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Vultee P-1015

High-Altitude Interceptor Aircraft Proposal [ 1941 ]

The Vultee P-1015 project interceptor was born from the same USAAC requirement that saw the Lockheed P-38 Lightning materialize.

Authored By: Staff Writer | Last Edited: 05/11/2020 | Content ©www.MilitaryFactory.com | The following text is exclusive to this site.

The same United States Army Air Corps (USAAC) requirement (X-608) that ultimately produced the classic, war-winning Lockheed P-38 "Lightning" single-seat, twin-engine heavy fighter also produced several lesser-known submissions from competitors of the period. This included a twin-engine submission from Vultee Aircraft Company which marketed its P-1015 project fighter against the requirement. While not selected, the aircraft nonetheless deserves attention as it sheds a little light on the thinking of the pre-World War 2 period.

Requirement X-608 appeared in February of 1937 and included submissions from a few select players including Curtiss, Lockheed, and Vultee. The requirement called for a new, all-modern single-seat high-altitude interceptor type operating on two engines. The powerplant of choice was 2 x Allison V-1710 liquid-cooled inline piston engines (with accompanying turbo-superchargers for enhanced high-altitude performance) helping to deliver a maximum speed of 360 miles-per-hour (at altitude) and a rate-of-climb of 3,333 feet-per-minute. A tricycle undercarriage was sought but not required.

The Vultee P-1015 utilized a conventional twin-engine arrangement in which each inline engine would be seated at each wing mainplane member. The nacelles would run completely through the member and extend out from the leading edge while meeting the trailing edge. The mainplanes were rounded at their tips and tapered along both edges while being mounted low and ahead of midships. The fuselage was purposefully drawn up as very slim, allowing just enough space to carry essentials including fuel stores and avionics. The cockpit was positioned well aft of a nosecone assembly which was designed to house the primary armament. The cockpit was to have a largely unobstructed canopy for excellent viewing and be positions ahead of midships. The tail unit was traditional, featuring a single vertical fin and a pair of low-set horizontal planes. The undercarriage was proposed as a "tail dragger" type with the main legs retracting inwards toward fuselage centerline at the wing roots (and not in each engine nacelle as was typical) while the tailwheel was situated under the tail in the usual way.

Structurally, the interceptor was given a running length of 40.10 feet and a wingspan of 54 feet.

Each Allison inline piston engine would drive a three bladed propeller unit in tractor fashion. The two installations would rotate in such a way as to cancel out the naturally occurring effects of torque encountered when using just a single engine. As such, the aircraft could be expected to showcase natural stability and the pilot's forward vision would remain unobstructed.

The proposed armament suite was in line with what the eventual competition winner fielded - 4 x 0.50 caliber Browning air-cooled Heavy Machine Guns (HMGs) coupled with a single 20mm automatic cannon, all to be housed in the nose assembly. This allowed for ease-of-maintenance / resupply as well as kept the weapons outside of the propeller arcs so no interrupter gear would be needed.

While this Vultee project aircraft was not awarded the USAAC contract, the design did undergo some wind tunnel testing before it met its end. These provided some promising figures for an interceptor that was never to be.

NOTE: Performance specifications found on this page are estimates on the part of the author.©MilitaryFactory.com
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Vultee Aircraft - USA
United States (cancelled)
Operators National flag of the United States
Service Year
United States
National Origin
Project Status

General ability to actively engage other aircraft of similar form and function, typically through guns, missiles, and/or aerial rockets.
Ability to intercept inbound aerial threats by way of high-performance, typically speed and rate-of-climb.
Aircraft developed for the role of prototyping, technology demonstration, or research / data collection.

40.9 ft
(12.47 meters)
54.0 ft
(16.45 meters)
12,125 lb
(5,500 kilograms)
Empty Weight
22,046 lb
(10,000 kilograms)
Maximum Take-Off Weight
+9,921 lb
(+4,500 kg)
Weight Difference

2 x Allison V-1710-C7 turbo-supercharged liquid-cooled inline piston engines developing an estimated 1,600 horsepower each and driving three-bladed propeller units in tractor arrangement.
258 mph
(415 kph | 224 knots)
Max Speed
41,010 ft
(12,500 m | 8 miles)
3,107 miles
(5,000 km | 2,700 nm)
4,550 ft/min
(1,387 m/min)

MACH Regime (Sonic)
RANGES (MPH) Subsonic: <614mph | Transonic: 614-921 | Supersonic: 921-3836 | Hypersonic: 3836-7673 | Hi-Hypersonic: 7673-19180 | Reentry: >19030

1 x 20mm (Hispano M29(C)) automatic cannon in the nose (150 rounds estimated).
4 x 0.50 caliber Browning air-cooled Heavy Machine Guns (HMGs) in the nose (500 rounds-per-gun estimated).


P-1015 - Base Project Designation; some wind tunnel testing completed before project's formal end.

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