Performance Data

List of Illustrations
	Figure	Subject
	A-1	Altitude vs. Range
	A-2	Airspeed Calibration
	A-3	Fuel Consumption and Endurance
	A-4	Horsepower Required and Available vs. Airspeed
	A-5	Vertical Rate of Climb
	A-6	Exhaust Gas vs. Ambient Temperature
	A-7	Weapon Drop Envelope, Mark 44 Mod 0 Torpedo
	A-8	Weapon Drop Envelope, Mark 46 Mod 0 Torpedo


Altitude vs. Range Figure A-1
DISTANCE TO THE HORIZON
Date: 2 February 1966						DATA BASIS: H.O. Pub No. 9 (1958)
HGT, Ft	NAUT Miles	STAT Miles	HGT Ft	NAUT Miles	STAT Miles	HGT, Ft	NAUT Miles	STAT Miles	HGT, Ft	NAUT Miles	STAT Miles
5 10 15 20 25 30 35 40 45 50 55 60 65 70 75 80 85	2.6 3.6 4.4 5.1 5.7 6.3 6.8 7.2 7.7 8.1 8.5 8.9 9.2 9.6 9.9 10.2 10.5	2.9 4.2 5.1 5.9 6.6 7.2 7.8 8.3 8.8 9.3 9.8 10.2 10.6 11.0 11.4 11.8 12.1	90 95 100 110 120 130 140 150 170 180 190 200 220 240 260 280 300	10.9 11.2 11.4 12.0 12.5 13.0 13.5 14.0 14.9 15.3 15.8 16.2 17.0 17.7 18.4 19.1 19.8	12.5 12.8 13.2 13.8 14.4 15.0 15.6 16.1 17.2 17.7 18.2 18.6 19.5 20.4 21.2 22.0 22.8	320 340 360 380 400 420 440 460 480 500 540 560 580 600 620 640 660	20.5 21.1 21.7 22.3 22.9 23.4 24.0 24.5 25.1 25.6 26.6 27.1 27.6 28.0 28.5 28.9 29.4	23.6 24.3 25.0 25.7 26.3 27.0 27.6 28.2 28.9 29.4 30.6 31.2 31.7 32.3 32.8 33.3 33.8	680 700 720 740 760 780 800 820 840 860 880 900 920 940 960 980 1000	29.8 30.3 30.7 31.1 31.5 31.9 32.4 32.8 33.2 33.5 33.9 34.3 34.7 35.1 35.4 35.8 36.2	34.3 34.8 35.3 35.8 36.3 36.8 37.3 37.7 38.2 38.6 39.1 39.5 39.9 40.4 40.8 41.2 41.6
Figure A-1 Altitude vs. Range
IF: Height of antenna = 75 feet Distance from destroyer to target = 23 Nautical Miles
THEN: Distance from antenna to horizon (from above Table) = 9.9 Nautical Miles (NMI) Distance from horizon to target (23 NMI - 9.9 NMI) = 13.1 NMI Drone altitude to maintain line of sight (interpolated from Table) = 132 feet*
*Note No compensation is shown for radio wave refraction which varies with local ambient atmospheric conditions.


Airspeed Calibration Figure A-2
MODEL: QH-50D		ENGINE: T50-BO-10 or -12
DATE: 15 OCTOBER 1965		FUEL GRADE: JP-5
DATA BASIS: FLIGHT TEST		FUEL DENSITY: 6.8 LB/GAL
FORWARD TRUE AIRSPEED vs. COMMAND READOUT
TO OBTAIN FORWARD TRUE AIRSPEED OF KNOTS	COMMAND READOUT (FWD) MUST BE:
	NO WEAPON	ONE WEAPON (Mark 44)	TWO WEAPONS (Mark 44)
20 30 40 50 60 70 80	21 27 35 44 54 65 78	18 24 31 40 49 60 71	15 22 29 38 48 59 70
Airspeed calibration data for the Mark 46 weapon store will be supplied when available.


Fuel Consumption and Endurance Figure A-3
MODEL: QH-50D			ENGINE: T50-BO-10 or -12
DATE: 5 MAY 1966			FUEL GRADE: JP-5
DATA BASIS: FLIGHT TEST			FUEL DENSITY: 6.8 LB/GAL
Typical Weapon Load-Out
WEAPONS	PARAMETER	HOVER		MAXIMUM RANGE	MAXIMUM ENDURANCE
TWO Mark 44 Torpedoes (2340 LB)	TRUE AIRSPEED, KNOTS	0		80 (Vmax)	55
	AVG FUEL CONSUMPTION, LB/HR	223		205	182
	ENDURANCE, HOURS*	1.40		1.53	1.72
NONE (1474 LB)	TRUE AIRSPEED, KNOTS	0		80 (Vmax)	50
	AVG FUEL CONSUMPTION, LB/HR	177		182	163
	ENDURANCE, HOURS*	1.77		1.72	1.92
* With fuel reserve of 10% of initial full fuel load. NOTE: Fuel consumption and endurance data for the Mark 46 weapon store will be supplied when available


Horsepower Required and Available vs. Airspeed Figure A-4
MODEL: QH-50D	ENGINE: T50-BO-10 or -12
DATE: 30 AUGUST 1966	FUEL GRADE: JP-5
DATA BASIS: FLIGHT TEST	FUEL DENSITY: 6.8 LB/GAL

Note: Horsepower data for the Mark 46 weapon store will be supplied when available!


