKE allows the GCAP fighter to operate either actively or passively in the electromagnetic spectrum. In active operation, its RF arrays can transmit to detect, identify, and track targets. In passive operation, the aircraft can detect, classify, and geolocate hostile radar and communications emissions without transmitting radar energy itself, reducing its electromagnetic signature. Several GCAPs or accompanying loyal wingmen can combine observations from geographically separated receivers to improve emitter location and targeting accuracy. A GCAP therefore does not necessarily need to illuminate a target with its own radar before contributing to an engagement.

  The RF architecture is complemented by infrared and electro-optical sensing, providing passive detection against aircraft and other targets without RF emissions. The Italian industry is associated with infrared sensor technology, while British and Japanese companies have major responsibilities for RF sensing, and Japan contributes satellite communications technology. Information from RF, infrared and other sensors is intended to be fused into common tracks rather than displayed to the pilot as independent sensor outputs. No confirmed IRST designation, spectral bands, field of regard, detection range, aperture dimensions, or electro-optical identification range has been released.

  Electronic warfare is incorporated directly into the Non-Kinetic Effects element of the ISANKE, rather than being treated only as a defensive countermeasures suite. The architecture encompasses electronic support, emitter detection and classification, geolocation, jamming, deception, and aircraft self-protection. This permits the GCAP to use electromagnetic effects offensively, including disrupting hostile radar or communications, while distributed operations allow sensing and jamming to be separated geographically. One GCAP or autonomous aircraft could transmit or jam while another remains passive, complicating an adversary's ability to associate the electronic emission with the crewed fighter's position.

  The GCAP will require exceptionally high onboard processing capacity to combine its own RF and infrared information with tracks received from F-35s, Typhoons, AEW&C aircraft, ships, ground forces, satellites and autonomous aircraft. Earlier Tempest MRFS development targeted generation of up to 10,000 times more data than existing systems, illustrating the processing scale being pursued rather than establishing a production GCAP sensor specification. AI-assisted processing is intended to correlate detections, identify and prioritize threats, manage electronic warfare, and reduce the quantity of raw sensor information requiring direct pilot interpretation. The software-defined architecture is also intended to allow new radar modes, electronic warfare techniques, communications functions, and sensor fusion algorithms to be introduced through software and computing upgrades during the aircraft's service life.

  The same computing and communications architecture supports crewed-uncrewed teaming (MUM-T). The GCAP is intended to supervise collaborative combat aircraft (CCAs) through mission-level commands rather than requiring its pilot to manually fly each autonomous aircraft. Tasks could include searching a designated sector, extending the formation's sensor coverage, investigating an emitter, conducting electronic attack, screening the crewed fighter, or engaging an assigned target. The ICS provides the network through which sensor tracks, targeting information, commands, and mission data can move between these distributed aircraft. Autonomous aircraft can consequently extend the GCAP's effective sensing, electronic warfare, and weapons footprint well beyond the crewed fighter's own position.

  Cockpit equipment is less firmly defined. Earlier Tempest development investigated large-area and virtual displays, helmet-projected augmented reality, eye tracking, gesture control, biometric and physiological monitoring and an AI-based Intelligent Virtual Assistant, but these technologies cannot yet all be identified as production GCAP equipment. The Farnborough 2026 full-scale configuration provides a more concrete indication of the current design direction, incorporating an ejection seat, physical control stick and large-area cockpit display. The production ejection-seat model, helmet-mounted display, HUD arrangement, display dimensions, and final human-machine interface remain undisclosed.

The 2026 GCAP concept uses a tailless delta-wing configuration, with no conventional horizontal stabilizers or prominent vertical tailfins.