Content .. 76 77 78 79 ..

F16C/D. FLIGHT MANUAL (2002) - page 78

T.O. GR1F16CJ11

B880Change 3

1F-16CJ-1-1-4098A

0.8

1.0

0.2

0.4

0.6

MACH NUMBER

TURN RA

TE DEGREES/SECOND

1.2

TIGHTEST TURN

(RADIUS =

3095 FEET)

MAXIMUM AIRSPEED

QUICKEST TURN

(15.2 DEGREES/SECOND)

Turn Performance 20,000 Feet

DATA BASIS FLIGHT TEST

CONFIGURATION:

CONDITIONS:

ENGINE F110-GE-129

STANDARD DAY

MAX AB

NOTE: REFER TO SECTION V FOR AIRSPEED LIMITATIONS.

DRAG INDEX = 200

GW = 28,000 POUNDS

-4

-2

TURN RA

(DEGREES/SECOND)

GW 1000 POUNDS

GW EFFECT

TURN RA

(DEGREES/SECOND)

TEMP DEV FROM

STD DAY C

TEMPERATURE EFFECT

1.1

1.0

0.9

TURN RADIUS F

ACTOR

RADIUS TEMP EFFECT

TEMP DEV FROM STD DAY C

-20

-10

1.4

3
2

-1

-2
-3

-20

-10

Figure B863.

T.O. GR1F16CJ11

Change 3B881

1F-16CJ-1-1-4105X

0.8

1.0

0.0

0.2

0.4

0.6

MACH NUMBER

TURN RA

TE DEGREES/SECOND

1.2

TIGHTEST TURN

(RADIUS =

4570 FEET)

MAXIMUM AIRSPEED

QUICKEST TURN

(11.9 DEGREES/SECOND)

-4

-2

TURN RA

(DEGREES/SECOND)

GW 1000 POUNDS

GW EFFECT

TURN RA

(DEGREES/SECOND)

TEMP DEV FROM

STD DAY C

TEMPERATURE EFFECT

1.1

1.0

0.9

TURN RADIUS F

ACTOR

RADIUS TEMP EFFECT

TEMP DEV FROM STD DAY C

-20

-10

Turn Performance 30,000 Feet

DATA BASIS FLIGHT TEST

CONFIGURATION:

CONDITIONS:

ENGINE F110-GE-129

STANDARD DAY

MAX AB

NOTE: REFER TO SECTION V FOR AIRSPEED LIMITATIONS.

DRAG INDEX = 200

GW = 28,000 POUNDS

1.4

3
2

-1

-2
-3

-20

-10

MAX AFT

STICK

Figure B864.

T.O. GR1F16CJ11

B882Change 3

1F-16CJ-1-1-4099A

INITIAL MACH NUMBER

GW 1000 POUNDS

TIME MINUTES

DIST

ANCE NM

0.6

0.8

1.0

1.2

1.4

1.6

BASELINE

120

FUEL USED POUNDS

0.5

1.0

1.5

2.0

2.5

3.0

0.6

0.8

1.0

1.2

1.4

1.6

0.6

0.8

1.0

1.2

1.4

1.6

BASELINE

Deceleration 20,000 Feet

DATA BASIS FLIGHT TEST

IDLE

WINGS LEVEL
STANDARD DAY

ENGINE F110-GE-129

CONDITIONS:

160

Figure B865.(Sheet 1)

T.O. GR1F16CJ11

Change 3B883

0.9

1.1

1.3

1.5

1.7

0.5

1.0

1.5

2.0

2.5

3.0

BASELINE

0.9

1.1

1.3

1.5

1.7

0.9

1.1

1.3

1.5

1.7

120

BASELINE

INITIAL MACH NUMBER

GW 1000 POUNDS

TIME MINUTES

DIST

ANCE NM

FUEL USED POUNDS

1F-16CJ-1-1-4100A

Deceleration 30,000 Feet

DATA BASIS FLIGHT TEST

IDLE

WINGS LEVEL

STANDARD DAY

ENGINE F110-GE-129

CONDITIONS:

