Lockheed L-205 (MX1554)

History of the Lockheed L-205 (MX1554)

In October 1947, the Bell X-1 rocket-powered research aircraft demonstrated straight, horizontal, supersonic flight (described in detail elsewhere) at on this page), aerospace designers focused on producing a viable military end product that would serve as the first supersonic machine for the United States Air Force (USAF) after World War II. Ultimately manifesting in the North American F-100 "Super Sabre", McDonnell F-101 "Voodoo" and CONVAIR F-102 "Triangle Dagger" types, the end of the road goes through multiple stops involving many proven defenders industry at the time, including Lockheed.

The L-205 project aircraft was the company's template for future needs and appeared in paper form around January 1951. It was designed to meet the official XM1554 interceptor specification of 1950, with an off-the-shelf solution available as early as 1954.

In true Lockheed fashion, the aircraft was given a sleek and aerodynamically refined look to achieve the expected supersonic speeds. The overall design of this fighter is a single-seat configuration, with the pilot sitting on the ejection seat under a two-piece canopy behind the nose cone assembly. The main planes have a relatively small surface area and sit aft in the center of the boat for balance, the low planes are tapered on both the leading and trailing edges and truncated at their tips (similar in form and function to another supersonic product ) F-104 "Starfighter" from Lockheed).

Range extender tanks will be mounted on the wingtips (like on the F-104). The fuselage tapers to the rear and is covered by a vertical stabilizer fin, with the horizontal plane attached halfway. The propulsion scheme sees system exhaust flowing out under the rear wing.

Mobile retractable landing gear shall be available for ground operations.

The most unique (and relatively unconventional) aspect of this inlet was the air intake, which was a semi-circular opening at the top of the fuselage, aft of the canopy/cockpit section. This feature clears the lower half of the fuselage and optimizes airflow under the fighter, while adding inherent protection to the aspirated engine against ingestion of foreign objects.

While no specific engine was specified, performance requirements at the time (primarily technically limited) would have resulted in a fighter jet having a top speed of at least 1,265 mph (to meet the Mach 1 target). While flying at altitudes over 60,000 feet - well within the intended target altitude for intercepting Soviet bombers. An advanced airborne fire control system (FCS) will assist in interception and ensure target destruction, and weapons should be centered on current generation missile technology.

In the case of the L-205, these would be 6 x Falcon air-to-air missiles (AAM) as well as 20 x 70mm high-explosive (HE) wing-stabilized airborne missiles, all mounted on the mid-belly of the internal armament Brackets (another feature that keeps the fighter streamlined).

When finished, the L-205 has a barrel length of 63.8 feet and a wingspan of 30.3 feet. Combat weight will reach 27,765 pounds, increasing to 32,125 pounds when fully loaded. The aircraft has an estimated range of 1,760 miles and a powered climb rate of 15,000 feet per minute.

As with other project fighter jets shortly after World War II, this Lockheed entry was not selected for further work, despite its promising qualities.

Specification

Basics

Years of Service

1954

Origins

United States

Status

Cancel

Development ended.

Crew

1

Production

0

Manufacturer

Lockheed - USA

Carrier

United States (removed)

scrolling

air-to-air combat, fighter

The general ability to actively attack other aircraft of similar form and function, usually using guns, missiles and/or airborne missiles.

Intercept

The ability to intercept incoming airborne threats with high performance, usually speed and rate of climb.

X-Plane (development, prototype, tech demo)

Aircraft designed for prototyping, technology demonstration, or research/data collection.

Attention Features

Inner Well

Hull volume includes space for internal weapons or special mission equipment.

High-speed performance

Can accelerate to higher speeds than the average aircraft at the time.

High performance

The ability to fly and operate at higher altitudes than the average aircraft of the day.

Extended range performance

Ability to travel long distances using on-board fuel supplies.

Super performance

The design covers the three key performance categories of speed, altitude and range.

Pilot/crew ejection system

Auxiliary procedures to allow pilot and/or crew ejection in the event of an air emergency.

Depression in crew members

Support the pressurization required for crew survival at higher operating altitudes.

Closed crew room

There are partially or fully enclosed crew work areas.

Scalable

Has retractable/retractable landing gear to maintain aerodynamic efficiency.

Dimensions and Weight

Length

63.8 feet

(19.45m)

Width/span

30.3 feet

(9.25m)

Cured weight

24,692 lbs

(11,200 kg)

MTOW

32,187 lbs

(14,600 kg)

Wgt Difference

+7,496 lbs

(+3,400 kg)

MAINPLANE STRUCTURE

wing/low/straight

Monoplane

Designed to use a single main wing main aircraft; this is the most popular arrangement of main aircraft.

install low

The main aircraft is mounted low on the side of the fuselage.

Straight

Floor plans involve the use of simple, straight main plan elements.

(Structural descriptors refer to production variant Lockheed L-205)

Performance

Installed:

Not specified; uses turbojets or possibly rocket-boosted engines to meet performance targets.

Maximum speed

786 km/h

(1,265 km/h | 683 kn)

Cruising speed

590 km/h

(950 km/h | 513 kn)

Maximum speed difference

+196 km/h

(+315 km/h | 170 kn)

Maximum

63,009 feet

(19,205 m | 12 km)

Area

1,762 km

(2,835 km | 5,250 nautical miles)

rate of climb

15,000 ft/min

(4,572 m/min)

Range (MPH) Subsonic: <614mph | Transonic: 614-921 | Supersonic: 921-3836 | Hypersonic: 3836-7673 | Hypersonic: 7673-19180 | Reentry: > 19030

Weapons

Recommended: 6 x Falcon Air-to-Air Missiles (AAM) in internal ventral weapons bay. 20 x 2.75 in (70 mm) high-explosive (HE) tail stabilized airborne missiles in the interior ventral weapons bay.