Content .. 77 78 79 80 ..

F16C/D. FLIGHT MANUAL (2002) - page 79

T.O. GR1F16CJ11

Change 7C111

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)

M129E2

3,4,6, OR 7

PYLON

229

MK 20 MOD 3,4

3,4,6, OR 7

PYLON/TER

490

11/14

MK 82 AIR

3,4,6, OR 7

PYLON/TER

540

7/11

MK 82 LDGP

3,4,6, OR 7

PYLON/TER

510

5/9

MK 82 (SNAKEYE)

3,4,6, OR 7

PYLON/TER

550

7/11

MK 84 AIR

3,4,6, OR 7

PYLON

2010

MK 84 LDGP

3,4,6, OR 7

PYLON

1970

MXU648A/A, C/A (TRAVEL POD)

(MAX CARGO WT IS 300 LB)

3,4,5,6, OR 7

PYLON/TER

108

(EMPTY)

10/10

SUU20A/A, B/A WITH:

(A/A) (B/A)

(6) BDU33B/B, D/B

3,4,6, OR 7

PYLON

474420

(6) MK 106

3,4,6, OR 7

PYLON

360306

(4) M151

3,4,6, OR 7

PYLON

414360

(6) BDU33B/B, D/B+(4) M151

3,4,6, OR 7

PYLON

558504

(6) MK 106+(4) M151

3,4,6, OR 7

PYLON

444390

EMPTY

3,4,6, OR 7

PYLON

330276

SUU5003A/A, B/A WITH:

(6) BDU33B/B, D/B

(6) MK 106

(4) CM151 (CRV7)

(6) BDU33B/B, D/B+(4) CM151

(6) MK 106+(4) CM151

(4) RA79T (RA82) (CRV7)

EMPTY

3,4,6, OR 7

PYLON

(A/A) (B/A)

583546

469432

561524

705668

591554

547510

439402

Figure C11.(Sheet 6)

T.O. GR1F16CJ11

C112Change 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)

TGM65A, B

3 OR 7

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

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

447

13/8

TGM65D, G

3 OR 7

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

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

474

13/8

300GALLON TANK (EMPTY/FULL):

NO STORES AT 4 OR 6

PYLON

392

/2432

STORES AT 4 AND 6

PYLON

392

/2432

370GALLON TANK (EMPTY/FULL):

NO STORES AT 3 OR 7

4 OR 6

NONE

531

/3047

AIM9'S AT 3 OR 7

4 OR 6

NONE

531

/3047

SINGLE RACKS OR STORES

AT 3 OR 7

4 OR 6

NONE

531

/3047

MULTIPLE STORES AT 3 OR 7

4 OR 6

NONE

531

/3047

600GALLON TANK (EMPTY/FULL):

NO STORES AT 3 OR 7

4 OR 6

PYLON (NJETT)

455

/4416

AIM9'S AT 3 OR 7

4 OR 6

PYLON (NJETT)

455

/4416

SINGLE RACKS OR STORES

AT 3 OR 7

4 OR 6

PYLON (NJETT)

455

/4416

MULTIPLE STORES AT 3 OR 7

4 OR 6

PYLON (NJETT)

455

/4416

CFT TANK (EMPTY/FULL)

N/A

NONE

486

/2014

300/370/600GALLON/CFT TANK WEIGHTS BASED ON JP8.

INCLUDES UNUSABLE FUEL.

Figure C11.(Sheet 7)

T.O. GR1F16CJ11

Change 7C113

1F-16X-1-1-0002A

DATA BASIS ESTIMATED

Position Error Correction Airspeed

and Altitude

800

700

600

500

400

300

200

100

-1000

-500

500

1000

-10

-5

TITUDE CORRECTION FEET

AIRSPEED CORRECTION KNOTS

CALIBRATED AIRSPEED KNOTS

PRESSURE ALTITUDE FEET

NOTE: USE ALTITUDE CORRECTION ONLY WHEN THE ALTIMETER MODE

SELECTOR IS IN THE PNEU (SECONDARY) OPERATIONS MODE.

PRESSURE ALTITUDE FEET

NOTE: SUBTRACT CORRECTION FROM DESIRED CONDITION TO OBTAIN INDICATOR READING.

Figure C12.(Sheet 1)

T.O. GR1F16CJ11

C114Change 7

1F-16X-1-1-0003X

DATA BASIS ESTIMATED

Position Error Correction Mach Number

NOTE: SUBTRACT FROM THE TRUE MACH TO OBTAIN MACH INDICATOR READING.