3.5

160

0.7

Figure B865.(Sheet 2)

T.O. GR1F16CJ11

B884Change 3

0.8

1.0

1.2

1.4

1.6

1.8

0.5

1.0

1.5

2.0

2.5

3.0

BASELINE

0.8

1.0

1.2

1.4

1.6

1.8

0.8

1.0

1.2

1.4

1.6

1.8

120

BASELINE

INITIAL MACH NUMBER

GW 1000 POUNDS

TIME MINUTES

DIST

ANCE NM

FUEL USED POUNDS

1F-16CJ-1-1-4101A

Deceleration 40,000 Feet

DATA BASIS FLIGHT TEST

IDLE

WINGS LEVEL

STANDARD DAY

ENGINE F110-GE-129

CONDITIONS:

3.5

160

Figure B865.(Sheet 3)

T.O. GR1F16CJ11

Change 7B91/(B92 blank)

PART 9 - MISSION PLANNING

Refer to Appendix A. Part 9 - Mission Planning

All data on pages B92 thru B918, including

Figures B91 thru B913, deleted.

T.O. GR1F16CJ11

Change 7C11

APPENDIX C

F100PW229 With Conformal Fuel Tanks

PERFORMANCE DATA

Part 1-Introduction

C11

. . . . . . . . . . . . . . . . . . . . . . .

Part 2-Takeoff

C21

. . . . . . . . . . . . . . . . . . . . . . . . . . . .

Part 3-Climb

C31

. . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Part 4-Cruise

C41

. . . . . . . . . . . . . . . . . . . . . . . . . . . .

Part 5-Endurance

C51

. . . . . . . . . . . . . . . . . . . . . . . .

Part 6-Descent

C61

. . . . . . . . . . . . . . . . . . . . . . . . . . .

Part 7-Landing

C71

. . . . . . . . . . . . . . . . . . . . . . . . . . .

Part 8-Combat

C81

. . . . . . . . . . . . . . . . . . . . . . . . . . .

Part 9-Mission Planning

C91

. . . . . . . . . . . . . . . . . .

PART 1-INTRODUCTION

TABLE OF CONTENTS

Page

Introduction

C11

. . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Drag Index and Configuration

Weight

C12

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Position Error Correction

C13

. . . . . . . . . . . . . . . . . .

Airspeed Conversion

C14

. . . . . . . . . . . . . . . . . . . . . .

Compressibility Correction to

Airspeed

C14

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Miscellaneous Charts

C14

. . . . . . . . . . . . . . . . . . . . .

Angle of Attack (AOA)

C14

. . . . . . . . . . . . . . . . . . . .

Available Load Factor

C15

. . . . . . . . . . . . . . . . . . . . .

Turn Conversion

C15

. . . . . . . . . . . . . . . . . . . . . . . . .

Ground Vehicle Friction

ReadingToRCR Conversion

C15

. . . . . . . . . . . .

LIST OF CHARTS

Figure

Page

Drag Indexes and Weights-

Basic Aircraft

C11

C16

. . . . . . . . . . .

. . . .

Drag Indexes and Weights

Suspension Equipment

C11

C17

. . .

. . . .

Drag Indexes and Weights-

Individual Stores

C11

C18

. . . . . . . .

. . . .

Position Error Correction-

Airspeed and Altitude

C12

C113

. . .

. . . .

Position Error Correction-

Mach Number

C12

C114

. . . . . . . . . .

. . . .

Airspeed Conversion

C13

C115

. . . . . . .

. . . .

Compressibility Correction

to Airspeed

C14

C117

. . . . . . . . . . . . .

. . . .

Figure

Page

Standard Atmosphere

C15

C118

. . . . . .

. . . .

Temperature Correction

for Compressibility

C16

C120

. . . . . .

. . . .

Angle of Attack

C17

C121

. . . . . . . . . . . .

. . . .

Available Load Factor

C18

C122

. . . . . .

. . . .

Turn Conversion

C19

C123

. . . . . . . . . .