Vertical Rate of Climb for Various Gross Weight, Ambient Temperature, and Barometric Pressure Conditions (Zero Airspeed) Figure A-5
MODEL: QH-50D	ENGINE: T50-BO-10 or -12
DATE: 17 MAY 1967	FUEL GRADE: JP-5
DATA BASIS: FLIGHT TEST	FUEL DENSITY: 6.8 LB/GAL

Instructions: Enter the ambient temperature at (A) and proceed up to curve at (B). Cross over to appropriate value of parameter at (C). Drop down to obtain vertical rate of climb at (D). NOTE: Chart shows vertical rate of climb under conditions of zero translational velocity with respect to the air mass, based on nominal available power (300 shp at 90 degree F, 330 shp at 59 degree F) and 610 rotor rpm.


Exhaust Gas vs. Ambient Temperature (T50-BO-12 Engine or T50-BO-10 with Bleed Valve Active) Figure A-6
MODEL: QH-50D	ENGINE: T50-BO-12 or -10 (with Bleed Valve Active)
DATE: 30 AUGUST 1966	FUEL GRADE: JP-5
DATA BASIS: FLIGHT TEST	FUEL DENSITY: 6.8 LB/GAL

Weapon Drop Envelope,
Mark 44 Mod 0 Torpedo
Figure A-7

MODEL: QH-50D

DATE: 2 FEBRUARY 1966

DATA BASIS: NATU TM No. 176

WEAPON DROP ENVELOPE is for:
MARK 44 TORPEDO with MARK 24 Mod 2 AIR STABILIZER

CAUTION:

Entire envelope shown above may be used when drone is within visual range of controller. When drone is beyond visual range of controller, a minimum commanded altitude of 300 feet must be maintained.

Weapon Drop Envelope,
Mark 46 Mod 0 Torpedo
Figure A-8

MODEL: QH-50D

DATE: 2 FEBRUARY 1966

DATA BASIS: NAVWEPS OP 1207

WEAPON DROP ENVELOPE is for:
MARK 46 TORPEDO with MARK 31 Mod 0 AIR STABILIZER

CAUTION:

Entire envelope shown above may be used when drone is within visual range of controller. When drone is beyond visual range of controller, a minimum commanded altitude of 300 feet must be maintained.

End of Appendix Section

Performance Data

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List of Illustrations

Figure

Subject

A-1

Altitude vs. Range

A-2

Airspeed Calibration

A-3

Fuel Consumption and Endurance

A-4

Horsepower Required and Available vs. Airspeed

A-5

Vertical Rate of Climb

A-6

Exhaust Gas vs. Ambient Temperature

A-7

Weapon Drop Envelope, Mark 44 Mod 0 Torpedo

A-8

Weapon Drop Envelope, Mark 46 Mod 0 Torpedo

Altitude vs. Range Figure A-1

DISTANCE TO THE HORIZON

Date: 2 February 1966

DATA BASIS: H.O. Pub No. 9 (1958)

HGT, Ft

NAUT Miles

STAT Miles

HGT Ft

NAUT Miles

STAT Miles

HGT, Ft

NAUT Miles

STAT Miles

HGT, Ft

NAUT Miles

STAT Miles

Figure A-1 Altitude vs. Range

IF: Height of antenna = 75 feet Distance from destroyer to target = 23 Nautical Miles

THEN: Distance from antenna to horizon (from above Table) = 9.9 Nautical Miles (NMI) Distance from horizon to target (23 NMI - 9.9 NMI) = 13.1 NMI

Drone altitude to maintain line of sight (interpolated from Table) = 132 feet*

*Note No compensation is shown for radio wave refraction which varies with local ambient atmospheric conditions.

Airspeed Calibration Figure A-2

MODEL: QH-50D

ENGINE: T50-BO-10 or -12

DATE: 15 OCTOBER 1965

FUEL GRADE: JP-5

DATA BASIS: FLIGHT TEST

FUEL DENSITY: 6.8 LB/GAL

FORWARD TRUE AIRSPEED vs. COMMAND READOUT

TO OBTAIN FORWARD TRUE AIRSPEED OF KNOTS

COMMAND READOUT (FWD) MUST BE:

NO WEAPON

ONE WEAPON (Mark 44)

TWO WEAPONS (Mark 44)

20

30

40

50

60

70

80

21

27

35

44

54

65

78

18

24

31

40

49

60

71

15

22

29

38

48

59

Altitude vs. Range
Figure A-1

HGT,
Ft

NAUT
Miles

STAT
Miles

HGT
Ft

NAUT
Miles

STAT
Miles

HGT,
Ft

NAUT
Miles

STAT
Miles

HGT,
Ft

NAUT
Miles

STAT
Miles

IF:
Height of antenna = 75 feet
Distance from destroyer to target = 23 Nautical Miles

THEN:

Distance from antenna to horizon (from above Table) = 9.9 Nautical Miles (NMI)
Distance from horizon to target (23 NMI - 9.9 NMI) = 13.1 NMI

*Note
No compensation is shown for radio wave refraction which varies with local ambient atmospheric conditions.

Airspeed Calibration
Figure A-2

TO OBTAIN
FORWARD TRUE
AIRSPEED OF KNOTS

COMMAND READOUT
(FWD) MUST BE:

NO
WEAPON

ONE
WEAPON
(Mark 44)

TWO
WEAPONS
(Mark 44)

Fuel Consumption and Endurance
Figure A-3

MAXIMUM
RANGE

MAXIMUM
ENDURANCE

TWO Mark 44
Torpedoes
(2340 LB)

NONE
(1474 LB)

Horsepower Required and Available vs. Airspeed
Figure A-4

Vertical Rate of Climb for Various Gross Weight, Ambient Temperature, and Barometric Pressure Conditions
(Zero Airspeed)
Figure A-5

Exhaust Gas vs. Ambient Temperature
(T50-BO-12 Engine or T50-BO-10 with Bleed Valve Active)
Figure A-6

ENGINE: T50-BO-12 or -10
(with Bleed Valve Active)