-0.04

-0.03

-0.02

-0.01

0.01

0.02

0.03

0.04

0.4

0.6

0.8

1.0

1.2

1.4

1.6

TRUE MACH NUMBER

MACH CORRECTION

Figure C12.(Sheet 2)

. GR1F

16CJ

Change 7C115

Airspeed Conversion

1F-16X-1-1-0004X

STD TEMP

ALTITUDE

1000 FT

10
15
20
25
30
35
40
45
50
55
60

-56

-54

-44

-35

-25

-15

-5

0.4

0.5

0.6

0.7

0.8

0.9

1.0

200

300

400

500

600

100

200

300

400

500

600

CALIBRATED AIRSPEED KNOTS

TRUE AIRSPEED KNOTS

MACH NUMBER

-80

-70

-60

-50

-40

-30

-20

-10

140

120

100

-20

-40

-60

-80

-100

FAHRENHEIT

CENTIGRADE

= (

)

9/ 5

(

)

Figure C13.(Sheet 1)

. GR1F

16CJ

C116Change 7

Airspeed Conversion

1F-16X-1-1-0005X

1.0

1.2

1.4

1.6

1.8

2.0

600

700

800

900

1000

1100

1200

200

300

400

500

600

700

800

MACH NUMBER

TRUE AIRSPEED KNOTS

CALIBRATED AIRSPEED KNOTS

Figure C13.(Sheet 2)

T.O. GR1F16CJ11

Change 7C117

1F-16X-1-1-0006X

Compressibility Correction to Airspeed

NOTE: EQUIVALENT AIRSPEED = CALIBRATED AIRSPEED CORRECTION.

100

200

300

400

500

600

700

800

COMPRESSIBILITY CORRECTION KNOTS

CALIBRATED AIRSPEED KNOTS

Figure C14.

T.O. GR1F16CJ11

C118Change 7

Standard Atmosphere

DATA BASIS US STANDARD ATMOSPHERE, 1966

STANDARD SEA LEVEL AIR:

