F16C/D. FLIGHT MANUAL (2002) - page 62

 

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F16C/D. FLIGHT MANUAL (2002) - page 62

 

 

T.O. GR1F16CJ11

A846Change 7

1F-16CJ-1-1-1067X

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 =

1602 FEET)

QUICKEST TURN

(21.1 DEGREES/SECOND)

MAXIMUM AIRSPEED

-4

-2

0

  TURN RA

TE

(DEGREES/SECOND)

GW   1000 POUNDS

GW EFFECT

28

32

36

40

  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:

CONDITIONS:

ENGINE F100-PW-229

STANDARD DAY

MIL

NOTE:  REFER TO SECTION V FOR AIRSPEED LIMITATIONS.

DRAG INDEX = 150

GW = 28,000 POUNDS

Figure A829.

T.O. GR1F16CJ11

Change 7A847

1F-16CJ-1-1-1068X

-4

-2

0

  TURN RA

TE

(DEGREES/SECOND)

GW   1000 POUNDS

GW EFFECT

28

32

36

40

  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

QUICKEST TURN

(17.8 DEGREES/SECOND)

TIGHTEST TURN

(RADIUS =

MAXIMUM AIRSPEED

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 = 150

GW = 28,000 POUNDS

2252 FEET)

Figure A830.

T.O. GR1F16CJ11

A848Change 7

1F-16CJ-1-1-1069X

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

(14.9 DEGREES/SECOND)

TIGHTEST TURN

(RADIUS =

3231 FEET)

-4

-2

0

  TURN RA

TE

(DEGREES/SECOND)

GW   1000 POUNDS

GW EFFECT

40

36

32

28

  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 = 150

GW = 28,000 POUNDS

Figure A831.

T.O. GR1F16CJ11

Change 7A849

1F-16CJ-1-1-1070X

0.8

1.0

0

4

8

12

16

20

24

0.0

0.2

0.4

0.6

MACH NUMBER

TURN RA

TE   DEGREES/SECOND

1.2

MAXIMUM AIRSPEED

QUICKEST TURN

(10.9 DEGREES/ SECOND)

TIGHTEST TURN

(RADIUS =

4707 FEET)

-4

-2

0

  TURN RA

TE

(DEGREES/SECOND)

GW   1000 POUNDS

GW EFFECT

40

36

32

28

  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 = 150

GW = 28,000 POUNDS

Figure A832.

T.O. GR1F16CJ11

A850Change 7

1F-16CJ-1-1-1071X

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 =

1602 FEET)

QUICKEST TURN

(21.1 DEGREES/SECOND)

-4

-2

0

  TURN RA

TE

(DEGREES/SECOND)

GW   1000 POUNDS

GW EFFECT

40

36

32

28

  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:

CONDITIONS:

ENGINE F100-PW-229

STANDARD DAY

MIL

NOTE:  REFER TO SECTION V FOR AIRSPEED LIMITATIONS.

DRAG INDEX = 200

GW = 28,000 POUNDS

Figure A833.

T.O. GR1F16CJ11

Change 7A851

1F-16CJ-1-1-1072X

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

(17.8 DEGREES/SECOND)

TIGHTEST TURN

(RADIUS =

2252 FEET)

-4

-2

0

  TURN RA

TE

(DEGREES/SECOND)

GW   1000 POUNDS

GW EFFECT

40

36

32

28

  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    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 = 200

GW = 28,000 POUNDS

Figure A834.

T.O. GR1F16CJ11

A852Change 7

1F-16CJ-1-1-1073X

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

(14.8 DEGREES/SECOND)

MAXIMUM AIRSPEED

-4

-2

0

  TURN RA

TE

(DEGREES/SECOND)

GW   1000 POUNDS

GW EFFECT

28

32

36

40

  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 = 200

GW = 28,000 POUNDS

3231 FEET)

Figure A835.

T.O. GR1F16CJ11

Change 7A853

1F-16CJ-1-1-1074X

0.8

1.0

0

4

8

12

16

20

24

0.0

0.2

0.4

0.6

MACH NUMBER

TURN RA

TE   DEGREES/SECOND

1.2

QUICKEST TURN

(10.7 DEGREES/SECOND)

MAXIMUM AIRSPEED

-4

-2

0

  TURN RA

TE

(DEGREES/SECOND)

GW   1000 POUNDS

GW EFFECT

28

32

36

40

  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 = 200

GW = 28,000 POUNDS

TIGHTEST TURN

(RADIUS =

4707 FEET)

Figure A836.

T.O. GR1F16CJ11

A854Change 7

1F-16CJ-1-1-1075X

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

1.4

LIMIT AIRSPEED

QUICKEST TURN

(24.8 DEGREES/SECOND)

TIGHTEST TURN

(RADIUS =

1082 FEET)

C

H

-4

-2

0

  TURN RA

TE

(DEGREES/SECOND)

GW   1000 POUNDS

GW EFFECT

22

24

26

D

E

  TURN RA

TE

(DEGREES/SECOND)

3
2

1

-1

-2
-3

10

20

-20

-10

TEMP DEV FROM

STD DAY    C

TEMPERATURE EFFECT

F

A

1.1

1.0

0.9

TURN RADIUS F

ACTOR

RADIUS TEMP EFFECT

TEMP DEV FROM STD DAY   C

-20

-10

0

10

20

J

Turn Performance    Sea Level

DATA BASIS FLIGHT TEST

CONFIGURATION:

CONDITIONS:

ENGINE F100-PW-229

STANDARD DAY

MAX AB

NOTE:  REFER TO SECTION V FOR AIRSPEED LIMITATIONS.

