F16C/D. FLIGHT MANUAL (2002) - page 61

T.O. GR1F16CJ11

A830Change 7

MAX AB Accelerations   40,000 Feet

DATA BASIS FLIGHT TEST

CONDITIONS:

ENGINE F100PW229

STANDARD DAY TEMPERATURE (-56

°

C)

NOTE:REFER TO SECTION V FOR AIRSPEED LIMITATIONS.

TIME (SEC)/DISTANCE (NM)/FUEL (LB)

TEMP EFFECT FACTOR

KIAS

MACH

GW 24,000 LB

28,000 LB

32,000 LB

36,000 LB

40,000 LB

+20°C

-20°C

200

0.67

0/0/0

0/0/0

0/0/0

0/0/0*

0/0/0**

1.00/1.00/1.00

1.00/1.00/1.00

250

0.82

29/3.4/116

40/4.7/162

63/7.3/251

91/10.9/372

81/10.1/351

1.11/1.16/1.13

0.92/0.88/0.88

0

300

0.97

55/7.1/239

74/9.6/323

109/14.0/470

159/20.6/694

1.14/1.19/1.13

0.89/0.84/0.88

15

0

350

1.10

130/19.6/643

196/29.8/977

0.72/0.67/0.72

I = 

1

400

1.24

196/31.9/1053

288/47.0/1551

0.71/0.66/0.70

DI 

450

1.37

357/65.8/2284

539/99.8/3469

0.53/0.48/0.49

CMBT SPD

439/84.0/2965 558/104.0/3624 225/32.6/1074

197/26.5/885

203/27.8/934

0.32/0.26/0.23

1.09/1.19/1.38

CMBT SPD

KIAS/MACH

459/1.40

451/1.38

323/1.03

308/0.99

300/0.96

0.71/0.74

1.23/1.23

*

BASED ON 209 KIAS/0.70 MACH.

**

BASED ON 226 KIAS/0.75 MACH.

TIME (SEC)/DISTANCE (NM)/FUEL (LB)

TEMP EFFECT FACTOR

KIAS

MACH

GW 26,000 LB

30,000 LB

34,000 LB

38,000 LB

42,000 LB

+20°C

-20°C

200

0.67

0/0/0

0/0/0

0/0/0

0/0/0*

0/0/0**

1.00/1.00/1.00

1.00/1.00/1.00

00

250

0.82

36/4.2/145

53/6.2/213

103/11.9/407

90/11.0/383

51/6.6/226

1.11/1.17/1.14

0.92/0.87/0.88

=

 2

0

300

0.97

71/9.2/310

101/13.2/442

177/22.7/760

1.16/1.22/1.16

0.87/0.83/0.86

D

I 

=

CMBT SPD

107/15.0/496

132/18.1/601

195/25.4/850

196/26.3/887

183/25.1/840

1.07/1.11/1.05

1.04/1.02/1.08

D

CMBT SPD

KIAS/MACH

312/1.00

308/0.99

303/0.97

295/0.95

286/0.93

0.99/0.99

1.02/1.02

*

BASED ON 220 KIAS/0.73 MACH.

**

BASED ON 241 KIAS/0.80 MACH.

TIME (SEC)/DISTANCE (NM)/FUEL (LB)

TEMP EFFECT FACTOR

KIAS

MACH

GW 26,000 LB

30,000 LB

34,000 LB

38,000 LB

42,000 LB

+20°C

-20°C

200

0.67

0/0/0

0/0/0

0/0/0*

0/0/0**

0/0/0***

1.00/1.00/1.00

1.00/1.00/1.00

250

250

0.82

38/4.5/154

58/6.8/232

105/12.3/418

95/11.7/407

14/1.9/63

1.12/1.17/1.14

0.91/0.87/0.88

=

 2

5

300

0.97

82/10.8/363

125/16.6/555

0.84/0.79/0.83

D

I 

=

CMBT SPD

104/14.2/473

132/17.7/590

193/25.0/836

196/26.0/882

168/23.1/771

1.08/1.12/1.07

0.92/0.88/0.93

D

CMBT SPD

KIAS/MACH

305/0.98

301/0.97

296/0.95

288/0.93

279/0.91

0.99/0.99

1.01/1.01

*

BASED ON 203 KIAS/0.68 MACH.

**

BASED ON 222 KIAS/0.74 MACH.

***

BASED ON 248 KIAS/0.82 MACH.