T = 59

F (15

= 29.921 IN. OF HG

W = 0.076475 LB/CU FT

= 0.0023769 SLUG/CU FT

1 IN. OF HG = 70.726 LB/SQ FT

1 IN. OF HG = 0.4912 LB/SQ IN.

= 1116.4 FT/SEC

= 661.48 KTS

ALTITUDE

DENSITY

AIR TEMPERATURE

SPEED OF

PRESSURE

ALTITUDE

FEET

DENSITY

RATIO

ρ/ρ

DEG F

DEG C

SPEED OF

SOUND

KNOTS

IN. OF

RATIO

P/P

-2000

-1000

1.0598

1.0296

0.9714

0.9855

66.132

62.566

18.962

16.981

665.98

663.73

32.15

31.02

1.0745

1.0368

1000

2000

3000

4000

1.0000

0.9711

0.9428

0.9151

0.8881

1.0000

1.0148

1.0299

1.0454

1.0611

59.000

55.434

51.868

48.302

44.735

15.000

13.019

11.038

9.057

7.075

661.48

659.23

656.92

654.60

652.35

29.92

28.86

27.82

26.82

25.84

1.0000

0.9644

0.9298

0.8962

0.8637

5000

6000

7000

8000

9000

0.8617

0.8359

0.8106

0.7860

0.7620

1.0773

1.0938

1.1107

1.1279

1.1456

41.169

37.603

34.037

30.471

26.905

5.094

3.113

1.132

-0.849

-2.831

650.04

647.72

645.34

643.02

640.71

24.90

23.98

23.09

22.22

21.39

0.8320

0.8014

0.7716

0.7428

0.7148

10,000

11,000

12,000

13,000

14,000

0.7385

0.7156

0.6932

0.6713

0.6500

1.1637

1.1822

1.2011

1.2205

1.2403

23.338

19.772

16.206

12.640

9.074

-4.812

-6.793

-8.774

-10.756

-12.737

638.33

635.95

633.63

631.25

628.87

20.58

19.79

19.03

18.29

17.58

0.6877

0.6614

0.6360

0.6113

0.5875

15,000

16,000

17,000

18,000

19,000

0.6292

0.6090

0.5892

0.5699

0.5511

1.2606

1.2815

1.3028

1.3246

1.3470

5.508

1.941

-1.625

-5.191

-8.757

-14.718

-16.699

-18.681

-20.662

-22.643

626.42

624.04

621.59

619.21

616.76

16.89

16.22

15.57

14.94

14.34

0.5643

0.5420

0.5203

0.4994

0.4791

20,000

21,000

22,000

23,000

24,000

0.5328

0.5150

0.4976

0.4807

0.4642

1.3700

1.3935

1.4176

1.4424

1.4678

-12.323

-15.889

-19.456

-23.022

-26.588

-24.624

-26.605

-28.587

-30.568

-32.549

614.32

611.87

609.42

606.91

604.46

13.75

13.18

12.64

12.11

11.60

0.4595

0.4406

0.4223

0.4046

0.3876

25,000

26,000

27,000

28,000

29,000

0.4481

0.4325

0.4173

0.4025

0.3881

1.4938

1.5206

1.5480

1.5762

1.6052

-30.154

-33.720

-37.286

-40.852

-44.419

-34.530

-36.511

-38.492

-40.473

-42.455

601.95

599.43

596.92

594.41

591.89

11.10

10.63

10.17

9.725

9.297

0.3711

0.3552

0.3398

0.3250

0.3107

Figure C15.(Sheet 1)

T.O. GR1F16CJ11

Change 7C119

Standard Atmosphere

DATA BASIS US STANDARD ATMOSPHERE, 1966

STANDARD SEA LEVEL AIR:

T = 59

F (15

= 29.921 IN. OF HG

W = 0.076475 LB/CU FT

= 0.0023769 SLUG/CU FT

1 IN. OF HG = 70.726 LB/SQ FT

1 IN. OF HG = 0.4912 LB/SQ IN.

= 1116.4 FT/SEC

o =

661.48 KTS

ALTITUDE

DENSITY

AIR TEMPERATURE

SPEED OF

PRESSURE

ALTITUDE

FEET

DENSITY

RATIO

ρ/ρ

DEG F

DEG C

SPEED OF

SOUND

KNOTS

IN. OF

RATIO

P/P

30,000

31,000

32,000

33,000

34,000

0.3741

0.3605

0.3473

0.3345

0.3220

1.6349

1.6654

1.6968

1.7291

1.7623

-47.985

-51.551

-55.117

-58.683

-62.249

-44.436

-46.417

-48.398

-50.379

-52.361

589.31

586.80

584.22

581.64

579.06

8.885

8.488

8.106

7.737

7.382

0.2970

0.2837

0.2709

0.2586

0.2467

35,000

36,089*

37,000

38,000

39,000

0.3099

0.2971

0.2844

0.2710

0.2583

1.7964

1.8347

1.8753

1.9209

1.9677

-65.816

-69.700

-54.342

-56.500

576.41

573.57

7.041

6.683

6.397

6.097

5.811

0.2353

0.2234

0.2138

0.2038

0.1942

40,000

41,000

42,000

43,000

44,000

0.2462

0.2346

0.2236

0.2131

0.2031

2.0155

2.0645

2.1148

2.1662

2.2189

-69.700

-56.500

573.57

5.538

5.278

5.030

4.794

4.569

0.1851

0.1764

0.1681

0.1602

0.1527

45,000

46,000

47,000

48,000

49,000

0.1936

0.1845

0.1758

0.1676

0.1597

2.2728

2.3281

2.3848

2.4428

2.5022

-69.700

-56.500

573.57

4.355

4.151

3.956

3.770

3.563

0.1455

0.1387

0.1322

0.1260

0.1201

50,000

51,000

52,000

53,000

54,000

0.1522

0.1451

0.1383

0.1318

0.1256

2.5630

2.6254

2.6892

2.7546

2.8216

-69.700

-56.500

573.57

3.425

3.264

3.111

2.965

2.826

0.1145

0.1091

0.1040

0.09909

0.09444

55,000

56,000

57,000

58,000

59,000

0.1197

0.1141

0.1087

0.1036

0.09877

2.8903

2.9606

3.0326

3.1063

3.1819

-69.700

-56.500

573.57

2.693

2.567

2.446

2.331

2.222

0.09001

0.08578

0.08176

0.07792

0.07426

60,000

61,000

62,000

63,000

64,000

65,000

0.09414

0.08972

0.08551

0.08150

0.07767

0.07403

3.2593

3.3386

3.4198

3.5029

3.5881

3.6754

-69.700

-56.500

573.57

2.118

2.018

1.924

1.833

1.747

1.665

0.07078

0.06746

0.06429

0.06127

0.05840

0.05566

Tropopause

Figure C15.(Sheet 2)

T.O. GR1F16CJ11

C120Change 7

Temperature Correction for Compressibility

1F-16X-1-1-0007A

-80

-60

-40

-20

0.2

0.4

0.6

0.8

1.0

1.2

1.4

1.6

1.8

2.0

AMBIENT TEMPERATURE C

MACH NUMBER

TOTAL TEMPERATURE C

TEMPERATURE RECOVERY

COEFFICIENT = 1.00

NOTE:

Figure C16.

