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Arrow Specs
Some tech scans from Avro Documents.
Description
Dimensions and General Data
 
 
 
GENERAL DESCRIPTION
1 The Avro ARROW 1 is a delta wing supersonic, high altitude,
all weather interceptor. The first aircraft is powered by two
Pratt & Whitney J75 P3 gas turbine engines which are of the
twin spool compressor type with afterburners. Subsequent aircraft
will be powered by two J75 P5 series engines. Each engine of
both series develops a military rated thrust of 15,500 pounds
and a maximum thrust of 23,500 pounds.
2 The crew of two, a pilot and a navigator, are accommodated
in separate cockpits arranged in tandem. Each cockpit is enclosed
by a clam-shell type canopy which is normally opened and closed
electrically. An explosive cartridge system is employed to open
the canopies in an emergency. The cockpits are equipped with
Martin-Baker C5 ejection seats to enable the crew to abandon
the aircraft. Firing of the emergency canopy system and seat
ejection are interconnected and require only one operation.
3 The airframe is of all metal stressed skin construction. The
structure is an integral assembly with centre and inner wing
torsion boxes forming the basis of the structure. The vertical
stabilizer is secured to the centre torsion box. The inner wing
torsion box skins are machined from the solid and the outer wing
skins are taper rolled. The engines, duct bay, engine bay and
rear fuselage are suspended from the inner wing to provide flexibility
to the structure.
4 The aileron, elevator and rudder flying control surfaces are
operated by a duplicated hydraulic system which powers control
surface actuators. A damping system stabilizes the aircraft in
all three axes, and also provides automatic rudder co-ordination.
Provision is made for three modes of control, Normal, Automatic
and Emergency. Hydraulic power is required for all three modes.
5 in the normal mode of control, forces applied to the control
column by the pilot are converted to electrical signals which
control electro-hydraulic servos. The movement of these servos
is transmitted through the mechanical system to control the aileron
and elevator hydraulic actuators.
6 In the automatic mode control signals to operate the electro-hydraulic
servos can be originated by a ground station, or from the aircraft
fire control or automatic navigation systems .
7 In the emergency mode, movement of the control column is boost
assisted and transmitted by the cables to control the aileron
and elevator actuators. Yaw damping and automatic rudder co-ordination
only are retained in this mode.
8 The air conditioning system uses air tapped from the engine
compressors. The air is cooled by air-to-air, and air-to-water
heat exchangers, and by an air turbine and fan unit. The system
supplies conditioned air to pressurize the cockpits. It also
supplies conditioned air to the electronic equipment and the
armament bay to maintain them at an operational working temperature.
An emergency ram air supply provides cooling air to the essential
equipment in the event of failure of the main system.
9 A low pressure air system supplied by air from the air conditioning
system provides air pressure for the inflation of canopy seals,
the instrument pack seals and the pilot and navigators anti-'g'
suits.
10 Fuel is carried in twelve integral wing tanks and in two
rubber cell type tanks in the fuselage. One of the tanks in each
wing acts as a collector tank and fuel is pumped to the engine
by a mechanically driven booster pump mounted in each collector
tank. Fuel is transferred to each collector tank through a flow
proportioner unit, from the wing tanks by air pressure, and from
the fuselage tanks by a combination of air pressure and electrically
driven transfer pumps.
11 The tanks in the RH wing and the front fuselage tank normally
feed the RH engine, and the tanks in the LH wing and the rear
fuselage tank, the LH engine. Provision is made for crossfeeding.
MISSING PAGE
FIXED DIMENSIONS
AND GENERAL DATA
CHARACTERISTICS:
ARROW 1 and ARROW 2
Length of aircraft (excluding probe)
(77 ft 9.65 in)
 
(76 ft 9.65 in)
Height of aircraft over highest portion of fin
21 ft 3.0 in
Ground angle (Angle between aircraft reference line and
ground static line)
4.55 degrees
Tread of main wheels
25 ft 5.66 in
Wheel base
30 ft 1.0 in
 
 
WINGS:
 
Wing area (including ailerons, elevators and 390.5 sq ft
of fuselage and not including 28.63 sq ft of extended leading
edge)
1,225.0 sq ft
Span
50 ft 0.0 in
Chord-Root
45 ft 0.0 in
       -Construction
tip
4 ft 4.98 in
Mean Aerodynamic Chord
30 ft 2.61 in
 
 
 
 
 
 
 
