Characteristics of the Example Helicopter

Design gross weight, G. W. Minimum operating weight Power plants Fuel tank capacity Parasite drag area, /

Vertical drag ratio, Dv/G. W.

Main Kotor Radius, R Disc area, A Tip speed, flR Chord, c No. of blades, b Solidity, a Blade area, Ah Airfoil Twist, 0г

Blade cutout ratio, xQ Hinge offset ratio, f/R Blade-flapping inertia, ly Lock no., у

Polar moment of inertia, J Shaft incidence, /

Height above C. G., hM

Tail Rotor

Radius, RT

6.5 ft.

Disc area, AT

133 ft2

Tip speed, CIRT

650 ft/sec

Chord, cT

1 ft

No. of blades, bT

3

Solidity, or

0.146

Blade area, Ab

19.4 ft2

UJ-

Airfoil

NACA 0012

Twist, 0lT

-5°

Lock no., yT

4

Polar moment of inertia, JT

25 slug ft2

Tail rotor moment arm, lT

37 ft

Distance from fin, d/R

1.5 ft

Height above C. G., hT

6 ft

Blocked area, SB

31.5 ft

Delta-three angle, 8}

1

О

о

Horizontal Stabilizer

Area, AH

18 ft2

Span, bff

9 ft

Aspect ratio, A. R.H

4.5

Taper ratio, cT/cR

.71

Sweep of mid-chord line, /гн

13°

Sweep of leading edge, ALeh

15°

Airfoil

NACA 0012

Moment arm, lH

33 ft

Height above C. G., h„

-1.5 ft

Incidence

-3°

Vertical Stabilizer

Area, Av

33 ft2

Span, bv

7.7 ft

Aspect ratio, ARy

1.8

Taper ratio, cT/cR

0.21

Sweep of mid-chord line, /2у

27°

Rudder deflection, 8r

10°

Moment arm, lv

35 ft

Height above C. G., hv

3 ft

Fuselage

Length, LF

57 ft

Width, WF

8 ft

Height, HF

10 ft

Wetted area, S^p

680 ft2

Volume, VF

4,600 ft3

Fineness ratio, F. R.f

5.2

Height above C. G., hF

.5 ft

Aircraft inertias:

Pitch

lyy = 40,000 slug ft2

Roll

іxx = 5,000 slug ft2

Yaw

Ia = 35,000 slug ft2

Miscellaneous:

Landing gear vertical design velocity = 15 ft/sec Effective transmission inertia (referenced to rotor rpm)

= 20 slug ft2

Power plant:

Engine rpm

20,000

Main rotor transmission rating

4000 h. p.

Tail rotor transmission rating

800 h. p.

Total engine nacelle wetted area

94 ft2

Ml L-STD-1374 PART l-TAB GROUP WEIGHT STATEMENT PAGE MO

NAME WEIGHT EMPTY MODEL

DATE REPORT

COMPONENT GROUP

1

WING GROUP

0

2

BASIC STRUCTURE – CENTER SECTION

3

– INTERMEDIATE PAN

EL

4

-OUTER PANEL

5

-GLOVE

6

SECONDARY STRUCTURE – INCL. WING F«

ILD WEIGHT

LBS.

7

AILERONS – INCL. BALANCE WEIGHT

LBS.

8

FLAPS-TRAILING EDGE

9

– LEADING EDGE

10

SLATS

11

SPOILERS

12

13

14

ROTOR GROUP

1466

15

BLADE ASSEMBLY

830

16

HUB & HINGE – INCL. BLAOE FOLD WEIGH

T

LBS.

636

17

18

19

TAIL GROUP

281

20

STRUCT.-STABILIZER (INCL

LB!

.SEC. STRUCT

.)

37

21

– FIN – INCL DORSAL (INCL

LBS. SEC.

STRUCT.)

63

22

VENTRAL

23

ELEVATOR – INCL. BALANCE WEIGHT

LBS.

24

RUDDERS – INCL BALANCE WEIGHT

LBS.

25

TAIL ROTOR – BLADES

181

26

– HUB & HINGE

27

28

BODY GROUP

1801

29

SASrC STRUCTURE — FUSELAGE OR HULL|

30

-BOOMS 1

31

SECONDARY STRUCTURE – FUSELAGE OR HULL

32

-BOOMS f

33

-SPEED BRAKES

34

– DOORS. RAMF

S, PANELS & N

ISC.