. . . .

Ground Vehicle Friction

ReadingToRCR

Conversion

C110

C124

. . . . . . . . . . . . .

. . . .

INTRODUCTION

The data presented in the charts is applicable to air

craft equipped with conformal fuel tanks (CFT's)

mounted and an F100PW229 engine. All perfor

mance data is based on use of all approved fuels. The

data covers a flight spectrum ranging from sea level

to approximately 60,000 feet and 02.0 mach. No con

servative factors are used in any of the fuel consump

tion data presented herein. The appendix is divided

into nine parts with performance data presented in

an appropriate order for flight planning. The usage

of the material requires that (except Part 9) all the

text be presented first followed by all the charts.

Because of the large number of stores and stores

loading combinations the aircraft is capable of carry

ing, most charts are presented in a drag index for

mat. All charts are based on estimated F16 perfor

mance due to the incorporation of CFT's. Refusal

Speed charts in Part 2 and all charts in Part 7 are

based on predicted brake performance.

T.O. GR1F16CJ11

C12Change 8

NOTE

Limiting conditions relative to altitude,

airspeed, stores, gross weight, etc., are

presented in Section V and should be

checked prior to selecting mission

conditions. Some charts may present

data for more than permissible maxi

mun weight per Section V. Such weight

presentation does not have precedence

over the limits of Section V. All data is

based on the (1962) U.S. standard

atmosphere and the (1966) U.S. stand

ard atmosphere supplements. Pressure

altitude and true mach are used for all

data unless specified otherwise.

DRAG INDEX AND CONFIGURATION

WEIGHT

Drag index is a numerical factor which provides a

means for quantifying the effects on aircraft perform

ance of adding stores to the basic aircraft. The drag

index system provides accurate corrections for store

effects at all subsonic speeds (less than 1.0 mach). At

supersonic speeds (greater than 1.0 mach), the size

and shape of the store(s) affect drag to a significant

degree, and a single value of drag index can no longer

exactly represent all stores and combinations at these

speeds. Therefore, it should be noted that actual

supersonic performance may vary from that pre

dicted by the performance charts.

Configuration weight is intended to facilitate mission

planning by precomputing the weight of a configura

tion which is to be added to the aircraft operating

weight to obtain aircraft start engine weight. Config

uration weight is the weight of the complete configu

ration which is uploaded to the basic aircraft. The

configuration weight includes the weight of all the

stores (missiles, bombs, pods, etc.), suspension equip

ment, full external fuel tanks (if used), and ECM pod

(if used).

The drag index and configuration weight of autho

rized takeoff store loadings are presented in T.O.

GR1F16CJ12, STORES LIMITATIONS.

The drag indexes and weights of specific stores and

suspension equipment items are given in figure C11.

If the drag index and configuration weight for a spe

cific loading are not presented in T.O.

GR1F16CJ12, STORES LIMITATIONS (i.e., nor

mal downloads), figure C11 may be used to deter

mine drag index and configuration weight.

NOTE

The drag index for a specific loading

accounts for the combined effects of the

stores on drag and therefore may vary

slightly from the drag index computed

using figure C11.

Configuration weight for a specific

loading may vary slightly from the

weight computed using figure C11

due to rounding.

Aircraft start engine weight is determined by adding

aircraft operating weight, internal usable fuel, and, if

installed, ammunition, chaff/flares, and configuration

weight. All these weights are given in figure C11.

The aircraft operating weight given is an approxi

mate value and includes pilot (

2 ), oil, oxygen,

unusable fuel, and tip missile launchers. For weight

and balance information, refer to the individual air

craft Form F (DD Form 3654) and the Weight and

Balance Handbook. An example of the determination

of the drag index, configuration weight, and aircraft

start engine weight is provided in the sample problem

which follows.

REFER TO FIGURE C11.

Assume a loading of four AIM9L missiles on LAU

129/A launchers, two MK 84 bombs, and two 370gal

lon fuel tanks. The drag index and configuration

weight for this loading from T.O. GR1F16CJ12,

STORES LIMITATIONS, are 152 and 11,777 pounds,

respectively.