DRAG INDEX = 0

GW = 22,000 POUNDS

F

28

A

B

I

A

G

Figure A837.

T.O. GR1F16CJ11

Change 7A855

1F-16CJ-1-1-1076X

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

1.4

TIGHTEST TURN

(RADIUS =

1320 FEET)

QUICKEST TURN

(22.7 DEGREES/SECOND)

LIMIT AIRSPEED

-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

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

MAX AB

NOTE:  REFER TO SECTION V FOR AIRSPEED LIMITATIONS.

DRAG INDEX = 0

GW = 22,000 POUNDS

28

Figure A838.

T.O. GR1F16CJ11

A856Change 7

1F-16CJ-1-1-1077X

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

1.4

1.6

LIMIT AIRSPEED

TIGHTEST TURN

(RADIUS =

1588 FEET)

QUICKEST TURN

(20.8 DEGREES/SECOND)

-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

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

MAX AB

NOTE:  REFER TO SECTION V FOR AIRSPEED LIMITATIONS.

DRAG INDEX = 0

GW = 22,000 POUNDS

-800

28

Figure A839.

T.O. GR1F16CJ11

Change 7A857

1F-16CJ-1-1-1078X

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

1.4

1.6

LIMIT AIRSPEED

QUICKEST TURN

(19.0 DEGREES/SECOND)

TIGHTEST TURN

(RADIUS =

-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

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

MAX AB

NOTE:  REFER TO SECTION V FOR AIRSPEED LIMITATIONS.

DRAG INDEX = 0

GW = 22,000 POUNDS

28

1938 FEET)

Figure A840.

T.O. GR1F16CJ11

A858Change 7

1F-16CJ-1-1-1079X

0.8

1.0

0

4

8

12

16

20

24

0.2

0.4

0.6

MACH NUMBER

TURN RA

TE   DEGREES/SECOND

1.2

1.4

1.6

LIMIT AIRSPEED

QUICKEST TURN

(17.4 DEGREES/SECOND)

TIGHTEST TURN

(RADIUS =

2365 FEET)

-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

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

MAX AB

NOTE:  REFER TO SECTION V FOR AIRSPEED LIMITATIONS.

DRAG INDEX = 0

GW = 22,000 POUNDS

1.8

28

Figure A841.

T.O. GR1F16CJ11

Change 7A859

1F-16CJ-1-1-1080X

1.0

1.2

0

4

8

12

16

20

0.2

0.4

0.6

0.8

MACH NUMBER

TURN RA

TE   DEGREES/SECOND

1.4

1.6

1.8

MAXIMUM AIRSPEED

TIGHTEST TURN

(RADIUS =

2890 FEET)

(15.8 DEGREES/SECOND)

-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

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

MAX AB

NOTE:  REFER TO SECTION V FOR AIRSPEED LIMITATIONS.

DRAG INDEX = 0

GW = 22,000 POUNDS

24

QUICKEST TURN

28

Figure A842.

T.O. GR1F16CJ11

A860Change 7

1F-16CJ-1-1-1081X

1.0

1.2

0

4

8

12

16

20

24

0.4

0.6

0.8

MACH NUMBER

TURN RA

TE   DEGREES/SECOND

1.4

1.6

1.8

MAXIMUM AIRSPEED

QUICKEST TURN

(14.4 DEGREES/SECOND)

TIGHTEST TURN

(RADIUS =

3538 FEET)

-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

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

MAX AB

NOTE:  REFER TO SECTION V FOR AIRSPEED LIMITATIONS.

DRAG INDEX = 0

GW = 22,000 POUNDS

28

Figure A843.

T.O. GR1F16CJ11

Change 7A861

1F-16CJ-1-1-1082X

-4

-2

0

  TURN RA

TE

(DEGREES/SECOND)

GW   1000 POUNDS

GW EFFECT

22

24

28

  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

1.8

0.4

0.6

MACH NUMBER

TURN RA

TE   DEGREES/SECOND

1.2

1.4

1.6

QUICKEST TURN

(12.2 DEGREES/SECOND)

TIGHTEST TURN

(RADIUS =

MAXIMUM AIRSPEED

Turn Performance    35,000 Feet

DATA BASIS FLIGHT TEST

CONFIGURATION:

CONDITIONS:

ENGINE F100-PW-229

STANDARD DAY

MAX AB

NOTE:  REFER TO SECTION V FOR AIRSPEED LIMITATIONS.

DRAG INDEX = 0

GW = 22,000 POUNDS

2.0

26

4343 FEET)

MAX AFT STICK

Figure A844.

 

 

 

 

 

 

 

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