Other designations or related variants include—unknown.

Production/Prototype Quantities —All aircraft were testbeds and were built in quantities of one each or were modified from earlier airframes.

Cockpit—All aircraft were single-ejection seat equipped. The controls were standard stick and rudder and instrumentation was totally analogue. Canopy designs were all faired-bubble either of organic glass or stretched acrylic (though almost certainty the former due to the temperature extremes experienced in high speed flight). Test instrumentation also was mounted in cockpit area. Cockpits all were pressurized and air-conditioned. Militarized testbed samples (Ye-152/Ye-152A) were equipped w/cockpit equipment and the Uragon-5B radar for integration into the Uragon-5 ground-control-intercept system.

Fuselage—Circular cross-section of primarily aluminum stressed-skin construction. All of the aircraft in this series were designed around the classic circular MiG nose intake and its associated shock spike assembly. The latter, in the Ye-152 and Ye-152A, housed the Uragon-5B radar unit behind a dielectric cone. In the case of the Ye-152M/Ye-166, the spike represented an extreme example of the Oswatitsch-type multi-cone-angle (4) design optimized for Mach 3+ speeds. The associated intake tunnel, w/the exception of the bifurcation for the cockpit and nose landing gear well, was large and relatively long. Boundary layer bleed slots were built into the throat area and dumped excess air overboard via large, faired exhausts on top of the nose (ahead of the windscreen) and below the nose. Conversely, blow-in doors for improved mass flow during taxi and while operating at low forward velocities, also were provided. The single-piece canopy was faired into a dorsal canoe that ran to the very aft end of the aircraft and into the base of the vertical fin. On the Ye-166, there were two hexagonally-shaped fairings w/one on either side of the nose. These are thought to be the original mounting points for a set of stabilizing canards utilized to increase directional stability during high-speed flight. Empennage area of all Ye-150 family members utilized titanium and steel to accommodate engine heat and dynamic loads.

Lifting and Control Surfaces —Conventional MiG-family delta planform w/57° leading edge sweep angle and approx. 4% thickness/chord ratio. Essentially three-spar design of aluminum construction. Hydraulically-boosted ailerons and hydraulically-actuated Fowler type flaps of conventional design and construction. Vertical tail surfaces of broad chord, thin-section design. Rudder hydraulically-boosted. On Ye-166, vertical fin had bullet fairing at dorsal extension break point w/camera for photographic observation purposes. Ye-166 w/single large ventral; Ye-152/Y-152A equipped w/two large ventrals angled outward from vertical plane. Various antennas and aerials mounted on vertical fin either externally or under dielectric panels. Hydraulically-boosted slab-type stabilators for pitch control only were mounted on the empennage. The Ye-166 is known to have flown w/movable or at least ground-adjustable canard surfaces mounted on its nose. A single wing fence was provided on each Ye-166 lower wing surface, only.

Landing Gear —The landing gear was generally similar to that found on the standard MiG-21 family, but w/out levered suspension system. Tricycle design w/main gear retracting inward toward fuselage centerline. Nose gear retracted forward. Main gear equipped w/disc-type brakes. It is presumed that the Ye-150, Ye-152, Ye-152A. and Ye-152M/Ye-166 were equipped w/a drag chute. Wheel and tire size required faired bulges on outside of wheel well doors. Steering is thought to have been via differential braking.

Miscellaneous Equipment —Large test boom mounted under forward nose section.

Powerplant/Fuel —The Ye-150 was powered by a single 20,503 lb. (9,300 kg.) th. Tumansky R-15-300M turbojet. The Ye-152A was powered by two 12,125 lb. (5,500 kg.) th. Tumansky R-11F-300 turbojets. The Ye-152 was powered by a single 22,046 lb. (10,000 kg.) th. Tumansky R-15-300 turbojet. The Ye-152M/Ye-166 was powered by a single 22,046 lb. (10,000 kg.) th. Tumansky R-15F-300 turbojet. Fuel carried in various dorsal fairing, fuselage. and wing fuel tanks. Ye-166 vertical tail is stated by some sources to have integral tanks, as well.

Armament —Two wing pylons on fighter-optimized Ye-152/Ye-152A testbeds to carry either K-8 or K-9 radar guided air-to-air missiles No guns carried. Radar interfaced w/weapon system and also Uragon-5 GCI.

Length —Ye-150: 63 ft. 6 in (19.8 m); Ye-152: 63 ft 6 in. (19.8 m); Ye-152A: 63 ft. 6 in. (19.8 m.); Ye-152M/Ye-166: 60 ft. 0 in (18.7 m).

Wingspan —Ye-150: 28 ft. 9 in (8,97 m); Ye-152: 28 ft. 9 in (8,97 m); Ye-152A: 28 ft. 9 in. (8.97 m); Ye-152M/Ye-166: 28 ft. 9 in (8.97 m).

Wing area —Ye-150: 304 ft.2 (28.2 m.2); Ye-152: 304 ft.2 (28.2 m.2): Ye-152A: 304 ft.2 (28.2 m.2); Ye-152M/Ye-166: 304 ft.2 (28.2 m.2).

Height — unknown

Empty weight — unknown.

Gross weight —Ye-150: 24,030 lb (10,900kg); others unknown.

Max. speed @ s.l.—unknown.

Max. speed —Ye-150: 1,864 mph at 48,125 ft. (3,000 km/h at 15,000 m); Ye-152: 1,883 mph at 64,167 It. (3,030 km/h at 20,000 m ) and 1,336 mph at 32,083 ft. (2,150 km/h at 10.000 m); Ye-152A: 1,553 mph at 64,167 ft. (2,500 km/h at 20,000 m.) and 1,342 mph at 32.083 ft. (2,160 km/h at 10,000 m); Ye-152M/Ye-166: 1,870 mph (3,010 km/h).

Rate of climb —Ye-150: 2 min 6 sec to 48,125 ft (15,000 m); Ye-152: 1 min 24 sec. to 32.083 ft. (10,000 m.); Ye-I52A: 1 min 30 sec to 32,083 ft. (10,000 m.)

Service ceiling-Ye-150: 80.208 ft (25,000 m); Ye-152: 80,208 ft (25,000 m); Ye-152A: 67,375 ft (21,000 m.).

Max.range — Ye-150:932mi. (1.500km); Ye-152:913 mi.(1.470km);Ye-1 S2A(w/aux tanks): 1.429mi.(2.300 km)

Notes — none.