Figure A813.(Sheet 2)

T.O. GR1F16CJ11

Change 7A831

1F-16CJ-1-1-1052X

1.1

1.0

0.9

TURN RADIUS F

ACTOR

RADIUS TEMP EFFECT

TEMP DEV FROM STD DAY   C

-20

-10

0

10

20

Turn Performance    Sea Level

DATA BASIS FLIGHT TEST

CONFIGURATION:

CONDITIONS:

ENGINE F100-PW-229

STANDARD DAY

MIL

NOTE:  REFER TO SECTION V FOR AIRSPEED LIMITATIONS.

DRAG INDEX = 0

GW = 22,000 POUNDS

  TURN RA

TE

(DEGREES/SECOND)

TEMP DEV FROM

STD DAY    C

TEMPERATURE EFFECT

-4

-2

0

  TURN RA

TE

(DEGREES/SECOND)

GW   1000 POUNDS

GW EFFECT

22

24

26

24

20

16

12

8

4

0

0

0.2

0.4

0.6

0.8

1.0

1.2

MACH NUMBER

TURN RA

TE   DEGREES/SECOND

QUICKEST TURN

(24.1 DEGREES/SECONDS)

TIGHTEST TURN

(RADIUS =

1217 FEET)

MAXIMUM AIRSPEED

28

3
2

1

-1

-2
-3

10

20

-20

-10

Figure A814.

T.O. GR1F16CJ11

A832Change 7

1F-16CJ-1-1-1053X

0.8

1.0

0

4

8

12

16

20

24

0

0.2

0.4

0.6

MACH NUMBER

TURN RA

TE   DEGREES/SECOND

1.2

QUICKEST TURN

(22.2 DEGREES/SECOND)

TIGHTEST TURN

(RADIUS =

1449 FEET)

MAXIMUM AIRSPEED

-4

-2

0

  TURN RA

TE

(DEGREES/SECOND)

GW   1000 POUNDS

GW EFFECT

22

24

26

  TURN RA

TE

(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

0

10

20

Turn Performance    5000 Feet

DATA BASIS FLIGHT TEST

CONFIGURATION:

CONDITIONS:

ENGINE F100-PW-229

STANDARD DAY

MIL

NOTE:  REFER TO SECTION V FOR AIRSPEED LIMITATIONS.

DRAG INDEX = 0

GW = 22,000 POUNDS

28

3
2

1

-1

-2
-3

10

20

-20

-10

Figure A815.

T.O. GR1F16CJ11

Change 7A833

1F-16CJ-1-1-1054X

1.1

1.0

0.9

TURN RADIUS F

ACTOR

RADIUS TEMP EFFECT

TEMP DEV FROM STD DAY   C

-20

-10

0

10

20

Turn Performance    10,000 Feet

DATA BASIS FLIGHT TEST

CONFIGURATION:

CONDITIONS:

ENGINE F100-PW-229

STANDARD DAY

MIL

NOTE:  REFER TO SECTION V FOR AIRSPEED LIMITATIONS.

DRAG INDEX = 0

GW = 22,000 POUNDS

-4

-2

0

  TURN RA

TE

(DEGREES/SECOND)

GW   1000 POUNDS

GW EFFECT

22

24

26

  TURN RA

TE

(DEGREES/SECOND)

TEMP DEV FROM

STD DAY    C

TEMPERATURE EFFECT

24

20

16

12

8

4

0

0

0.2

0.4

0.6

0.8

1.0

1.2

MACH NUMBER

TURN RA

TE   DEGREES/SECOND

QUICKEST TURN

(20.3 DEGREES/SECOND)

MAXIMUM AIRSPEED

TIGHTEST TURN

(RADIUS =

1723 FEET)

28

3
2

1

-1

-2
-3

10

20

-20

-10

Figure A816.

T.O. GR1F16CJ11

A834Change 7

1F-16CJ-1-1-1055X

0.8

1.0

0

4

8

12

16

20

24

0

0.2

0.4

0.6

MACH NUMBER

TURN RA

TE   DEGREES/SECOND

1.2

QUICKEST TURN

(18.6 DEGREES/SECOND)

MAXIMUM AIRSPEED

TIGHTEST TURN

(RADIUS =

2067 FEET)

-4

-2

0

  TURN RA

TE

(DEGREES/SECOND)

GW   1000 POUNDS

GW EFFECT

22

24

26

  TURN RA

TE

(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

0

10

20

Turn Performance    15,000 Feet

DATA BASIS FLIGHT TEST

CONFIGURATION:

CONDITIONS:

ENGINE F100-PW-229

STANDARD DAY

MIL

NOTE:  REFER TO SECTION V FOR AIRSPEED LIMITATIONS.

