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Pilot`s Notes Wellington Pilot`s Notes

WELLINGTON III, X, XI, XII, XIII AND XIV

PILOT'S NOTES

January 1944.

(iii) Hercules VI, XVI and XVII fuel consumptions:

(a) The approximate total consumptions in RICH mixture art as follows:

Boost

lb./sq.in    R.p.m.    Galls./hr.

+8    2,900    320

+6    2,4OO    239

(b) The approximate total consumptions (galls./hr.) in WEAK mixture are as follows:

M ratio at 5,000 ft.
Boost lb/sq.in. 2,400 R.p.m. 2,200 R.p.m 2,000 R.p.m 1,800 R.p.m
+2 118 110 102 94
0 106 98 92 80
-2 94 88 82 74
-4 84 80 74 68
S ratio at 15,000 ft.
Boost lb/sq.in. 2,400 R.p.m. 2,200 R.p.m 2,000 R.p.m 1,800 R.p.m
+2 116 110 106 96
0 104 100 96 88
-2 94 90 86 80
-4 86 82 78 -

For every 1,000 ft. above heights quoted add ½ gall./hr.

For every 1,000 ft. below theights quoted deduct ½ gall./hr.

• For Hercules XVII engines these figures should be increased by five.

61. Static vent speeds

The following table shows the various handling speeds in m.p.h. and equivalent knots for aircraft with the A.S.I, connected to the static vent:

  M.p.h. Knots
Take-off speed (minimum) 95 85
Safety speed—no flaps 135 120
Safety speed—200 fla 125 110
Climbing speed (initial 140 145
Flying at low airspeeds (200 flap) 135 120
Stalling speeds:
At 28,500 1b.—all up 85-90 75-80
At 28,500 Ib.—all down 70-80 60-705
At 34,500 1b.—all up 95-100 85-90
At 34,500 Ib.—all down 80-90 70-80
Circuit speeds:
Before lowering flaps 150 130
After lowering flaps 130 115
Approach speeds:
At 26,000 1b.—engine assisted 95 85
At 26,000 Ib.—glide 110 95
At 26,000 lb.—flapless-engine assisted 115 100
At 29,000 Ib.—engine assisted 100 90
At 29,000 Ib.—glide 115 100
At 29,000 lb.—flapless-engine assisted 120 105
Mislanding 100 90
Beam approach - initial 140 120
Beam approach - final 110-115 95-100
Maximum speeds:
Diving 310 270
Leight light lowered 230 200
Undercarriage down 150 130
Flaps down to Т.О. position 150 130
Flaps fully down 130 115
Landing lamp lowered 110 95
Economical flying:
Climbing 140 125
Climbing 140 125
Cruising (Medium and high altitudes)
Fully loaded 160 140
Lightly loaded 150 130
Cruising (Low altitudes)
Max. range 165 145
Max. endurance 150-155 130-135
Engine failure during take-off 125 110
Single engine flight 130-135 115-120
Fuel jettisoning:
Flaps up 110 95
Flaps down 20° 135 120
Flaps fully down 90 80

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