Content .. 71 72 73 74 ..

F16C/D. FLIGHT MANUAL (2002) - page 73

T.O. GR1F16CJ11

Change 3B79/(B710 blank)

GR1F-16CJ-1-1-4048A37

Short Field Landing Distance SEC With

CORRECTED GROUND ROLL DISTANCE 1000 FEET

UNCORRECTED GROUND ROLL DIST

ANCE 1000 FEET

BASELINE

ON AN ICY RUNWAY

(RCR=4) WITH SEC,

THE STOPPING DISTANCE

WITH ZERO HEADWIND

MAY EXCEED 12,000

Drag Chute (Corrected)

2
3

WIND

KNOTS

SLOPE

DATA BASIS ESTIMATED

CONFIGURATION:

CONDITIONS:

ENGINE F110-GE-129

TOUCHDOWN AT 13 DEGREES AOA

ALL DRAG INDEXES

SPEEDBRAKES OPEN

IDLE SELECTED AT TOUCHDOWN

MAX EFFORT BRAKING

ENTER CHART WITH UNCORRECTED GROUND

ROLL DISTANCE FROM SHEET 4

DRAG CHUTE DEPLOYED

BELOW 170 KIAS

DEPLOYING THE DRAG

CHUTE AT AIRSPEEDS

GREATER THAN 170

KIAS MAY RESULT IN

LOSS OF THE CHUTE

CANOPY.

FEET.

Figure B72.(Sheet 6)

T.O. GR1F16CJ11

Change 3B81

PART 8-COMBAT

TABLE OF CONTENTS

Page

Combat Ceilings and Optimum Cruise

Altitude

B82

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

Level Flight Combat Speeds

and Altitudes

B83

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

Level Flight Combat Speed

B83

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

Fuel Flow (MIL and MAX AB)

B83

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

MIL Acceleration

B83

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

MAX AB Acceleration

B84

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

Turn Performance

B84

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

Deceleration

B85

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

LIST OF CHARTS

Figure

Page

Combat Ceilings and Opti

mum Cruise Altitude

B81

B86

. . . .

Level Flight Combat Speeds

and Altitudes (MIL/MAX

AB)

B82

B87

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

. . . .

Level Flight Combat Speed

(MIL/MAX AB)

B83

B811

. . . . . . . . .

. . . .

Fuel Flow (MIL/MAX AB)

B84

B812

. . .

. . . .

MIL Accelerations-Sea

Level

B85

B813

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

. . . .

MIL Accelerations-10,000

Feet

B86

B815

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

. . . .

MIL Accelerations-20,000

Feet

B87

B817

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

. . . .

MIL Accelerations-30,000

Feet

B88

B819

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

. . . .

MAX AB Accelerations-Sea

Level

B89

B821

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

. . . .

MAX AB Accelerations-

10,000 Feet

B810

B823

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

. . . .

MAX AB Accelerations-

20,000 Feet

B811

B825

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

. . . .

MAX AB Accelerations-

30,000 Feet

B812

B827

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

. . . .

MAX AB Accelerations-

40,000 Feet

B813

B829

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

. . . .

MIL:

Drag index = 0

Turn Performance-Sea

Level

B814

B831

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

. . . .

Turn Performance-5000

Feet

B815

B832

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

. . . .

Turn Performance-10,000

Feet

B816

B833

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

. . . .

Turn Performance-15,000

Feet

B817

B834

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

. . . .

Figure

Page

Turn Performance-20,000

Feet

B818

B835

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

. . . .

Turn Performance-25,000

Feet

B819

B836

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

. . . .

Turn Performance-30,000

Feet

B820

B837

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

. . . .

MIL:

Drag index = 50

Turn Performance-Sea

Level

B821

B838

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

. . . .

Turn Performance-10,000

Feet

B822

B839

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

. . . .

Turn Performance-20,000

Feet

B823

B840

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

. . . .

Turn Performance-30,000

Feet

B824

B841

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

. . . .

MIL:

Drag index = 100

Turn Performance-Sea

Level

B825

B842

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

. . . .

Turn Performance-10,000

Feet

B826

B843

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

. . . .

Turn Performance-20,000

Feet

B827

B844

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

. . . .

Turn Performance-30,000

Feet

B828

B845

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

. . . .

MIL:

Drag index = 150

Turn Performance-Sea

Level

B829

B846

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

. . . .

Turn Performance-10,000

Feet

B830

B847

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

. . . .

Turn Performance-20,000

Feet

B831

B848

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

. . . .

Turn Performance-30,000

Feet

B832

B849

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

. . . .

MIL:

Drag index = 200

Turn Performance-Sea

Level

B833

B850

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

. . . .

Turn Performance-10,000

Feet

B834

B851

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

. . . .

Turn Performance-20,000

Feet

B835

B852

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

. . . .

Turn Performance-30,000

Feet

B836

B853

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

. . . .

T.O. GR1F16CJ11

B82Change 3

Figure

Page

MAX AB:

Drag index = 0

Turn Performance-Sea

Level

B837

B854

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

. . . .

Turn Performance-5000

Feet

B838

B855

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

. . . .

