Credit
Don S. Montgomery, USN · Public domain · Resized · Public domain · Source ↗ · Modified
FORCETALLY
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At a glance
AIM-54 Phoenixlarger figure on 1 of 1
K-13 (missile)larger figure on 0 of 1
Counts only measures both sources give with the same scope. A larger figure is not a better system.
Measured figures
Length
Single source12 ft 9 + 1 ⁄ 2 in (3.9 m)[source]
R-13M
Single sourceConfiguration
| Specification | AIM-54 Phoenix | K-13 (missile) |
|---|---|---|
| Type | Long range BVR air-to-air missile[source] | Short-range infrared homing air-to-air missile[source] |
| Place of origin | United States[source] | Soviet Union[source] |
| In service | 1974–present[source] | 1961[source] |
| Used by | United States Navy (former) Iranian Air Force[source] | See Operators |
R-3R
Single source2.830 m (9 ft 3.4 in) (R-13M) 3.48 m (11 ft 5 in) (R-3R)[source]
Maximum; AIM-54A/B - Mach 4.3 (
Single sourceMaximum; ) AIM-54C – Mach 5 (
Single sourceMaximum; Maximum speed · source measurement 3
Single sourceMaximum; Maximum speed · source measurement 4
Single sourceAIM-54A/B - Mach 4.3 (1,460 m/s; 4,800 ft/s) AIM-54C – Mach 5 (1,700 m/s; 5,600 ft/s)[source]
Operational; AIM-54A/B
Single sourceOperational; AIM-54C
Single sourceAIM-54A/B - 72.9 nmi (135.0 km; 83.9 mi) AIM-54C – 99.4 nmi (184.1 km; 114.4 mi)[source]
Operational; Operational range
Single sourceR-3S / R-3R · effective
Single sourceWarhead weight
Single source133 lb (60.33 kg)[source]
Bars compare reported quantities only. A larger figure does not make a system better; configurations and test conditions differ.
| Designer | Hughes Aircraft Company[source] | — |
|---|
| Designed | 1960–1966[source] | — |
|---|
| Manufacturer | Hughes Aircraft Company Raytheon Corporation[source] | Vympel[source] |
|---|
| Unit cost | US$ 477,131 (1974 FY)[source] | — |
|---|
| Produced | 1966-1993[source] | — |
|---|
| Warhead | AIM-54A/B - HE continuous rod AIM-54C – HE Mk 82; WDU‐29/B continuous rod[source] | 7.4 kg (16 lb)[source] |
|---|
| Detonation mechanism | Proximity fuze[source] | — |
|---|
| Engine | Solid propellant rocket motor[source] | solid-fuel rocket engine[source] |
|---|
| Flight ceiling | 103,500 ft (31.5 km)[source] | — |
|---|
| Guidance system | Semi-active radar homing and terminal phase active radar homing[source] | infrared homing[source] |
|---|
| Launch platform | Grumman F-14 Tomcat[source] | MiG-21 , MiG-23 , MiG-19 , MiG-17 Sukhoi Su-17/20/22[source] |
|---|
| References | Janes[source] | — |
|---|
| Guidance | — | (R-3S) infrared homing ; (R-3R) SARH[source] |
|---|
| Launch weight | — | (R-3S) 75 kg (166 lb); (R-3R) 93 kg (205 lb)[source] |
|---|
| Explosive content | — | 5.3 kg (11.68 lbs) of TGAF-5 (40% TNT, 40% RDX, 20% Aluminium powder)[source] |
|---|
| Fuze | — | type 428 proximity fuze and I-107 Contact fuze (R-3R)[source] |
|---|
| Former operator · Bulgaria | — | Bulgaria[source] |
|---|
| Former operator · Guinea | — | Guinea[source] |
|---|
| Reported operators |
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|---|
R-3S / R-3R · max
Single source