 
The landing gear is of the hydraulically-actuated- tricycle
type, with the main gear retracting inward and forward into the
inner wing. The steerable nose gear retracts forward into the
front fuselage.
The landing gear, wheel brakes, nosewheel steering and speed
brakes are actuated by a 4,000 psi utility hydraulic system.
A compressed air system is available for emergency lowering of
the landing gear. The fully powered and irreversible flying control
surfaces are operated by a separate 4, 000 psi hydraulic system
consisting of two completely independent circuits.
Power for the electrical system is provided by two engine-driven
alternators with constant speed drives for alterating current,
and two transformer-rectifiers for conversion to direct current.
Where necessary space in the radar nose and weapon bay is utilized
for test equipment and instrumentation to enable the development
aircraft to carry out their designated role as flight test vehicles.
The external configuration of the ARROW 2 is basically the same
as that of the ARROW 1. However, there are major internal differences,
namely the weapon pack carrying four Sparrow 2D air-to-air guided
missiles, installation of the ASTRA 1 electronic system, and
replacement of the J75 engines with Orenda Iroquois engines.
Provision is made for a jettisonable external fuel tank, and
the mechanical proportioner type fuel system used for centre
of gravity control on the ARROW 1 is replaced by an electrically
controlled sequencing system.
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Wingspan:
50 feet
Lenght:
85 feet 6 inches
Height:
21 feet 3 inches
Weight (empty)
43 960 pounds
Weight (max take-off)
62 430 pounds
Cruising speed:
701 mph (Mach 1.06)
Max speed:
1 312 mph (Mach 1.98)
Climbing speed(0 to 50 000 feet)
4 minutes 24 seconds
Operating ceiling:
58 500 feet
Interception ceiling:
75 000 feet
Powerplants:
2 x Pratt Withney J-75 rated at 23 450 pounds each
 