Turn Performance-10,000

Feet

B839

B856

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

. . . .

Turn Performance-15,000

Feet

B840

B857

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

. . . .

Turn Performance-20,000

Feet

B841

B858

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

. . . .

Turn Performance-25,000

Feet

B842

B859

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

. . . .

Turn Performance-30,000

Feet

B843

B860

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

. . . .

Turn Performance-35,000

Feet

B844

B861

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

. . . .

Turn Performance-40,000

Feet

B845

B862

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

. . . .

Turn Performance-45,000

Feet

B846

B863

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

. . . .

Turn Performance-50,000

Feet

B847

B864

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

. . . .

MAX AB:

Drag index = 50

Turn Performance-Sea

Level

B848

B865

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

. . . .

Turn Performance-10,000

Feet

B849

B866

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

. . . .

Turn Performance-20,000

Feet

B850

B867

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

. . . .

Turn Performance-30,000

Feet

B851

B868

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

. . . .

Turn Performance-40,000

Feet

B852

B869

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

. . . .

MAX AB:

Drag index = 100

Turn Performance-Sea

Level

B853

B870

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

. . . .

Turn Performance-10,000

Feet

B854

B871

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

. . . .

Turn Performance-20,000

Feet

B855

B872

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

. . . .

Turn Performance-30,000

Feet

B856

B873

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

. . . .

MAX AB:

Drag index = 150

Turn Performance-Sea

Level

B857

B874

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

. . . .

Turn Performance-10,000

Feet

B858

B875

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

. . . .

Figure

Page

Turn Performance-20,000

Feet

B859

B876

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

. . . .

Turn Performance-30,000

Feet

B860

B877

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

. . . .

MAX AB:

Drag index = 200

Turn Performance-Sea

Level

B861

B878

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

. . . .

Turn Performance-10,000

Feet

B862

B879

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

. . . .

Turn Performance-20,000

Feet

B863

B880

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

. . . .

Turn Performance-30,000

Feet

B864

B881

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

. . . .

Deceleration -20,000

Feet

B865

B882

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

. . . .

Deceleration -30,000

Feet

B865

B883

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

. . . .

Deceleration -40,000

Feet

B865

B884

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

. . . .

COMBAT CEILINGS AND OPTIMUM

CRUISE ALTITUDE

Combat ceiling and optimum cruise altitude data is

shown in figure B81. All data is based on use of opti

mum cruise mach number. Correction factors to

adjust MIL combat ceiling to cruise or service ceilings

are given on the chart.

REFER TO FIGURE B81.

For standard day, enter upper portion of the chart

with GW (A), proceed upward to drag index (B), and

then proceed to the left to read cruise altitude (C).

Enter lower portion of the chart with GW (A), proceed

upward to drag index (B), and then proceed to the left

to read combat ceiling (D).

For MIL cruise ceiling, add 650 feet to MIL combat

ceiling. For MIL service ceiling, add 1300 feet to MIL

combat ceiling.

SAMPLE PROBLEM.

A. GW

= 33,000 pounds

B. Drag index

= 150

C. Cruise altitude

= 34,900 feet

D. MIL combat ceiling

(500 fpm)

= 35,550 feet

MIL cruise ceiling

(300 fpm)

= 36,200 feet

MIL service ceiling

(100 fpm)

= 36,850 feet

T.O. GR1F16CJ11

Change 8B83

LEVEL FLIGHT COMBAT SPEEDS AND

ALTITUDES

Combat speed and altitude envelopes are shown in

figure B82 (sheets 1 through 4) for MIL and MAX AB.

All data shown reflects speed/altitude conditions

where 500 fpm climb potential remains at the speci

fied thrust setting.

REFER TO FIGURE B82, SHEET 1.

Enter the plot labeled with the appropriate drag

index with altitude (A), proceed to the right to GW (B),

and then down to read mach number (C). Reverse this

process to find maximum altitude.

SAMPLE PROBLEM.

Drag index

= 50

A. Altitude

= 40,000 feet

B. GW

= 24,000 pounds

C. Maximum mach:

MIL

= 0.95

MAX AB

= 1.9

For nonstandard day, use the adjustments noted in

figure B83 at or below 30,000 feet. For altitudes

above 30,000 feet, nonstandard day operations are

not shown since the altitude as well as mach number

is affected by temperature changes.

LEVEL FLIGHT COMBAT SPEED

Maximum speed capabilities for MIL and MAX AB

during level flight are provided as indicated airspeed

in tabular form in figure B83. The data is presented

as a function of altitude and drag index with tempera

ture effects shown as correction increments. No GW

effects are shown because speed capability is not sig

nificantly affected by weight in the altitude range

shown.

REFER TO FIGURE B83.

Enter the table with thrust, altitude, and drag index

and read indicated airspeed at standard day tempera

ture. The resulting value is the maximum attainable

airspeed in level flight under the given conditions.

Temperature corrections are found in the bottom half

of figure B83. Enter the table with altitude and drag

index and read the temperature correction. The

correction increments are given for a 20

C deviation

from standard. For other temperature deviations,

determine ratio of the table values.

SAMPLE PROBLEM.