For this example, drag index and configuration

weight are computed as follows:

STA 1 and 9 (2 AIM9L missiles on LAU129/A

launchers)

The basic aircraft drag index includes tip missiles

on 16S210 missile launchers. The drag index is 1

for a tip missile on a LAU129/A missile launcher

and the weight of an AIM9L is 195 pounds.

For two AIM9L's on LAU129/A launchers:

Drag index = 2

1 = 2

Weight= 2

195 = 390 pounds

T.O. GR1F16CJ11

Change 7C13

STA 2 and 8 (AIM9L missiles on LAU129/A launch

ers + adapters)

One AIM9L has a drag index of 5 and weighs 195

pounds. The drag index of a LAU129/A launcher

with adapter is 6 and the weight is 113 pounds.

Since AIM9L's are carried at stations 2 and 8,

multiply each drag index and weight by 2 and

sum the results.

For two AIM9L's and LAU129/A launchers with

adapters:

Drag index = (2

5) + (2

= 22

Weight

= (2

195) + (2

113) = 616

pounds

STA 3 and 7 (MK 84 on wing weapon pylon)

The drag index of one MK 84 bomb is 9 and the

bomb weight is 1970 pounds. The drag index of a

pylon with MAU12C/A, D/A rack at station 3 or

7 is 15 and the weight is 281 pounds. Since two

MK 84 bombs are to be carried on pylons, multiply

each drag index and weight by 2 and sum the

results.

For two MK 84's on wing weapon pylons:

Drag index =(2

9) + (2

15)

= 48

Weight

=(2

1970) + (2

281) = 4502

pounds

STA 4 and 6 (370gallon fuel tanks)

In a similar manner, find that the drag index of

one 370gallon fuel tank, mounted on station 4 or

6 with single stores at 3 or 7, is 35 and its weight

is 531 pounds (empty) or 3047 pounds (full). Note

that no rack is required to install the tank on the

wing.

For two tanks:

Drag index = 2

= 70

Weight

= 2

3047

= 6094

pounds

(full)

The total store loading drag index and configuration

weight can now be determined by summing the indi

vidual store station values.

Drag Index

Configuration

Weight

STA 1 and 9

390

STA 2 and 8

616

STA 3 and 7

4,502

STA 4 and 6

6,094

Total

142

11,602

pounds

Using these values plus the basic aircraft drag index

and weights, the drag index and start engine weight

can be determined:

Drag Index

Basic aircraft drag index

Store loading drag index

= 142

Drag index total

= 149

Start Engine Weight

Aircraft operating weight

= 21,168

Internal usable fuel (JP8)

= 7,116

Conformal Fuel Tanks (JP8)

= 3,056

Ammunition (full drum)

=287

Chaff/flares (not loaded)

= 0

Configuration weight

=11,602

Total start engine weight

= 43,229

pounds

NOTE

Assumed values for basic aircraft

operating weight and drag index are

used in the sample problems through

out this appendix in order to eliminate

reworking the problems whenever the

basic operating weight or drag index

changes due to modifications. The

sample problems are aids in using the

appendix and are not necessarily

applicable to specific configurations.

POSITION ERROR CORRECTION

A single nosemounted pitotstatic probe supplies

static and total pressure information to the CADC,

altimeter, and airspeed indicator. The CADC com

putes calibrated airspeed, true airspeed, true mach,

and calibrated altitude and provides the required sig

nals to drive the airspeed and altitude indications on

the HUD.

T.O. GR1F16CJ11

C14Change 7

The CADC provides corrected (calibrated) altitude

signals to the altimeter when the altimeter is in

ELECT. When the altimeter is in PNEU, it displays

indicated (not corrected for position error) altitude.

The airspeed indicator always displays indicated air

speed and mach number. Position error corrections

are shown in figure C12.

REFER TO FIGURE C12.

