MiG-17F / SP-2

The focus of this program was the performance of the RP-3 Kor – shun ("kite") ranging radar designed by the Slepushkin OKB. The Kor- shun-equipped MiG-17F was built in response to two directives from the USSR council of ministers, dated 10 June 1950 and 10 August 1951. These directives called for the development of a fighter “to intercept and destroy, day or night and whatever the weather conditions, any enemy bomber, reconnaissance aircraft, or escort fighter." The Kor – shun ranging radar used a Cartesian-coordinate scanning mode.

The SP-2, derived from the SI-2, differed from the basic MiG-17F in the following ways:

1. The fuselage nose section had to be modified

2. The N-37D cannon was removed, but the ammunition reserve for

The SP-2 was an experimental variant of the MiG-17F intended to assess the perfor­mance of the Korshun radar.

the remaining NR-23 guns was increased to 90 and 120 rounds, respectively

3. Several systems were relocated

4. The airbrakes opened automatically at M 1.03 and retracted as soon as the aircraft’s speed dropped to M 0.97 (and they could still be operated manually)

5. The camera gun was moved to the right side of the engine air intake

6. The capacity of the rear fuselage tank was increased to 250 1 (66 US gallons) from 195 1 (51 US gallons)

G. A. Sedov conducted the factoiy tests between March and Nov­ember 1951. State acceptance trials were carried out from 28 Novem­ber to 29 December by Nil WS and PVO military pilots such as A. P. Suprun, Yu. A. Antipov, V. G. Ivanov, Ye. I. Dziuba, Ye. Ya. Savitskiy, and R. N. Sereda. Experiments with the Korshun radar proceeded in July and August 1951 on an 1-320 fighter prototype. The Korshun was basically a modified rendition of the Toriy-A, which was tested from February to May 1950 in an SP-1. Neither radar could operate in an automatic tracking mode.

The SM 1 is in fact the MiG-15 bis 45 reengmed with two Mikulin AM 5As These tur bojets were later fitted with afterburners and renamed AM-5F

Specifications and Performance of the SP-2 Specifications and performance Design requirements SP-2 Takeoff weight — 5,320 kg (11,725 lb) Fuel capacity – 1,510 1 (399 US gal) Maximum speed At 3,000 m (9,840 ft) – 1,109 km/h (599 kt) At 5,000 m (16,400 ft) 1 094 km/h (591 kt) 1,097(592) At 10,000 m (32,800 ft) 1,042(563) 1,046 (565) At 12,000 m (39,360 ft) 1 022 (552) 1,020(551) Maximum Mach number — 1.03 Climb To 5,000 m (16,400 ft) 2 mm 2 min To 10,000 m (32,800 ft) 5 1 5.2 Service ceiling 15,600 m (51,170 ft) 15,200 m (49,860 ft) Range at 12,000 m (39,360 ft) Without drop tanks 1,300 km (805 mi) 1,375 km (855 mi) With drop tanks 2,500 (1,550) 2,510 (1,560) Armament 2 x NR-23 2 X NR-23 Ammunition 90 + 120 rounds Source: MiG OKB

The following extract from the final test report is especially note­worthy:

1. The SP-2’s performance meets the targets stipulated in the direc­tives of the USSR council of ministers

2. The SP-2’s performance data are almost identical to those of the MiG-17F

3. The aircraft’s combat capabilities are limited because it is diffi­cult for the pilot of a single-seater to follow up the Korshun data (searching for, approaching, and sighting the target) for several reasons: first, it is impossible to determine with sufficient accura­cy the distance between the fighter and its target; second, it is impossible to reduce the aircraft’s speed quickly when approach­ing the target because of the poor efficiency of the airbrakes; and third, the radar is not very reliable

4. Taxiing and taking off with two 600-1 [158-US gallon] drop tanks is rather tricky because of the aircraft’s inertia

For these and other reasons the Nil WS put an end to the Korshun research program. The table above is quite noteworthy because it allows us to compare the design performance data outlined in the gov­ernment directives with those of the SP-2