Thrust

= MIL

Altitude

= 15,000 feet

Drag index

= 100

Maximum indicated

airspeed, standard

day

= 495 knots

Standard day tem

perature

= -15

Ambient temperature = -10

Temperature devi

ation

= 5

C hot

Indicated airspeed

for +20

C tempera

ture deviation at

15,000 feet and DI =

100

= -12 knots

Maximum indicated

airspeed for ambient

temperature of -10

C = 495-(12

5/20) =

492 knots

FUEL FLOW (MIL AND MAX AB)

Fuel flow data for MIL and MAX AB thrust is given

in figure B84. The data may be used to estimate fuel

consumption at combat conditions. For instance, a

MAX AB turn at 1.6 mach and 30,000 feet altitude

consumes 56,200 pounds of fuel per hour or (56,200

60) = 937 pounds of fuel every minute.

MIL ACCELERATION

MIL acceleration performance from 200 KIAS to com

bat speed is given in figures B85, B86, B87, and

B88 for sea level and 10,000, 20,000, and 30,000 feet

altitude, respectively. The data in these charts covers

the subsonic and transonic flight region for drag

indexes up to 250 and is presented as a function of

altitude, drag index, and GW with temperature

effects shown as factors.

REFER TO FIGURE B85, SHEET 1.

To find the time, distance, and fuel consumed in a

constant altitude acceleration, enter the table with

drag index, GW, and initial airspeed. Then read time/

distance/fuel consumed. Next, enter the table with

the final airspeed and read time/distance/fuel con

sumed. The difference between the two sets of data is

then the time/distance/fuel consumed for the accel

eration. Temperature effects factors are found on the

right side of each chart. Multiply the standard day

time/distance/fuel consumed initial and final condi

tions by their respective factors to get initial and final

T.O. GR1F16CJ11

B84Change 3

conditions for 20

C deviation from standard. To

compute the time/distance/fuel consumed for other

temperatures, simply ratio the difference between

standard day values and 20

C values for the partic

ular temperature deviation. The difference between

initial and final conditions is the time/distance/fuel

consumed in acceleration for nonstandard day tem

perature.

SAMPLE PROBLEM.

A. Altitude

= SL

B. Drag index

= 0

C. GW

= 20,000 pounds

D. Standard day tem

perature

= 15

E. Ambient temperature = 22

F. Temperature devi

ation

= 7

C hot

G. Initial airspeed

= 300 KIAS

H. Final airspeed

= 600 KIAS

FIND FUEL CONSUMED:

I. Fuel at initial condi

tion (STD)

= 28 pounds

J. Temperature effect

factor at +20

= 1.08

K. Fuel at initial condi

tion is 1.08

28 for

+20

= 30.2 pounds

L. Fuel at initial condi

tion for 7

C is 28 +

(2.2

)

= 28.8 pounds

M. Fuel at final condi

tions (STD)

= 143 pounds

N. Temperature effect

factor at +20

= 1.19

O. Fuel at final condi

tion is 1.19

143 for

+20

= 170.2 pounds

P. Fuel at initial condi

tion for 7

C is 143 +

(27.2

)

= 152.5 pounds

Q. Fuel consumed

(152.5-28.8)

= 123.7 pounds

The above method also applies to computing time and

range for the acceleration.

MAX AB ACCELERATION

MAX AB acceleration performance from 200 KIAS to

combat speed is given in figures B89, B810, B811,

B812, and B813 for sea level and 10,000, 20,000,

30,000, and 40,000 feet altitude, respectively. The

data in these charts covers the subsonic, transonic,

and supersonic flight region for drag indexes up to

250 and is presented as a function of altitude, drag

index, and GW with temperature effects shown as fac

tors. Refer to MIL ACCELERATION for procedures.

TURN PERFORMANCE

Figures B814 through B864 contain constant alti

tude and drag index turn performance data plotted

versus mach for lines of constant energy rate (Ps).

Lines of load factor and turn radius are superimposed

on each chart. Correction insets containing GW and

temperature effects are also included on each chart.

Altitudes range from sea level to 30,000 feet for MIL

standard day thrust and sea level to 50,000 feet for

MAX AB standard day thrust. Both MIL and MAX AB

thrust charts contain drag indexes of 0 through 200

and varying GW's. The boundaries of the data are

defined by the CAT I or CAT III AOA limiters, load

factor limits, maximum aft stick limits, maximum

airspeed (Ps = 0 at 1g), and limit airspeed. Within

these boundaries, the data defines how much Ps

remains at any load factor, mach, or turn rate. On

figure B837, for instance, the Ps lines show that 0.9

mach is an ideal speed for maneuvering and increas

ing energy (climbing) simultaneously. At 9g, Ps is

almost 600 fps or an instantaneous rate of climb of

almost 36,000 fpm. At the same load factor, however,

turn radius can be reduced by making the turn at 0.70

mach while still maintaining airspeed and altitude

(Ps = 0). The quickest turn occurs at about 8g, 0.54

mach. Note, however, Ps is less than 0 (Ps < -500 fps)

indicating either speed or altitude must be decreased

to maintain the turn. In this case, the turn condition

is limited by the CAT I limiter. Speed decays at

constant altitude, and load factor decreases along the

CAT I limit line until Ps = 0 is reached at about 3.5g,

0.33 mach. The effects of varying GW's or nonstan

dard temperatures may also be included, as in the

example below. A close study of the turn performance

charts assists in forming a picture of the interrela

tionships between maneuverability, speed, altitude,

energy rate, etc.