Enter Position Error Correction-Airspeed and

Altitude chart with desired calibrated airspeed (A),

proceed vertically to desired pressure altitude lines

(B), then proceed horizontally to read altitude

correction (C) and airspeed correction (D). Subtract

the corrections from the desired conditions to obtain

indication reading. Mach position error corrections

may be found in a similar manner.

SAMPLE PROBLEM.

A. KCAS

= 380

B. Pressure altitude

= 30,000 feet

C. Altitude correction = 175 feet

Altimeter reading

= 30,000-175 =

29,825 feet

D. Airspeed correction = 1.5 knots

Airspeed indicator

reading

= 380-1.5 = 378.5

knots

AIRSPEED CONVERSION

Curves shown in figure C13 are presented as an aid

for conversion between calibrated airspeed, true air

speed, and mach number. Fahrenheit/Centigrade

temperature conversion is also shown.

REFER TO FIGURE C13.

To obtain mach numbers, enter Airspeed Conversion

chart with calibrated airspeed (A). Proceed vertically

to altitude (B) and horizontally left to read mach

number (C).

To obtain KTAS, enter Airspeed Conversion chart

with calibrated airspeed (A). Proceed vertically to

altitude (B), then horizontally left to temperature (D),

and then vertically upward or downward, as applica

ble, to read KTAS (E).

SAMPLE PROBLEM.

A. KCAS

= 225

B. Altitude

= 40,000 feet

C. Mach number

= 0.75

D. Temperature

= -40

E. KTAS

= 446

COMPRESSIBILITY CORRECTION

TO AIRSPEED

Figure C14 is provided as an aid to converting cali

brated airspeed into equivalent airspeed.

REFER TO FIGURE C14.

Enter Compressibility Correction to Airspeed chart

with calibrated airspeed (A), proceed vertically up

ward to altitude (B) and proceed horizontally left to

read compressibility correction (C). Note that the

chart can also be entered at (B) with mach and alti

tude. Subtract the compressibility correction from

calibrated airspeed to obtain equivalent airspeed.

SAMPLE PROBLEM.

A. KCAS

= 300

B. Altitude

= 30,000 feet

C. Compressibility

correction

= 15 knots

KEAS

= 300-15 = 285

MISCELLANEOUS CHARTS

STANDARD ATMOSPHERE, figure C15, and TEM

PERATURE CORRECTION FOR COMPRESSIBIL

ITY, figure C16, are included for information. No

samples are provided for these charts since they are

selfexplanatory.

ANGLE OF ATTACK (AOA)

AOA data is provided in figure C17 for information.

AOA data for altitudes from sea level to 60,000 feet

and from 0.31.2 mach is shown.

REFER TO FIGURE C17.

Enter AOA chart with GW (A), proceed horizontally

to altitude (B), vertically down to mach number (C),

and horizontally left to read AOA (D).

SAMPLE PROBLEM.

A. GW

= 33,000 pounds

B. Altitude

= 30,000 feet

C. Mach number

= 0.80

D. AOA

= 4.3 degrees

T.O. GR1F16CJ11

Change 7C15

AVAILABLE LOAD FACTOR

Load factors available with the LG handle in UP and

the STORES CONFIG switch in CAT I or CAT III are

presented in figure C18. The load factor data is pre

sented as a function of altitude, mach, and GW and is

valid for all temperatures, throttle settings, and DI.

The load factor value obtained from this chart is

based solely on the aerodynamic characteristics of the

aircraft. Sustained load factor capabilities are pre

sented in Part 8.

REFER TO FIGURE C18.

Determine either CAT I or CAT III loading. Enter

Available Load Factor chart with mach (A). Proceed

vertically to altitude (B) and then horizontally left to

the GW baseline and parallel guidelines to GW (C).

Finally, proceed left to read available load factor (D).

SAMPLE PROBLEMS (CAT I).

A. Mach

= 0.6

B. Altitude

= 20,000 feet

KCAS

= 275

C. GW

= 23,000 pounds

D. Available load

factor

= 4.6g

A. Mach

= 1.4

B. Altitude

= 10,000 feet

KCAS

= 794 (obtained from

figure C13)

C. GW

= 28,000 pounds

D. Available load

factor

= 9.0g

SAMPLE PROBLEMS (CAT III).