DRAG INDEX = 0

GW = 22,000 POUNDS

28

3
2

1

-1

-2
-3

10

20

-20

-10

Figure A817.

T.O. GR1F16CJ11

Change 7A835

1F-16CJ-1-1-1056X

0.8

1.0

0

4

8

12

16

20

24

0

0.2

0.4

0.6

MACH NUMBER

TURN RA

TE   DEGREES/SECOND

1.2

QUICKEST TURN

(17.1 DEGREES/SECOND)

TIGHTEST TURN

(RADIUS =

2491 FEET)

MAXIMUM AIRSPEED

1.1

1.0

0.9

TURN RADIUS F

ACTOR

RADIUS TEMP EFFECT

TEMP DEV FROM STD DAY   C

-20

-10

0

10

20

  TURN RA

TE

(DEGREES/SECOND)

TEMP DEV FROM

STD DAY    C

TEMPERATURE EFFECT

-4

-2

0

  TURN RA

TE

(DEGREES/SECOND)

GW   1000 POUNDS

GW EFFECT

22

24

26

Turn Performance    20,000 Feet

DATA BASIS FLIGHT TEST

CONFIGURATION:

CONDITIONS:

ENGINE F100-PW-229

STANDARD DAY

MIL

NOTE:  REFER TO SECTION V FOR AIRSPEED LIMITATIONS.

DRAG INDEX = 0

GW = 22,000 POUNDS

28

3
2

1

-1

-2
-3

10

20

-20

-10

Figure A818.

T.O. GR1F16CJ11

A836Change 7

1F-16CJ-1-1-1057X

0.8

1.0

0

4

8

12

16

20

24

0

0.2

0.4

0.6

MACH NUMBER

TURN RA

TE   DEGREES/SECOND

1.2

MAXIMUM AIRSPEED

QUICKEST TURN

(15.6 DEGREES/SECOND)

TIGHTEST TURN

(RADIUS =

3009 FEET)

1.1

1.0

0.9

TURN RADIUS F

ACTOR

RADIUS TEMP EFFECT

TEMP DEV FROM STD DAY   C

-20

-10

0

10

20

Turn Performance    25,000 Feet

DATA BASIS FLIGHT TEST

CONFIGURATION:

CONDITIONS:

ENGINE F100-PW-229

STANDARD DAY

MIL

NOTE:  REFER TO SECTION V FOR AIRSPEED LIMITATIONS.

DRAG INDEX = 0

GW = 22,000 POUNDS

-4

-2

0

  TURN RA

TE

(DEGREES/SECOND)

GW   1000 POUNDS

GW EFFECT

22

24

26

  TURN RA

TE

(DEGREES/SECOND)

TEMP DEV FROM

STD DAY    C

TEMPERATURE EFFECT

28

3
2

1

-1

-2
-3

10

20

-20

-10

Figure A819.

T.O. GR1F16CJ11

Change 7A837

1F-16CJ-1-1-1058X

0.8

1.0

0

4

8

12

16

20

24

0

0.2

0.4

0.6

MACH NUMBER

TURN RA

TE   DEGREES/SECOND

1.2

1.1

1.0

0.9

TURN RADIUS F

ACTOR

RADIUS TEMP EFFECT

TEMP DEV FROM STD DAY   C

-20

-10

0

10

20

Turn Performance    30,000 Feet

DATA BASIS FLIGHT TEST

CONFIGURATION:

CONDITIONS:

ENGINE F100-PW-229

STANDARD DAY

MIL

NOTE:  REFER TO SECTION V FOR AIRSPEED LIMITATIONS.

DRAG INDEX = 0

GW = 22,000 POUNDS

-4

-2

0

  TURN RA

TE

(DEGREES/SECOND)

GW   1000 POUNDS

GW EFFECT

22

24

26

  TURN RA

TE

(DEGREES/SECOND)

3
2

1

-1

-2
-3

10

20

-20

-10

TEMP DEV FROM

STD DAY    C

TEMPERATURE EFFECT

28

Figure A820.