T.O. GR1F16CJ11

Change 3B85

REFER TO FIGURE B837.

Enter the chart with mach number (A), proceed verti

cally to desired Ps (B), and proceed horizontally to

read turn rate (C). Enter GW Effect inset at desired

GW (D), proceed vertically to mach number (A), and

then left horizontally to read

∆

turn rate (E). Enter

Temperature Effect inset at temperature deviation

from standard day value (F), proceed vertically to

mach number (A), and then horizontally to read

∆

turn rate (G). Combine (E), (G), and (C) to obtain a

corrected turn rate (H). With the corrected turn rate,

proceed horizontally back to mach number (A) to

define the new location of the Ps line. Read the turn

radius (I). Enter Radius Temperature Effect inset at

standard temperature deviation value (F); proceed

vertically to line and then horizontally to read turn

radius factor (J). Multiply turn radius and turn

radius factor to obtain corrected turn radius (K).

NOTE

The accuracy of GW and temperature

corrections to turn rate is considerably

degraded when large (steep) Ps line

slopes are encountered.

SAMPLE PROBLEM.

A. Mach number

= 0.60

B. Ps

= 0 (level turn)

C. Turn rate

= 21.1 degrees/second

D. GW

= 24,000 pounds

∆

Turn rate

= -2.2 degrees/second

F. Temp dev from std

day

= +20

∆

Turn rate

= -2.6 degrees/second

H. Corrected turn rate =

21.1-2.2-2.6

= 16.3 degrees/second

(at Ps = 0)

I. Turn radius

= 2453 feet

J. Turn radius factor

= 1.069

K. Corrected turn

radius 2453

feet

1.069

= 2622 feet

DECELERATION

Level 1g deceleration performance is shown in figure

B865 for 20,000, 30,000, and 40,000 feet altitude,

respectively. Sufficient drag index lines are provided

to cover most supersonic loadings plus a line repre

senting speedbrakes open at aircraft drag index = 0.

REFER TO FIGURE B865, SHEET 1.

Enter top portion of chart with initial mach number

(A), proceed vertically to drag index (B), proceed hori

zontally to the right to weight baseline and follow

guidelines to GW (C), and finally proceed horizontally

to the right to read fuel consumed (D). Repeat this

process in the remaining portions of the chart to

determine distance (E) and time (F) to decelerate.

Repeat the entire procedure substituting final mach

for initial mach and subtract the result from the first

set of data to obtain fuel used, distance, and time to

decelerate from initial to final mach.

SAMPLE PROBLEM (20,000 FEET).

A. Initial mach

= 1.5

B. Drag index*

= 20

C. GW

= 22,000 pounds

D. Fuel used

= 58 pounds

E. Distance

= 14.2 nm

F. Time

= 1.6 minutes

* Example drag index

The above data is for a deceleration from 1.5 to 0.6

mach. If the deceleration is stopped at 0.7 mach:

G. Fuel used

= 58-8 = 50 pounds

H. Distance

= 14.2-2.7 = 11.5 nm

I. Time

= 1.6-0.4 = 1.2 minute

T.O. GR1F16CJ11

B86Change 3

1F-16CJ-1-1-4046A

DATA BASIS FLIGHT TEST

STANDARD DAY

CONDITIONS:

ENGINE F110-GE-129

OPTIMUM CRUISE MACH NUMBER

OPTIMUM CRUISE ALTITUDE

Combat Ceilings and Optimum Cruise

Altitude

COMBAT CEILING (500 FPM)

GW 1000 POUNDS

NOTE: FOR ALL DRAG INDEXES

+20 C OR -20 C OFF

STANDARD TEMPERATURE

EFFECTS ARE NEGLIGIBLE.

MIL

MAX AB

GW 1000 POUNDS

COMBA

T CEILING 1000 FEET

CRUISE AL

TITUDE 1000 FEET

NOTES:

FOR MIL CRUISE CEILING (300 FPM),

INCREASE ALTITUDE 650 FEET.

FOR MIL SERVICE CEILING (100 FPM),

INCREASE ALTITUDE 1300 FEET.

NOTE: FOR ALL DRAG INDEXES

+20 C OR -20 C OFF

STANDARD TEMPERATURE

EFFECTS ARE NEGLIGIBLE.

MACH

0.90

0.85

0.82

100

150

0.82

0.73

0.67

200

300

400

DRAG INDEX

OPTIMUM CRUISE

Figure B81.