A. Mach

= 1.6

B. Altitude

= 35,000 feet

KCAS

= 584

C. GW

= 33,000 pounds

D. Available load

factor

= 5.1g

A. Mach

= 0.5

B. Altitude

= 30,000 feet

KCAS

= 184

C. GW

= 28,000 pounds

D. Available load

factor

= 1.4g

A. Mach

= 0.8

B. Altitude

= Sea level

KCAS

= 529 (obtained from

figure C13)

C. GW

= 28,000 pounds

D. Available load

factor

= 9.0g

TURN CONVERSION

Figure C19 is provided as an aid for conversion

between load factor, turn rate, turn radius, KTAS,

and bank angle.

GROUND VEHICLE FRICTION READ

INGTORCR CONVERSION

Figure C110 is provided as an aid for conversion

between ground vehicle friction reading and RCR/

braking action level.

T.O. GR1F16CJ11

C16Change 7

Drag Indexes and Weights

Basic Aircraft

DATA BASIS ESTIMATED

AIRCRAFT OPERATING WEIGHT LB*

F16C**

F16D**

BASIC AIRCRAFT

21,200

22,300

INCLUDES PILOT (

2), OIL, UNUSABLE FUEL, TIP MISSILE LAUNCHERS AND CFTs.

ALL WEIGHTS ARE APPROXIMATE. REFER TO INDIVIDUAL AIRCRAFT WEIGHT AND BALANCE HANDBOOK FOR

ACTUAL AIRCRAFT WEIGHT.

DRAG INDEX (SUBSONIC/SUPERSONIC)*

F16C

F16D

BASIC AIRCRAFT

7/6

11/7

AIM9L TIP MISSILES ON 16S210 LAUNCHERS INCLUDED.

EXPENDABLES WEIGHT LB

F16C

F16D

INTERNAL USABLE FUEL
CONFORMAL FUEL TANKS (CFT) USABLE FUEL
EXTERNAL USABLE FUEL:

300GALLON TANK
370GALLON TANK
600GALLON TANK

CHAFF/FLARES:
GUN AMMO

FULL DRUM (511 ROUNDS)
FIRED OUT (RETAINED AMMO/CASINGS, 511 ROUNDS)

JP8

7116
1528
2040
2516
3961

287
130

5874
1528
2040
2516
3961

287
130

CHAFF/FLARE WEIGHT BASED ON 2 FULLY LOADED CHAFF MAGAZINES AND 2 FULLY LOADED FLARE

MAGAZINES

CHAFF/FLARE WEIGHT BASED ON 4 FULLY LOADED CHAFF MAGAZINES AND 4 FULLY LOADED FLARE

MAGAZINES

Figure C11.(Sheet 1)

T.O. GR1F16CJ11

Change 7C17

Drag Indexes and Weights

Suspension Equipment

DATA BASIS ESTIMATED

SUSPENSION EQUIPMENT

STATION

JETTISON

WEIGHT

TOTAL

WEIGHT

DRAG

INDEX

ADAPTER (16S301)

AIM9 LAUNCHER (16S210)

AIM9 LAUNCHER (16S210) +

ADAPTER (16S301)

CENTERLINE PYLON

(16S951)

NONJETTISON (NJETT) FUEL PYLON

LANTIRN TARGETING POD

PYLON (16S1150)

LAU88/A + WEAPON PYLON

LAU88 A/A + WEAPON PYLON

LAU117/A, A(V)1/A, A(V)3/A +

WEAPON PYLON

LAU118(V)4/A + WEAPON

PYLON

LAU129/A LAUNCHER

LAU129/A LAUNCHER +

ADAPTER (16S301)

TER (16S1750) + WEAPON PYLON

TER (66J45517) + WEAPON PYLON

WEAPON PYLON

(16S1700)

2,3,7, OR 8

1 OR 9

2,3,7, OR 8

4 OR 6

3 OR 7

1 OR 9

2,3,7, OR 8

3,4,6, OR 7

468

476

130

120

117 (123

)

93 (99

)

177

304

749

757

411

401

113

398 (404

)

374 (380

)

281

INCLUDES MAU12C/A, D/A.

