One of two parallel studies to meet a VVS requirement
for a new frontal fighter capable of operating from
small, austerely-equipped forward bases, the
MiG-23PD - Pod'yomnye dvigateli, or, literally, "lifting
engines" - or 23-01 was first flown on 3 April 1967. Featuring
a 57° delta wing planform fundamentally
similar to that of the MiG-21 but scaled up 73.6%,
the MiG-23PD alias 23-01 featured auxiliary lift engines
close to the CG. Two 2350kg Kolesov
RD-36-35 engines were accommodated by a bay inserted
in the centre fuselage and provided with a rear-hinged
and louvred dorsal trap-type intake box and a
ventral grid of transverse louvres deflecting the jet
thrust during accelerating transition. A similar
arrangement had been tested by the OKB in the previous
year with the MiG-21PD test bed, which, with a
90cm fuselage lengthening aft of the cockpit
and two RD-36-35 lift engines, had entered flight test
on 16 June 1966. The primary power plant of the
MiG-23PD was a Khachaturov R-27-300 of 5200kg and 7800kg with afterburning,
and air was bled from the last compressor stage for
flap blowing, the combination of lift engines and blown
flaps reducing take-off distance to 180-
200m. Armament consisted of one 23mm GSh-23
cannon and two AAMs - one radar-guided K-23R and
one IR-homing K-23T. Flight test continued until the autumn of 1967 when further development was discontinued
in favour of the parallel MiG-23-11.
|A three-view drawing (1677 x 1000)|
| Take-off weight||18500 kg||40786 lb|
| Wingspan||7.72 m||25 ft 4 in|
| Length||16.80 m||55 ft 1 in|
| Height||5.15 m||17 ft 11 in|
| Wing area||40.00 m2||430.56 sq ft|
|REDSOUN, e-mail, 23.04.2014 12:26|
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|cengiz gündoğdu, e-mail, 08.03.2012 17:25|
güzel bir uçak kısa kalkış için flap üflemesi o yıllara göreoldukça farklı bir dizayn
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