T.O. GR1F16CJ11

Change 3B87

1F-16CJ-1-1-4047A

DATA BASIS FLIGHT TEST

ENGINE F110-GE-129

CONDITIONS:

Level Flight Combat Speeds and Altitudes

(MIL/MAX AB)

STANDARD DAY

500 FPM CLIMB POTENTIAL REMAINING
AT SPECIFIED THRUST

NOTES:

FOR NONSTANDARD DAY, REFER

TO FIGURE B8-3 TO ADJUST AIR-
SPEED BELOW 30,000 FEET. ABOVE
30,000 FEET, REFER TO TEXT.

REFER TO SECTION V FOR AIR-

SPEED LIMITATIONS.

0.4

0.8

1.2 0

0.4

0.8

1.2

1.6

2.0

0.4

0.8

1.2 0

0.4

0.8

1.2

1.6

2.0

TITUDE 1000 FEET

MACH NUMBER

MIL

MAX AB

LIMIT AIRSPEED

0.2

0.6

1.0

0.2

0.6

1.0

1.4

1.8

0.2

0.6

1.0

0.2

0.6

1.0

1.4

1.8

LIMIT

AIRSPEED

MACH NUMBER

DRAG INDEX = 0

MIL

MAX AB

DRAG INDEX = 0

DRAG INDEX = 50

Figure B82.(Sheet 1)

T.O. GR1F16CJ11

B88Change 3

Level Flight Combat Speeds and Altitudes

(MIL/MAX AB)

DATA BASIS FLIGHT TEST

ENGINE F110-GE-129

NOTES:

FOR NONSTANDARD DAY, REFER
TO FIGURE B8-3 TO ADJUST AIR-
SPEED BELOW 30,000 FEET. ABOVE
30,000 FEET, REFER TO TEXT.
REFER TO SECTION V FOR
AIRSPEED LIMITATIONS.

1F-16CJ-1-1-4048A

0.4

0.8

1.2

MACH NUMBER

TITUDE 1000 FEET

DRAG INDEX = 100

0.4

0.8

1.2

MACH NUMBER

TITUDE 1000 FEET

DRAG INDEX = 150

LIMIT AIRSPEED

0.4

0.8

1.2

1.6

2.0

DRAG INDEX = 100

LIMIT AIRSPEED

0.4

0.8

1.2

1.6

2.0

DRAG INDEX = 150

MACH NUMBER

MIL

MAX AB

MIL

CONDITIONS:

STANDARD DAY

500 FPM CLIMB POTENTIAL REMAINING
AT SPECIFIED THRUST

0.2

0.6

1.0

0.2

0.6

1.0

0.2

0.6

1.0

1.4

1.8

0.2

0.6

1.0

1.4

1.8

Figure B82.(Sheet 2)

T.O. GR1F16CJ11

Change 3B89

Level Flight Combat Speeds and Altitudes

(MIL/MAX AB)

DATA BASIS FLIGHT TEST

ENGINE F110-GE-129

NOTES:

FOR NONSTANDARD DAY, REFER
TO FIGURE B8-3 TO ADJUST AIR-
SPEED BELOW 30,000 FEET. ABOVE
30,000 FEET, REFER TO TEXT.
REFER TO SECTION V FOR
AIRSPEED LIMITATIONS.

1F-16CJ-1-1-4049A

0.4

0.8

1.2

MACH NUMBER

TITUDE 1000 FEET

DRAG INDEX = 200

0.4

0.8

1.2

MACH NUMBER

TITUDE 1000 FEET

DRAG INDEX = 250

LIMIT AIRSPEED

0.4

0.8

1.2

1.6

2.0

DRAG INDEX = 200

LIMIT AIRSPEED

0.4

0.8

1.2

1.6

2.0

DRAG INDEX = 250

MACH NUMBER

MIL

MAX AB

MIL

CONDITIONS:

STANDARD DAY

500 FPM CLIMB POTENTIAL REMAINING
AT SPECIFIED THRUST

0.2

0.6

1.0

0.2

0.6

1.0

0.2

0.6

1.0

1.4

1.8

0.2

0.6

1.0

1.4

1.8

Figure B82.(Sheet 3)

T.O. GR1F16CJ11

B810Change 3

0.4

0.8

1.2

MACH NUMBER

TITUDE 1000 FEET

LIMIT AIRSPEED

0.4

0.8

1.2

1.6

2.0

Level Flight Combat Speeds and Altitudes

(MIL/MAX AB)

DATA BASIS FLIGHT TEST

ENGINE F110-GE-129

NOTES:

FOR NONSTANDARD DAY, REFER
TO FIGURE B8-3 TO ADJUST AIR-
SPEED BELOW 30,000 FEET. ABOVE
30,000 FEET, REFER TO TEXT.
REFER TO SECTION V FOR
AIRSPEED LIMITATIONS.

MACH NUMBER

MIL

MAX AB

DRAG INDEX = 300

1F-16CJ-1-1-4050A

CONDITIONS:

STANDARD DAY

500 FPM CLIMB POTENTIAL REMAINING
AT SPECIFIED THRUST

0.2

0.6

1.0

0.2

0.6

1.0

1.4

1.8

Figure B82.(Sheet 4)

T.O. GR1F16CJ11

Change 3B811

Level Flight Combat Speed

(MIL/MAX AB)

DATA BASIS FLIGHT TEST

CONDITIONS:

ENGINE F110GE129

ALL GW'S

NOTE:REFER TO SECTION V FOR AIRSPEED LIMITATIONS.