WEIGHT IF BDU33 ADAPTERS ARE INSTALLED.

Figure C11.(Sheet 2)

T.O. GR1F16CJ11

C18Change 7

Drag Indexes and Weights

Individual Stores

DATA BASIS ESTIMATED

NOTE: WEIGHT AND DRAG INDEXES DO NOT

INCLUDE SUSPENSION EQUIPMENT.

REFER TO SHEET 2.

STORE

STATION

RACK

WEIGHT

(EACH STORE)

DRAG

INDEX

(EACH STORE)

A/A 37U36:

TARGET STOWED

3 OR 7

PYLON

903

TARGET DEPLOYED

3 OR 7

PYLON

204

TOW REEL ONLY

(TARGET/CABLE RELEASED)

3 OR 7

PYLON

495

AGM65A, B

3 OR 7

LAU88/A, A/A, 117/A,

A(V)1/A, A(V)3/A

464

13/8

AGM65D

3 OR 7

LAU88/A, A/A, 117/A,

A(V)1/A, A(V)3/A

493

13/8

AGM65G

3 OR 7

LAU117/A, A(V)1/A,

A(V)3/A

672

AGM84D1

3 OR 7

PYLON WITH HIAK

1172

AGM88B

3 OR 7

LAU118(V)4/A

770

AIM9P, P1

1 OR 9

LAUNCHER

166

AIM9P2, P3, P4, P5, N, N3

1 OR 9

LAUNCHER

178

AIM9L, M, S

1 OR 9

LAUNCHER

195

AIM9P, P1

2,3,7, OR 8

LAUNCHER + ADAPTER

166

AIM9P2, P3, P4, P5, N, N3

2,3,7, OR 8

LAUNCHER + ADAPTER

178

AIM9L, M, S

2,3,7, OR 8

LAUNCHER + ADAPTER

195

AIM120B

1 OR 9

LAUNCHER

341

AIM120B

2,3,7, OR 8

LAUNCHER + ADAPTER

341

AN/ASQ:

T17 (P4A)

1 OR 9

2,3,7, OR 8

LAUNCHER

LAUNCHER + ADAPTER

122

T20 (P4AX)

1 OR 9

2,3,7, OR 8

LAUNCHER

LAUNCHER + ADAPTER

123

T25 (P4AM)

1 OR 9

2,3,7, OR 8

LAUNCHER

LAUNCHER + ADAPTER

125

ATM84D1

3 OR 7

PYLON WITH HIAK

1172

USED FOR REMOVING WINGTIP AIM9 MISSILE SINCE BASIC AIRCRAFT CONFIGURATION INCLUDES AIM9'S

AT STATIONS 1 AND 9. USING DRAG INDEX ZERO GIVES SLIGHTLY CONSERVATIVE RESULTS WITHOUT TIP

MISSILES.

USED FOR REPLACING WINGTIP AIM9 MISSILE. DRAG INDEX IS 2 LESS THAN AIM9 MISSILE AT STATION 1 OR 9.

Figure C11.(Sheet 3)

T.O. GR1F16CJ11

Change 7C19

Drag Indexes and Weights

Individual Stores

DATA BASIS ESTIMATED

NOTE: WEIGHT AND DRAG INDEXES DO NOT

INCLUDE SUSPENSION EQUIPMENT.

REFER TO SHEET 2.

