During the 1960s, in the global race to achieve supersonic passenger flight (under the adopted title of "SuperSonic Transport" - or "SST"), the American concern of Boeing drew up plans for a 250- to 300-seat speedster under the model designation of "2707". This aircraft would have been powered by no fewer than four turbojet engines and reach cruising speeds near Mach 3 (approximately 2,300 miles-per-hour). While some development on the advanced aircraft was had during the height of the Cold War period (1947-1991), it was ultimately cancelled in full during 1971. By this time, Europe had already been flying its classic "Concorde" supersonic airliner and the Soviets delivered on their Tupolev Tu-144 (both detailed elsewhere on this site).
Lockheed, another contender for the SST competition, also cancelled their "L-2000" development in 1971. North American Aviation proposed their "NAC-60" which was based on their ultimately-abandoned / cancelled XB-70 "Valkyrie" supersonic bomber.
Supersonic airliners were on Boeing's radar as early as the early-1950s as several design studies were undertaken into the feasibility of such aircraft in the commercial sector. Momentum grew before the end of the decade and the company began to pour additional funding and engineering power into the concept which ultimately begat such internal projects as the "Model 733". The movement was aided by the political and military "race" against the East that was the "Cold War", with the primary enemy being the Soviet Union.
Three versions of what would become the "Model 2707" SST were drawn up by Boeing engineers: the original "Model 2707-100" was to feature a variable sweep ("swing-wing") wing for real-time, in-air changes to the mainplanes as needed, the "Model 2707-200" sporting canards for additional control (while retaining the swing-wings of the Model 2707-100), and the "Model 2707-300" with its more traditional fixed-wing mainplanes.
As finalized, the canard-equipped, swing-wing Model 2707-200 was to have an overall length of 306 feet, a wingspan of 180.3 feet, and a height of 46.2 feet. Empty weight was to reach 287,500lb against a Maximum Take-Off Weight (MTOW) of 430,000lb.
The most likely form, the Model 2707-300, showcased a slim, rounded fuselage with a very pointed nosecone at front and traditional single-finned tail unit at the rear. The nosecone would have been hinged to angle down and provide improved viewing for the piloting crew during ground maneuvering, take-off, and landing actions. The wings were of delta-wing configuration with well-swept leading edges and straight trailing edges. Under each wing member, and towards the trailing edge line, would be four podded engine nacelles each housing a single turbojet engine (two engines per wing). A tricycle undercarriage would be fitted for ground-running with the nose leg sporting twin wheels and the main legs given six wheels each (across three bogies) - such was the estimated weight of this massive aircraft.
Power was slated to come from 4 x General Electric GE4/J5P afterburning turbojet engines outputting 63,200lb of thrust each. This would have allowed for cruising speeds of 1,800 miles-per-hour, a range out to 4,250 miles, and a service ceiling of 73,000 feet.
Internally, the Model 2707 was to feature an advanced "glass" cockpit at a time when "steam" guages dominated instrument panels. The operating crew would have been at least three personnel.
Despite advancements in aviation technology, the age of the "supersonic airliner" never materialized to the levels originally envisioned so both the Concorde and Tu-144 saw only limited production numbers (20 and 16 units, respectively) and were restricted in their operational use. There proved too many issues in attempting to get passengers to their destinations in short-order: operating noises, shockwave concerns, excessive fuel burn (a common failing of early turbojets), and limited passenger seating / cargo-hauling capabilities within the slim and narrow fuselage designs. As such, air carriers eventually moved away from the concept of supersonic passenger flight in the subsequent decades and, only recently, has the topic been revisited through several upcoming, in-development designs detailed throughout this site.
Boeing managed to complete a single mock-up of its Model 2707.
Specifications
Year: 1971
Status Cancelled
Crew 3
Production 0 Units
Boeing Company - USA
United States (cancelled)
- Transport
- Commercial Market
- X-Plane / Developmental
Length:
305.94 ft (93.25 m)
Width:
180.45 ft (55 m)
Height:
46.26 ft (14.1 m)
Empty Weight:
287,483 lb (130,400 kg)
MTOW:
674,615 lb (306,000 kg)
(Diff: +387,132lb)
(Showcased weight values pertain to the Boeing Model 2707-200 production model)
4 x General Electric GE4/J5P turbojet engines developing 63,200 lb of thrust each.
Max Speed:
1,802 mph (2,900 kph; 1,566 kts)
Service Ceiling:
72,178 feet (22,000 m; 13.67 miles)
Max Range:
4,890 miles (7,870 km; 4,249 nm)
Rate-of-Climb:
5,000 ft/min (1,524 m/min)
(Showcased performance values pertain to the Boeing Model 2707-200 production model; Compare this aircraft entry against any other in our database)
None.
(Showcased armament details pertain to the Boeing Model 2707-200 production model)
Model 2707 - Base Series / Project Designation.
Model 2707-100 - Initial design model with variable-sweep wing mainplanes.
Model 2707-200 - Canards added for broadened control zones; swing-wing capability of the -100 variant retained.
Model 2707-300 - Fixed wing mainplanes.
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United States (cancelled)