MIL

STANDARD

INDICATED AIRSPEED - KNOTS

STANDARD

TEMPERATURE

°C

ALTITUDE

FEET

DRAG

INDEX0

100

150

200

250

300

+15

644

629

613

600

587

567

547

5,000

603

588

574

562

553

539

522

-5

10,000

563

548

536

524

514

507

493

-15

15,000

527

507

495

483

473

466

453

-25

20,000

464

452

441

432

425

-35

25,000

421

410

398

-44

30,000

377

INDICATED AIRSPEED - KNOTS

1/15

2/19

2/16

3/27

7/38

12/40

15/42

5,000

8/13

7/14

8/15

7/16

6/29

12/36

16/40

10,000

12/14

6/12

5/15

5/14

5/18

4/30

9/36

15,000

14/18

4/11

3/12

3/11

3/9

2/18

4/23

20,000

1/7

0/6

0/5

0/9

25,000

0/4

1/3

0/2

30,000

0/1

MAX AB

STANDARD

INDICATED AIRSPEED - KNOTS

STANDARD

TEMPERATURE

°C

ALTITUDE

FEET

DRAG

INDEX0

100

150

200

250

300

+15

**800

763

686

659

647

638

630

5,000

**800

793

723

636

612

601

592

-5

10,000

**800

790

716

650

576

561

552

-15

15,000

**800

776

705

635

544

521

512

-25

20,000

**800

758

691

614

562

484

471

-35

25,000

783

734

675

595

537

443

429

-44

30,000

752

708

657

579

386

INDICATED AIRSPEED - KNOTS

**0/28

14/76

7/29

3/15

2/13

2/14

2/15

5,000

**0/26

9/104

11/96

2/29

3/16

3/15

4/14

10,000

**0/27

**10/103

24/105

34/80

57/20

17/14

11/13

15,000

**0/40

**24/95

61/84

48/98

86/27

20/13

7/12

20,000

**0/63

**42/88

80/88

56/73

47/83

80/16

3/10

25,000

**17/72

**66/84

79/89

66/71

57/94

83/14

1/8

30,000

**48/72

80/79

86/90

82/81

0/4

TEMPERATURE DEVIATION FROM STANDARD = -20

C/+20

LIMIT AIRSPEED

Figure B83.

T.O. GR1F16CJ11

B812Change 8

Fuel Flow (MIL/MAX AB)

DATA BASIS FLIGHT TEST

ENGINE F110-GE-129

STANDARD DAY

CONDITIONS:

1F-16CJ-1-1-4051A

0.4

0.6

0.8

1.0

1.2

1.4

1.6

1.8

2.0

MAX AB FUEL FLOW 1000 POUNDS/HOUR

MAX AB

MACH NUMBER

MIL

ALTITUDE 1000 FEET

100

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1.0

MIL FUEL FLOW 1000 POUNDS/HOUR

MACH NUMBER

ALTITUDE 1000 FEET

Figure B84.

T.O. GR1F16CJ11

Change 3B813

MIL Accelerations Sea Level

DATA BASIS FLIGHT TEST

CONDITIONS

ENGINE F110GE129

STANDARD DAY TEMPERATURE (15

NOTE: REFER TO SECTION V FOR AIRSPEED LIMITATIONS.

TIME (SEC)/DISTANCE (NM)/FUEL (LB)

TEMP EFFECT FACTOR

KIAS

MACH

GW 20,000 LB

24,000 LB

28,000 LB

32,000 LB

36,000 LB

+20°C

-20°C

200

0.30

0/0/0

1.00/1.00/1.00

250

0.38

4/0.2/14

5/0.3/17

6/0.4/20

7/0.4/24

8/0.5/29

1.10/1.14/1.08

0.96/0.92/0.92

300

0.45

8/0.5/28

10/0.7/34

11/0.8/41

14/0.9/49

16/1.1/57

1.13/1.17/1.08

0.95/0.92/0.92

= 0

350

0.53

12/0.9/43

14/1.1/52

17/1.3/62

20/1.5/74

24/1.8/86

1.16/1.21/1.09

0.95/0.91/0.92

400

0.60

16/1.3/59

19/1.6/72

23/1.9/85

27/2.2/100

31/2.5/116

1.19/1.24/1.10

0.94/0.90/0.92

450

0.68

20/1.8/76

24/2.2/93

28/2.6/110

33/3.0/129

39/3.5/149

1.22/1.28/1.11

0.93/0.89/0.92

G I

500

0.76

24/2.4/95

29/2.9/116

35/3.4/137

40/3.9/160

47/4.5/185

1.25/1.31/1.13

0.91/0.87/0.92

550

0.83

29/3.1/117

35/3.7/142

42/4.4/168

48/5.1/196

56/5.9/225

1.28/1.36/1.15

0.90/0.85/0.91

600

0.91

35/4.0/143

42/4.8/174

50/5.7/205

57/6.6/238

66/7.5/272

1.33/1.43/1.19

0.89/0.85/0.90

CMBT SPD

52/7.0/225

62/8.3/268

72/9.6/311

82/10.9/355

93/12.3/401

1.31/1.36/1.14

0.91/0.87/0.91

CMBT SPD

KIAS/MACH

644/0.97

643/0.97

0.98/0.98

1.00/1.00

TIME (SEC)/DISTANCE (NM)/FUEL (LB)