STORE

STATION

RACK

WEIGHT

(EACH STORE)

DRAG

INDEX

(EACH STORE)

BDU33B/B, D/B

3,4,6, OR 7

TER

BDU50/B, A/B

3,4,6, OR 7

PYLON/TER

510

5/9

BL755 MK 2

3,4,6, OR 7

PYLON/TER

610

19/23

BLU107/B

3,4,6, OR 7

PYLON/TER

482

5/8

BLU109/B

3 OR 7

PYLON

2020

CATM84D2

3 OR 7

PYLON WITH HIAK

1161

CATM88B (WITH WINGS AND

FINS)

3 OR 7

LAU118(V)4/A

795

CATM88B (WITHOUT WINGS

AND FINS)

3 OR 7

LAU118(V)4/A

733

CATM120A (107), B (106)

1 OR 9

LAUNCHER

345

CATM120A (107), B (106)

2,3,7, OR 8

LAUNCHER + ADAPTER

345

CBU52B/B

CBU58/B, A/B

CBU71/B

(SUU30 H/B)

3,4,6, OR 7

PYLON/TER

785

800

20/24

CBU87/B (SUU65/B)

3,4,6, OR 7

PYLON/TER

950

18/22

GBU10/B, A/B, C/B, D/B, E/B, F/B

3,4,6, OR 7

PYLON

2052

GBU10G/B, H/B, J/B

3,4,6, OR 7

PYLON

2135

GBU12/B, A/B, B/B, C/B, D/B, E/B

3,4,6, OR 7

PYLON

611

GBU12B/B, C/B, D/B, E/B

3 OR 7

TER

611

GBU24/B

3,4,6, OR 7

PYLON

2306

GBU24A/B

3,4,6, OR 7

PYLON

2354

IRIST

2,3,7, OR 8

LAUNCHER + ADAPTER

198

ITM88B

3 OR 7

LAU118(V)4/A

770

LANTIRN POD:

NAVIGATION

TARGETING

PYLON

429

553

WITH PYLON.

Figure C11.(Sheet 4)

T.O. GR1F16CJ11

C110Change 7

Drag Indexes and Weights

Individual Stores

DATA BASIS ESTIMATED

NOTE: WEIGHT AND DRAG INDEXES DO NOT

INCLUDE SUSPENSION EQUIPMENT.

REFER TO SHEET 2.

STORE

STATION

RACK

WEIGHT

(EACH STORE)

DRAG

INDEX

(EACH STORE)

LAU3/A, B/A, C/A, D/A ROCKET

LAUNCHER WITH:

(19) M151

3,4,6, OR 7

PYLON/TER

496

14/20

(19) M156

3,4,6, OR 7

PYLON/TER

496

14/20

(19) MK 1

3,4,6, OR 7

PYLON/TER

418

14/20

(19) MK 5

3,4,6, OR 7

PYLON/TER

418

14/20

FIRED OUT (NO FWD FAIRING)

3,4,6, OR 7

PYLON/TER

26/39

EMPTY WITH FWD FAIRING

3,4,6, OR 7

PYLON/TER

14/20

LAU68A/A, B/A ROCKET

LAUNCHER WITH:

(7) M151

3 OR 7

TER

215

(7) M156

3 OR 7

TER

215

(7) MK 1

3 OR 7

TER

194

(7) MK 5

3 OR 7

TER

194

FIRED OUT (NO FWD FAIRING)

3 OR 7

TER

EMPTY WITH FWD FAIRING

3 OR 7

TER

LAU131/A ROCKET LAUNCHER

WITH:

(7) M151

3 OR 7

TER

223

(7) M156

3 OR 7

TER

223

(7) MK 1

3 OR 7

TER

195

(7) MK 5

3 OR 7

TER

195

FIRED OUT (NO FWD FAIRING)

3 OR 7

TER

EMPTY WITH FWD FAIRING

3 OR 7

TER

LAU5003/A ROCKET LAUNCHER

WITH:

(19) CM151 (CRV7)

(19) RA79 (CRV7)

FIRED OUT (NO FWD FAIRING)

EMPTY WITH FWD FAIRING

3 OR 7

TER

530

658

Figure C11.(Sheet 5)

Content .. 76 77 78 79 ..

F16C/D. FLIGHT MANUAL (2002) - page 78

F16C/D. FLIGHT MANUAL (2002) - page 78