T.O. GR1F16CJ11

A838Change 7

1F-16CJ-1-1-1059X

0.8

1.0

0

4

8

12

16

20

24

0

0.2

0.4

0.6

MACH NUMBER

TURN RA

TE   DEGREES/SECOND

1.2

QUICKEST TURN

(22.0 DEGREES/SECOND)

MAXIMUM AIRSPEED

TIGHTEST TURN

(RADIUS =

1473 FEET)

Turn Performance    Sea Level

DATA BASIS FLIGHT TEST

CONFIGURATION:

CONDITIONS:

ENGINE F100-PW-229

STANDARD DAY

MIL

NOTE:  REFER TO SECTION V FOR AIRSPEED LIMITATIONS.

DRAG INDEX = 50

GW = 26,000 POUNDS

-4

-2

0

  TURN RA

TE

(DEGREES/SECOND)

GW   1000 POUNDS

GW EFFECT

26

28

30

  TURN RA

TE

(DEGREES/SECOND)

3
2

1

-1

-2
-3

10

20

-20

-10

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

0

10

20

32

Figure A821.

T.O. GR1F16CJ11

Change 7A839

1F-16CJ-1-1-1060X

0.8

1.0

0

4

8

12

16

20

24

0

0.2

0.4

0.6

MACH NUMBER

TURN RA

TE   DEGREES/SECOND

1.2

MAXIMUM AIRSPEED

QUICKEST TURN

(18.6 DEGREES/SECOND)

TIGHTEST TURN

(RADIUS =

2075 FEET)

Turn Performance    10,000 Feet

DATA BASIS FLIGHT TEST

CONFIGURATION:

CONDITIONS:

ENGINE F100-PW-229

STANDARD DAY

MIL

NOTE:  REFER TO SECTION V FOR AIRSPEED LIMITATIONS.

DRAG INDEX = 50

GW = 26,000 POUNDS

-4

-2

0

  TURN RA

TE

(DEGREES/SECOND)

GW   1000 POUNDS

GW EFFECT

26

28

30

  TURN RA

TE

(DEGREES/SECOND)

3
2

1

-1

-2
-3

10

20

-20

-10

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

0

10

20

32

Figure A822.

T.O. GR1F16CJ11

A840Change 7

1F-16CJ-1-1-1061X

0.8

1.0

0

4

8

12

16

20

24

0

0.2

0.4

0.6

MACH NUMBER

TURN RA

TE   DEGREES/SECOND

1.2

MAXIMUM AIRSPEED

QUICKEST TURN

(15.6 DEGREES/SECOND)

TIGHTEST TURN

(RADIUS =

2984 FEET)

Turn Performance    20,000 Feet

DATA BASIS FLIGHT TEST

CONFIGURATION:

CONDITIONS:

ENGINE F100-PW-229

STANDARD DAY

MIL

NOTE:  REFER TO SECTION V FOR AIRSPEED LIMITATIONS.

DRAG INDEX = 50

GW = 26,000 POUNDS

-4

-2

0

  TURN RA

TE

(DEGREES/SECOND)

GW   1000 POUNDS

GW EFFECT

26

28

30

  TURN RA

TE

(DEGREES/SECOND)

3
2

1

-1

-2
-3

10

20

-20

-10

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

0

10

20

32

Figure A823.

T.O. GR1F16CJ11

Change 7A841

1F-16CJ-1-1-1062X

0.8

1.0

0

4

8

12

16

20

24

0

0.2

0.4

0.6

MACH NUMBER

TURN RA

TE   DEGREES/SECOND

1.2

MAXIMUM AIRSPEED

QUICKEST TURN

(12.2 DEGREES/SECOND)

TIGHTEST TURN

(RADIUS =

4354 FEET)

-4

-2

0

  TURN RA

TE

(DEGREES/SECOND)

GW   1000 POUNDS

GW EFFECT

26

28

30

  TURN RA

TE

(DEGREES/SECOND)

3
2

1

-1

-2
-3

10

20

-20

-10

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

0

10

20

Turn Performance    30,000 Feet

DATA BASIS FLIGHT TEST

CONFIGURATION:

CONDITIONS:

ENGINE F100-PW-229

STANDARD DAY

MIL

NOTE:  REFER TO SECTION V FOR AIRSPEED LIMITATIONS.

DRAG INDEX = 50

GW = 26,000 POUNDS

1

2

3

4

5

6

-2000

-1600

32

Figure A824.