 
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CHARACTERISTICS
ARROW 1 and ARROW 2
Air. - Foil section - Inner wing profile - Outer wing profile
Camber
Incidence - At root
- At construction tip Anhedral of chord plane Aspect'ratio
Taper ratio
Thickness ratio - parallel to Ch, Sweepback at 25% chord
of aircraft
NACA - 0003. 5-6-3. 7 (Modified) NACA - 0003.5-6-3.7 (Modified)
NACA - 0003. 8-6-3. 7 (Modified) .0075 (Modified)
Zero degrees Zero degrees 4.0 degrees 2.04
0.0889
3. 5 and 3. 8 55 degrees
AILERONS:
Aileron area (aft of hinge line) - Total Span
Chord (average percent of wing
chord) - Root
ELEVATORS:
Elevator area (aft of hinge line) - Total Span
Chord (average percent of wing chord)
_ Tip Vertical tail area (including rudder) Span
Chord Root Construction tip Mean aerodynamic chord Airfoil section
- Root
NACA
Aspect ratio Taper ratio Thickness ratio (parallel to aircraft
datum) Rudder area (aft of hinge line)
Rudder - Span (average)
- Chord (average percent vertical fin chord)
SPEED BRAKES:
Speed brake area (2) - Projected Span (each)
Chord
66. 55 sq ft 10 ft 0.0 in 25. 735
35. 0
106. 90 sq ft 10 ft 2. 0 in 14. 109 25.735
158. 79 sq ft 12 ft 10. 5 in 19 ft 0. 0 in., 5 ft 8. 0 in
13 ft 6.41 in 0004-6-3. 7 ( Modified)
Sweep Back - Leading edge59. 34 degrees
- Trailing edge 33. 08 degrees
- 1/4 chord 55. 0 degrees
1.04 0.2982 4.0%
38. 17 sq ft 9 ft 11. 0 in
14. 37 sq ft 2 ft 1. 08 in 4 ft 1. 0 in
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LEADING PARTICULARS
FU EL SYSTEM Tank Capacities
TANK NO. OF CAPACITY OF TOTAL VOLUME OF
NO. TANKS EACH TANK USABLE FUEL
1 Fuselage 1 308 imp 370 US gal 263 imp 316 US gal
2 Fuselage 1 307 imp 371 US gal 259 imp 311 US gal
3 Wing 2 165 imp 198 US gal 302 imp 362 US gal
4 Wing 2 101 imp 121 US gal 180 imp 216 US gal
5 Collector 170 imp 204 US gal 292 imp 350 US gal
6 Wing 176 imp 211 US gal 308 imp 370 US gal
7 Wing 2 322 imp 386 US gal 558 imp 670 US gal
8 Wing 2 207 imp 248 US gal 346 imp 415 US gal
TOTAL FUEL CAPACITY 2, 508 imp 3,010 US gal 19,562 lb.
Tank Pressure - Wings 25 psia (initial flights 1st aircraft)
19 psia (subsequently)
- Fuselage 10 psi differential (initial flights 1st aircraft)
7. 5 psi differential (subsequently)
Pressure Refuelling One point in each wing
ENGINES
Designation Pratt and Whitney J75 P3 (1st aircraft)
J75 P5 (subsequently)
Twin spool axial flow gas turbine with
afterburner
Fuel specification 3GP-22B-1 Ref 34A/159
MIL-F-5624 Grade JP4 CU. S. )
D. Eng R. D. 2486 (U.K.)
F. 40 (NATO Symbol)
Oil specification MIL-L-7808C Ref 34A/226
C-148 (NATO Symbol)
Oil tank capacity 5. 5 gal U.S.
Usable Oil 3. 5 gal U. S.
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ACCESSORIES GEARBOX
Manufacturer Sargeant Engineering
Accessories gearbox to engine ratio 0. 823:1
Engine starter to engine ratio 0. 823:1
Oil specification As for engines
Gearbox oil capacity 1 gal. imp
MAIN LANDING GEAR
. Type
Manufacturer and model
Track
Shock absorber Fluid specification Recuperator
Whe e is Tires < Inflation pressure Brakes
Hydraulically retracted with twin wheels in tandem
Dowty - XV 1283-1A LH XV 1283-1B RH 25 feet 9 inches static
25 feet 7. 6 inches touchdown
Dowty liquid spring with recuperator Dowcan 200 silicone fluid
Dowty - V 1283-6A LH V 1283-6B RH Goodyear
Goodyear 29 x 7.7 Type VII tubeless 255 psi
Goodyear hydraulically operated
NOSE LANDING GEAR
Type
Manufacturer and model Shock absorber
Fluid specification Wheels
Tires
Inflation pressure
Hydraulically retracted, steerable twin wheeled unit
Jarry Hydraulics 1500 Dowty liquid spring Dowcan 200 silicon
fluid Dunlop
Dunlop 18 x 5. 5 Type VII tubeless 170 psi
UTILITY HYDRAULICS
Fluid specification
Pumps (2)
Pressure regulator setting Reduced pressure Accumulators System
(1)
Emergency brakes (2) Return surge damping Compensator (1)
Compensator capacity Emergency Nitrogen System Manufacturer
Charging pressure Bottle capacity (1)
3GP-26A Ref 34A/ 100 MIL-H-5606A (U.S.) D.T.D. 585 (U.K.) H-515
(NATO Symbol) Vickers constant delivery 4200-4250 psi
1500 psi 200 cu. in. 110 cu. in. 60 cu. in. Loud
5 gal. imp.
Walter Kidde 5000 ps i
300 cu. in.
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FLYING CONTROL HYDRAULICS
Fluid specification Pumps (2 each system) Pump pressure Reduced
pressure Accumulators System (1 each system) Return surge damping
(1 each system) Booster circuit
(1 each system) Compensators (1 each system) Compensator capacity
As for utility hydraulics Vickers variable delivery 4000 psi
1250 psi
Self displacing 100 cu. in. 60 cu. in.
25 cu. in.
Loud dual pressurized 5 gal. imp.
EJECTION SEATS - 2
Liquid oxygen converter (1) Converter capacity Regulators (2)
Supply pressure to regulators Emergency Oxygen System Bottles
(?.) gaseous
Bottle capacity Charging pressure
Aro Equipment Corp. 5.0 litres
Firewell F 2400 - 11C 70 psi
Walter Kidde 50 cu. in. 1800 psi
FIRE EXTINGUISHER SYSTEM
Bottles (2) Extinguishant Capacity of each bottle Nitrogen pressure
Walter Kidde Freon 12B2 12 lb
400 psi at 70 OF
ENGINE DE-ICING
Type
AIRFRAME DE-ICING
Hot air bleed from compressor
Pilot's windshield and side panels Engine intake and ramp
Electro-thermal Electro-thermal
ELECTRICAL SYSTEM AC
Constant speed unit Alternators
General Electric Lucas Rotax
115/200 volts AC. 400 cycles 3 phase
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7f1I-I314-1
interconnected by frames and covered by an upper and a lower
skin. Each speed brake is pivoted independently at the forward
end on two hinge pins and is actuated by a jack enclosed in a
sealed compartment in the duct bay. See fig 13.
53 The forward faces of the two floating duct sections are connected
to the ducts in the centre fuselage by flexible joints which
are sealed by rubber 'O'-rings. The aft end of each duct is supported
by two IV' struts from the inner wing and is located laterally
by a turnbuckle from the structure. The joint between the aft
end of the duct and the engine tunnel is sealed by a sheet rubber
seal.
54 Twenty-four gills, spring-loaded tothe open position are
fitted to the inside of each duct in line with the engine adaptor
ring. See fig 14. For operation of the cooling gills see Arfow
1 Service Data - Engine Installation.
IG. 13 SPEED BRAKE ATTACHMENT
and a IV' support , strut at station 538.77. It is attached
to the centre fuselage bulkhead at station 485 and the engine
bay frame at station 591. 65. The bay houses two floating sections
of the engine air intake ducts and two speed brakes. It consists
of a main frame, four longerons and twenty intermediate frames >> red
by an outer skin.
50 The upper longe rons connect with the lower longerons of
the centre: fuselage and terminate at the main frame at silation
5313.77: The two lower longerons are connected to bulkhead 485
at the instrument pack rear attachment points and extend the
full length of the duct bay to connect with the engine bay main
frame at station 591.65.
51 Two longitudinal beams, inboard of the speed brakes connect
the bulkhead at station 485 to the main frame at station 538.
77 and form the main members for the speed brake inboard hinges
and the speed brake actuating jack r-tachments. The support hinges
securing the ~_~t bay to the inner wing are sealed by a stain=
less steel seal.
GILL SPRING TUNNEL FAIRING ENGINE TUNNEL
FLOATING DUCT
FLEXIBLE SEAL-DUCT TO TUNNEL
HEAT EXCHANGER AIR OUTLET
TIII-1313-1
5Z Each speed brake.eonsistr of two beams,
FIG. 14 ENGINE BAY COOLING GILLS
 
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