35

36

371

ALIGHTING GEAR GROUP-TYPE**

539

36

LOCATION

RUNNING

•STRUCT.

CONTROLS

39

MAIN

40

NOSE/TAIL

41

ARRESTING GEAR

42

CATAPULTING GEAR

43

44

45

ENGINE SECTION OR NACELLE GROUP

207

46

BODY – INTERNAL

47

-EXTERNAL

48

WING – INBOARO

49

– OUTBOARD

50

51

AIR INDUCTION GROUP

0

52

-DUCTS

53

– RAMPS, PLUGS, SPIKES

54

– DOORS, PANELS & MISC.

55

56

57

TOTAL STRUCTURE

4294

• CHANGE TO FLOATS ANO STRUTS FOR WATER TYPE GEAR,

—LANOING GEAR "TYPE”: INSERT TRICYCLE”. TAIL WHEEL”. "BICYCLE", "QUAORICYCLE”. OR SIMILAR

M«c-STO-i3T4 DESCRIPTIVE NOMENCLATURE.

86

AUXILIARY POWER PLANT GROUP

150

87

INSTRUMENTS GROUP

172

88

HYDRAULIC & PNEUMATIC GROUP

88

89

90

ELECTRICAL GROUP

548

91

92

AVIONICS GROUP

400

93

EQUIPMENT

94

INSTALLATION

95

L

96

ARMAMENT GROUP (INCL. PASSIVE PROT.

LBS

)

0

97

FURNISHINGS & EQUIPMENT GROUP

1130

98

ACCOMMODATION FOR PERSONNEL

99

MISCELLANEOUS EQUIPMENT

100

FURNISHINGS

101

EMERGENCY EQUIPMENT

102

103

AIR CONDITIONING GROUP

160

104

ANTI-ICING GROUP

105

106

PHOTOGRAPHIC GROUP

0

107

LOAD & HANOLING GROUP

0

108

AIRCRAFT HANOLING

109

LOADING HANOLING

110

BALLAST

111

MANUFACTURING VARIATION

80

112

TOTAL CONTRACTOR CONTROLLED

113

TOTAL GFAE

114

TOTAL WEIGHT EMPTY – PG 2-3

10000

MIL-STO-1374

З

MIL-STD-1374 PART I-TAB

NAME

DATE

115

[load санатаы

1

/

/ NORMAL

/ FERRY

/

/ _!

116

117

CREW (NO. 2 )

360

360

118

PASSENGERS (NO. 30 )

5100

119

FUEL LOCATION TYPE

GALS.

120

UNUSABLE FUSE JP-4

4.6

(6.5 Ib/gal)

30

30

121

INTERNAL FWD JP-4

228.5

1485

1485

122

AFT JP-4

228.5

1485

1485

123

CABIN JP-4

740

4809

124

125

EXTERNAL (FERRY)

1259

8182 –

126

127

123

OIL

129

TRAPPED

130

ENGINE

40

131

132

FUEL TANKS (LOCATION )

133

WATER INJECTION FLUID (

gal:

>.)

134

135

BAGGAGE

1500

136

CARGO

137

138

GUN INSTALLATIONS

139

GUNS LOCAT. FIX. OR FLEX. QUANTITY C>

tLIBER

140

141

142

AMMO.

143

144

145

SUPPTS*

146

WEAPONS INSTALL.**

147

148

149

150

151

152

153

154

155

156

157

158

159

CABIN TANK

481

160

161

EXTERNAL TANKS

818

162

SURVIVAL KITS

100

163

LIFE RAFTS

50

164

OXYGEN

200

165

MtSC.

166

167

168

169

TOTAL USEFUL LOAD

10000

18000

170

WEIGHT EMPTY 10000 10000

171

GROSS WEIGHT 20000 28000

* IF REMOVABLE AND SPECIFIED AS USEFUL LOAD.

•*LIST STORES. MISSILES. SONOBUOYS. ETC.. FOLLOWED BY RACKS. LAUNCHERS. CHUTES. ETC., THAT ARE NOT PART OF mil-STD-1374 WEIGHT EMPTY. LIST IDENTIFICATION. LOCATION. AND QUANTITY FOR ALL ITEMS SHOWN INCLUDING INSTALLATION.

os

^1

^1

Fuselage Station

FIGURE A.1 Example Helicopter

FIGURE A.4 Fuselage Lateral-Directional Aerodynamic Character­istics

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