T.O. GR1F16CJ11

A842Change 7

1F-16CJ-1-1-1063X

0.8

1.0

0

4

8

12

16

20

24

0

0.2

0.4

0.6

MACH NUMBER

TURN RA

TE   DEGREES/SECOND

1.2

MAXIMUM AIRSPEED

TIGHTEST TURN

(RADIUS =

1473 FEET)

QUICKEST TURN

(22.0 DEGREES/SECOND)

-4

-2

0

  TURN RA

TE

(DEGREES/SECOND)

GW   1000 POUNDS

GW EFFECT

26

30

34

38

  TURN RA

TE

(DEGREES/SECOND)

3
2

1

-1

-2
-3

10

20

-20

-10

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

0

10

20

Turn Performance    Sea Level

DATA BASIS FLIGHT TEST

CONFIGURATION:

ENGINE F100-PW-229

NOTE:  REFER TO SECTION V FOR AIRSPEED LIMITATIONS.

DRAG INDEX = 100

GW = 26,000 POUNDS

CONDITIONS:

STANDARD DAY

MIL

Figure A825.

T.O. GR1F16CJ11

Change 7A843

1F-16CJ-1-1-1064X

-4

-2

0

  TURN RA

TE

(DEGREES/SECOND)

GW   1000 POUNDS

GW EFFECT

26

30

34

38

  TURN RA

TE

(DEGREES/SECOND)

3
2

1

-1

-2
-3

10

20

-20

-10

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

0

10

20

0.8

1.0

0

4

8

12

16

20

24

0

0.2

0.4

0.6

MACH NUMBER

TURN RA

TE   DEGREES/SECOND

1.2

TIGHTEST TURN

(RADIUS =

QUICKEST TURN

(18.6 DEGREES/SECOND)

Turn Performance    10,000 Feet

DATA BASIS FLIGHT TEST

CONFIGURATION:

CONDITIONS:

ENGINE F100-PW-229

STANDARD DAY

MIL

NOTE:  REFER TO SECTION V FOR AIRSPEED LIMITATIONS.

DRAG INDEX = 100

GW = 26,000 POUNDS

MAXIMUM AIRSPEED

2075 FEET)

Figure A826.

T.O. GR1F16CJ11

A844Change 7

1F-16CJ-1-1-1065X

0.8

1.0

0

4

8

12

16

20

24

0

0.2

0.4

0.6

MACH NUMBER

TURN RA

TE   DEGREES/SECOND

1.2

MAXIMUM AIRSPEED

TIGHTEST TURN

(RADIUS =

QUICKEST TURN

(15.6 DEGREES/SECOND)

-4

-2

0

  TURN RA

TE

(DEGREES/SECOND)

GW   1000 POUNDS

GW EFFECT

26

30

34

38

  TURN RA

TE

(DEGREES/SECOND)

3
2

1

-1

-2
-3

10

20

-20

-10

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

0

10

20

Turn Performance    20,000 Feet

DATA BASIS FLIGHT TEST

CONFIGURATION:

CONDITIONS:

ENGINE F100-PW-229

STANDARD DAY

MIL

NOTE:  REFER TO SECTION V FOR AIRSPEED LIMITATIONS.

DRAG INDEX = 100

GW = 26,000 POUNDS

2985 FEET)

Figure A827.

T.O. GR1F16CJ11

Change 7A845

1F-16CJ-1-1-1066X

-4

-2

0

  TURN RA

TE

(DEGREES/SECOND)

GW   1000 POUNDS

GW EFFECT

26

30

34

38

  TURN RA

TE

(DEGREES/SECOND)

3
2

1

-1

-2
-3

10

20

-20

-10

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

0

10

20

0.8

1.0

0

4

8

12

16

20

24

0

0.2

0.4

0.6

MACH NUMBER

TURN RA

TE   DEGREES/SECOND

1.2

TIGHTEST TURN

(RADIUS =

QUICKEST TURN

(11.9 DEGREES/SECOND)

MAXIMUM AIRSPEED

Turn Performance    30,000 Feet

DATA BASIS FLIGHT TEST

CONFIGURATION:

CONDITIONS:

ENGINE F100-PW-229

STANDARD DAY

MIL

NOTE:  REFER TO SECTION V FOR AIRSPEED LIMITATIONS.

DRAG INDEX = 100

GW = 26,000 POUNDS

4355 FEET)

Figure A828.