T.O. GR1F16CJ11

Change 7C121

1F-16CJ-1-1-0008X37

Angle of Attack

DATA BASIS ESTIMATED

LG UP

ALL DRAG INDEXES

1G LEVEL FLIGHT

NO THRUST EFFECTS INCLUDED

CONFIGURATION:

CONDITIONS:

AOA DEGREES

GW 1000 POUNDS

Figure C17.

T.O. GR1F16CJ11

C122Change 7

1F-16CJ-1-1-1009X37

0.4

0.8

1.2

AILABLE LOAD F

ACTOR G

GW 1000 LB

BASELINE

1.6

2.0

MACH NUMBER

AILABLE LOAD F

ACTOR G

GW 1000 LB

BASELINE

0.0

0.4

0.8

1.2

1.6

2.0

0.0

CAT III

CAT I

MACH NUMBER

Available Load Factor

DATA BASIS ESTIMATED

ALL DRAG INDEXES

LG UP

ENGINE F100-PW-229/CFT

CONDITIONS:

CONFIGURATION:

NOTES:

ALL TEMPERATURES
ALL THROTTLE SETTING

REFER TO SECTION V FOR G LIMITATIONS.

KCAS ON 9.0G LIMITER IS INACCURATE. (REFER TO FIGURE C1-3.)

2.4

Figure C18.

TURN RADIUS 1000 FEET

LOAD F

ACTOR G

1F-16X-1-1-0009A

BANK ANGLE DEGREES

TURN RATE DEGREES/SECOND

Turn Conversion

. GR1F

16CJ

Change 7C123

Figure C19.

T.O. GR1F16CJ11

C124Change 7

1F-16X-1-1-0001X

0.80

0.70

0.60

0.50

0.40

0.30

0.20

0.10

MEDIUM

MEDIUM TO POOR

GROUND

VEHICLE

FRICTION

READING

RCR/

BRAKING

ACTION

LEVEL

Ground Vehicle Friction Reading-To-RCR

Conversion

NOTES:

IN MANY AREAS, GROUND VEHICLE FRICTION READING IS THE ONLY AVAILABLE MEASURE

FOR RUNWAY BRAKING ACTION.
NORMALLY THE GROUND VEHICLE FRICTION READING, ALSO REFERRED TO AS BRAKING

ACTION COEFFICIENT, IS GIVEN AS WHOLE NUMBERS, NOT AS DECIMALS (I.E., 40 INSTEAD

OF 0.40).

MEDIUM TO GOOD

POOR

GOOD

Figure C110.

T.O. GR1F16CJ11

Change 7C21

PART 2 - TAKEOFF

TABLE OF CONTENTS

Page

Takeoff Data

C21

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

Definitions of Terms

C21

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

Data Basis for Charts

C22

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

Takeoff Planning

C22

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

Takeoff Factor

C22

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

Takeoff Speed

C23

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

Takeoff Distance

C23

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

Acceleration Check Speed

C24

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

Refusal Speed

C24

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

Minimum AB Blowout Speed

C24

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

Takeoff Roll Trim With

Asymmetric Stores

C25

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

Takeoff and Landing Crosswind

Limits

C25

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

Brake Energy Limits-Maximum

Effort Braking

C25

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

LIST OF CHARTS

Figure

Page

Takeoff Factor

C21

C27

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

. . . .

Takeoff Speed

C22

C28

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

. . . .

Takeoff Distance

C23

C29

. . . . . . . . . .

. . . .

Acceleration Check

Speed

C24

C210

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

. . . .

Refusal Speed (NonAB)

C25

C211

. . . .

Refusal Speed (AB)

C26

C214

. . . . . . . .

. . . .

Refusal Speed With Drag

Chute (NonAB)

C27

C217

. . . . . . . . . . .

. . . .

Refusal Speed With Drag

Chute (AB)

C28

C221

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

. . . .

Minimum AB Blowout

Speed

C29

C225

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

. . . .

Takeoff Roll Trim With

Asymmetric Stores

C210

C226

. . . . . .

. . . .

Takeoff and Landing Cross

wind Limits

C211

C227

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

. . . .

Brake Energy Limits-Max

Effort Braking

C212

C228

. . . . . . . . . .

. . . .

Safe Tire Bead Temperature-

For Quick Turnaround

C213

C231

. . .

. . . .