TEMP EFFECT FACTOR

KIAS

MACH

GW 20,000 LB

24,000 LB

28,000 LB

32,000 LB

36,000 LB

+20°C

-20°C

200

0.30

0/0/0

1.00/1.00/1.00

250

0.38

4/0.2/14

5/0.3/17

6/0.4/21

7/0.4/25

9/05/30

1.10/1.14/1.08

0.96/0.92/0.92

300

0.45

8/0.5/28

10/0.7/35

12/0.8/42

14/1.0/50

16/1.1/59

1.13/1.17/1.08

0.95/0.92/0.92

= 5

350

0.53

12/0.9/44

15/1.1/54

17/1.3/64

21/1.6/75

24/1.8/88

1.16/1.21/1.09

0.95/0.91/0.92

400

0.60

16/1.3/61

20/1.6/74

23/1.9/88

27/2.3/103

32/2.6/120

1.20/1.25/1.11

0.94/0.90/0.92

450

0.68

20/1.9/79

25/2.3/96

30/2.7/114

35/3.1/134

40/3.6/155

1.23/1.29/1.12

0.93/0.89/0.92

500

0.76

25/2.5/100

31/3.0/122

36/3.6/145

43/4.2/169

49/4.8/194

1.27/1.34/1.15

0.91/0.86/0.91

550

0.83

31/3.3/126

38/4.0/153

44/4.8/181

52/5.5/210

60/6.3/241

1.32/1.40/1.18

0.89/0.84/0.90

600

0.91

38/4.5/159

46/5.4/193

55/6.4/227

63/7.4/263

73/8.4/302

1.44/1.56/1.28

0.88/0.83/0.89

CMBT SPD

57/7.7/246

67/9.1/293

78/10.5/340

90/11.9/388

101/13.4/437

1.23/1.25/1.07

0.87/0.83/0.87

CMBT SPD

KIAS/MACH

630/0.95

629/0.95

0.97/0.97

1.00/1.00

TIME (SEC)/DISTANCE (NM)/FUEL (LB)

TEMP EFFECT FACTOR

KIAS

MACH

GW 22,000 LB

26,000 LB

30,000 LB

34,000 LB

38,000 LB

+20°C

-20°C

200

0.30

0/0/0

1.00/1.00/1.00

250

0.38

4/0.3/16

5/0.3/19

7/0.4/23

8/0.5/28

10/0.6/33

1.11/1.15/1.08

0.96/0.92/0.92

300

0.45

9/0.6/32

11/0.8/39

13/0.9/46

15/1.1/55

18/1.3/65

1.13/1.18/1.09

0.95/0.92/0.92

350

0.53

14/1.0/50

16/1.2/60

19/1.5/71

23/1.7/84

27/2.0/98

1.17/1.22/1.10

0.95/0.91/0.92

EX =

400

0.60

18/1.5/69

22/1.8/83

26/2.2/98

30/2.5/115

35/2.9/133

1.21/1.26/1.12

0.94/0.90/0.92

450

0.68

24/2.1/91

28/2.6/110

33/3.0/129

39/3.5/150

45/4.0/173

1.25/1.31/1.14

0.92/0.88/0.92

500

0.76

30/2.9/118

35/3.5/141

42/4.1/166

48/4.8/192

56/5.5/220

1.30/1.38/1.17

0.90/0.85/0.90

RAG

550

0.83

37/4.0/151

44/4.8/181

52/5.6/212

60/6.5/244

69/7.4/280

1.38/1.48/1.24

0.88/0.83/0.89

600

0.91

48/5.8/203

57/6.9/242

67/8.1/282

77/9.3/325

88/10.5/370

0.86/0.81/0.87

CMBT SPD

63/8.3/271

74/9.7/318

85/11.1/366

97/12.5/415

109/14.0/466

1.40/1.47/1.23

0.88/0.85/0.89

CMBT SPD

KIAS/MACH

613/0.93

0.97/0.97

1.00/1.00

Figure B85.(Sheet 1)

