Characteristics of the Example Helicopter

Our heavyweight helicopter equal in the world does not have

In Rostov started production of the most load-lifting rotary-wing car The Russian holding «Helicopt[...]

The old plane — nonsense, pilots think - there was an attack

In spite of the fact that the main version of crash of the Russian plane of the Kogalymavia company [...]

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

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.

Fuselage Station

FIGURE A.1 Example Helicopter

FIGURE A.4 Fuselage Lateral-Directional Aerodynamic Characteristics

Helicopters & Aircrafts

Helicopters & Aircrafts

Helicopters & Aircrafts

Helicopters & Aircrafts

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