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:

  1. Enter the ambient temperature at (A) and proceed up to curve at (B).

  2. Cross over to appropriate value of parameter at (C).

  3. 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

Home Up Description Normal Procedures Emergency Procedures Auxiliary Equipment Operating Limitations Flight Characteristics Systems Operation Crew Duties All Weather Ops Performance Data

 


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