TAKEOFF DATA

All data needed for takeoff planning is presented in

this section. Takeoff data is presented for MIL and

MAX AB throttle settings. For the purpose of Part 2,

MIL thrust is called nonAB and MAX AB thrust is

called AB. All data is based on normal flap positions

(LEF's are at - 2 degrees and TEF's are at 20 degrees

down while weight is on the MLG). Rotation speed,

takeoff speed, ground run distance, acceleration

check speed, maximum refusal speed, and crosswind

data may be determined from these charts. Effects of

wind, temperature, pressure altitude, runway slope

and length, drag index, and RCR are included on

appropriate charts.

DEFINITIONS OF TERMS

Takeoff factor - A computed number which is a func

tion of engine thrust, temperature, and altitude. It is

used as a control parameter for most charts in this

section.

Rotation speed - Airspeed at which rotation to liftoff

attitude should be started.

Takeoff speed - Airspeed at which the main tires

leave the ground.

Takeoff ground run distance (also takeoff distance) -

Ground run in feet from brake release to takeoff

speed.

Refusal speed - Maximum airspeed that can be

attained and still stop on remaining runway should

takeoff be aborted.

Minimum AB blowout speed - Minimum airspeed at

which an AB blowout can occur and still reach takeoff

speed within the remaining runway length using

nonAB thrust.

Runway slope - Change in runway elevation divided

by runway length multiplied by 100 (expressed in per

cent uphill or downhill).

Aerodynamic braking (threepoint attitude) - Use of

fully opened speedbrakes and maximum horizontal

tail deflection (without raising nose tire from runway)

to increase deceleration. (Data base for aborted take

off.)

T.O. GR1F16CJ11

C22Change 7

Maximum effort braking - A single continuous wheel

brake application using maximum pedal pressure

consistent with maintaining directional control (anti

skid on) in conjunction with aerodynamic braking

and drag chute.

DATA BASIS FOR CHARTS

Estimated aerodynamic and propulsion data based

on wind tunnel and flight test results was used to gen

erate the information presented in this section.

Changes in LEF's positions and engine bleed require

ments for weight on or off LG have been accounted for,

as appropriate. Assumptions and approximations

made during the construction of each chart are dis

cussed along with the chart.

TAKEOFF PLANNING

Careful takeoff planning is essential from a stand

point of flight safety and mission success. Proper

planning will permit maximum use of the capability

of the aircraft to take off with heavy payloads while

maintaining adequate safety margins. Takeoff plan

ning comprises the following:

Determine aircraft configuration (total air

craft takeoff GW and drag index).

Obtain runway conditions for expected takeoff

time (pressure altitude, temperature, windspeed,

wind direction, length, slope, etc.).

Compute appropriate data.

This information will permit decisions to be made

regarding downloading or continuing or aborting

takeoff in the event of an emergency. Each chart is

discussed in detail in the following paragraphs. An

example takeoff planning problem is worked in con

junction with the discussion. The following typical

aircraft and field information is normally obtained

before using the charts:

Takeoff GW (air

craft operating

weight plus fuel,

ammo, and stores)

= 33,000 pounds (Allow for

ground operation fuel con

sumption; refer to Part 3)

(Normal taxi operations

require approximately 25

pounds of fuel per minute)

Stores loading

= Two AIM9L missiles at

stations 1 and 9, two MK 84

bombs at stations 3 and 7,

two 370gallon fuel tanks

at stations 4 and 6

Takeoff CG

= Refer to Weight and Bal

ance Form F (DD Form

3654)

Drag index

= Refer to T.O.

GR1F16CJ12, STORES

LIMITATIONS

Runway pressure

altitude

= 2000 feet

Runway

temperature

= 42

Runway length

= 6000 feet (available length)

Runway conditions = Dry concrete (RCR = 23)

Runway slope

= 1 percent (uphill)

Runway wind

= 10 knots (headwind)

TAKEOFF FACTOR

The takeoff factor concept of presenting takeoff per

formance is used to simplify chart presentations. The

takeoff factor is a computed number and is common

to all charts for a given thrust setting, pressure alti

tude, and temperature.

REFER TO FIGURE C21.

Enter the chart with runway temperature (A). Pro

ceed horizontally to pressure altitude (B) and then

vertically down to read MIL takeoff factor (C) or MAX

AB takeoff factor (D).

SAMPLE PROBLEM.

A. Runway temperature

= 42

B. Pressure altitude

= 2000 feet

C. MIL takeoff factor

= 2.54

D. MAX AB takeoff factor = 1.44

Content .. 77 78 79 80 ..

F16C/D. FLIGHT MANUAL (2002) - page 79

F16C/D. FLIGHT MANUAL (2002) - page 79