Content .. 52 53 54 55 ..

F16C/D. FLIGHT MANUAL (2002) - page 54

T.O. GR1F16CJ11

Change 7A15

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 A18. 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 A18.

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

= 4.7g

A. Mach

= 1.4

B. Altitude

= 10,000 feet

KCAS

= 794 (obtained from

figure A13)

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

= 5.5g

A. Mach

= 0.5

B. Altitude

= 30,000 feet

KCAS

= 184

C. GW

= 28,000 pounds

D. Available load

factor

= 1.3g

A. Mach

= 0.8

B. Altitude

= Sea level

KCAS

= 529 (obtained from

figure A13)

C. GW

= 28,000 pounds

D. Available load

factor

= 9.0g

TURN CONVERSION

Figure A19 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 A110 is provided as an aid for conversion

between ground vehicle friction reading and RCR/

braking action level.

T.O. GR1F16CJ11

A16Change 7

Drag Indexes and Weights

Basic Aircraft

DATA BASIS FLIGHT TEST

AIRCRAFT OPERATING WEIGHT LB*

F16C**

F16D**

BASIC AIRCRAFT

20,200

21,400

INCLUDES PILOT (

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

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
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

2040
2516
3961

287
130

5874

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 A11.(Sheet 1)

T.O. GR1F16CJ11

Change 7A17

Drag Indexes and Weights

Suspension Equipment

DATA BASIS FLIGHT TEST

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 A11.(Sheet 2)

T.O. GR1F16CJ11

A18Change 7

Drag Indexes and Weights

Individual Stores

DATA BASIS FLIGHT TEST

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

117

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 A11.(Sheet 3)

T.O. GR1F16CJ11

Change 7A19

Drag Indexes and Weights

Individual Stores

DATA BASIS FLIGHT TEST

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

ITM88B

3 OR 7

LAU118(V)4/A

770

IRIST

2,3,7, OR 8

LAUNCHER + ADAPTER

198

LANTIRN POD:

NAVIGATION

TARGETING

PYLON

429

553

WITH PYLON.

Figure A11.(Sheet 4)

T.O. GR1F16CJ11

A110Change 7

Drag Indexes and Weights

Individual Stores

DATA BASIS FLIGHT TEST

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 A11.(Sheet 5)

T.O. GR1F16CJ11

Change 7A111

Drag Indexes and Weights

Individual Stores

DATA BASIS FLIGHT TEST

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 A11.(Sheet 6)

T.O. GR1F16CJ11

A112Change 7

Drag Indexes and Weights

Individual Stores

DATA BASIS FLIGHT TEST

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)

399

/4360

AIM9'S AT 3 OR 7

4 OR 6

PYLON (NJETT)

399

/4360

SINGLE RACKS OR STORES

AT 3 OR 7

4 OR 6

PYLON (NJETT)

399

/4360

MULTIPLE STORES AT 3 OR 7

4 OR 6

PYLON (NJETT)

399

/4360

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

INCLUDES UNUSABLE FUEL.

Figure A11.(Sheet 7)

T.O. GR1F16CJ11

Change 7A113

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

DATA BASIS FLIGHT TEST

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 A1Ć2.ą(Sheet 1)

T.O. GR1F16CJ11

A114Change 7

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

DATA BASIS FLIGHT TEST

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 A12.(Sheet 2)

. GR1F

16CJ

Change 7A115

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 A13.(Sheet 1)

. GR1F

16CJ

A116Change 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 A13.(Sheet 2)

T.O. GR1F16CJ11

Change 7A117

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 A14.

T.O. GR1F16CJ11

A118Change 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 A15.(Sheet 1)

T.O. GR1F16CJ11

Change 7A119

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 A15.(Sheet 2)

T.O. GR1F16CJ11

A120Change 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 A16.

Content .. 52 53 54 55 ..

F16C/D. FLIGHT MANUAL (2002) - page 54

F16C/D. FLIGHT MANUAL (2002) - page 54