T.O. GR1F16CJ11

B814Change 3

MIL Accelerations Sea Level

DATA BASIS FLIGHT TEST

CONDITIONS

ENGINE F110GE129

STANDARD DAY TEMPERATURE (15

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

0.30

0/0/0

1.00/1.00/1.00

250

0.38

5/0.3/17

6/0.4/21

7/0.5/26

9/0.6/31

11/0.7/37

1.11/1.15/1.08

0.96/0.92/0.92

300

0.45

10/0.7/36

12/0.8/43

14/1.0/52

17/1.2/61

20/1.4/72

1.14/1.18/1.09

0.95/0.92/0.92

350

0.53

15/1.2/56

18/1.4/67

22/1.6/79

25/1.9/93

30/2.2/109

1.18/1.23/1.11

0.95/0.91/0.92

X =

400

0.60

21/1.7/79

25/2.1/94

29/2.4/110

34/2.8/128

39/3.3/149

1.22/1.28/1.13

0.94/0.90/0.92

450

0.68

27/2.5/105

32/2.9/125

38/3.4/146

44/4.0/169

50/4.5/195

1.27/1.34/1.16

0.92/0.88/0.91

500

0.76

34/3.5/137

41/4.1/163

48/4.8/190

55/5.5/219

63/6.3/251

1.34/1.43/1.21

0.89/0.85/0.90

RAG

550

0.83

45/4.9/183

53/5.8/216

61/6.7/251

70/7.7/288

81/8.8/329

1.50/1.64/1.35

0.86/0.81/0.87

600

0.91

69/8.9/295

81/10.4/346

93/11.9/399

106/13.6/455

121/15.3/515

0.79/0.73/0.79

CMBT SPD

72/9.4/311

84/11.0/363

97/12.5/416

110/14.1/471

124/15.8/528

1.47/1.53/1.29

0.85/0.81/0.86

CMBT SPD

KIAS/MACH

601/0.91

0.96/0.96

1.00/1.00

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

0.30

0/0/0

1.00/1.00/1.00

250

0.38

6/0.4/20

7/0.4/24

8/0.5/29

10/0.6/34

12/0.8/42

1.11/1.15/1.09

0.96/0.92/0.92

200

300

0.45

11/0.8/40

14/0.9/48

16/1.1/57

19/1.3/68

23/1.6/81

1.14/1.19/1.10

0.95/0.92/0.92

350

0.53

17/1.3/63

20/1.6/75

24/1.8/88

28/2.1/103

33/2.5/121

1.19/1.24/1.11

0.95/0.91/0.92

400

0.60

24/2.0/89

28/2.3/105

33/2.7/123

38/3.2/143

44/3.6/166

1.23/1.29/1.14

0.93/0.90/0.92

IND

450

0.68

31/2.8/120

36/3.3/142

42/3.9/165

49/4.5/190

57/5.1/219

1.29/1.37/1.18

0.92/0.87/0.91

G I

500

0.76

40/4.1/161

47/4.8/189

55/5.5/220

63/6.3/252

73/7.2/289

1.40/1.51/1.27

0.88/0.83/0.89

550

0.83

55/6.2/226

64/7.2/264

74/8.3/305

85/9.5/349

97/10.8/397

0.83/0.78/0.84

CMBT SPD

92/12.2/400

106/13.9/458

120/15.7/517

135/17.5/580

151/19.4/647

1.21/1.20/1.05

0.84/0.80/0.85

CMBT SPD

KIAS/MACH

588/0.89

587/0.89

0.93/0.93

1.01/1.01

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

0.30

0/0/0

1.00/1.00/1.00

250

0.38

6/0.4/20

7/0.4/24

8/0.5/29

10/0.6/35

12/0.8/43

1.12/1.16/1.09

0.96/0.92/0.92

250

300

0.45

12/0.8/41

14/1.0/49

16/1.1/59

19/1.3/69

23/1.6/83

1.15/1.19/1.10

0.95/0.92/0.92

350

0.53

18/1.4/65

21/1.6/77

25/1.9/91

29/2.2/106

34/2.6/125

1.19/1.24/1.12

0.95/0.91/0.92

400

0.60

24/2.1/93

29/2.4/109

34/2.8/128

39/3.3/149

46/3.8/173

1.25/1.31/1.15

0.93/0.90/0.92

IND

450

0.68

32/3.0/127

38/3.5/149

45/4.1/174

52/4.7/201

60/5.4/232

1.32/1.41/1.21

0.91/0.87/0.90

G I

500

0.76

44/4.5/175

51/5.3/206

59/6.1/239

68/7.0/275

79/8.0/315

1.51/1.64/1.37

0.87/0.82/0.87

550

0.83

65/7.7/273

76/8.9/318

88/10.3/367

101/11.7/420

115/13.3/479

0.78/0.72/0.79

CMBT SPD

98/12.8/424

112/14.5/480

126/16.2/541

141/18.0/603

157/19.8/668

1.16/1.13/1.00

0.86/0.83/0.88

CMBT SPD

KIAS/MACH

568/0.86

567/0.86

566/0.86

0.93/0.93

1.02/1.02

Figure B85.(Sheet 2)

T.O. GR1F16CJ11

Change 3B815

MIL Accelerations 10,000 Feet

DATA BASIS FLIGHT TEST

CONDITIONS

ENGINE F110GE129

STANDARD DAY TEMPERATURE (-5

NOTE: REFER TO SECTION V FOR AIRSPEED LIMITATIONS.

TIME (SEC)/DISTANCE (NM)/FUEL (LB)

TEMP EFFECT FACTOR

KIAS

MACH

GW 20,000 LB

24,000 LB

28,000 LB

32,000 LB

36,000 LB

+20°C

-20°C

200

0.36

0/0/0

1.00/1.00/1.00

250

0.45

7/0.5/17

8/0.6/21

10/0.7/26

13/0.9/32

16/1.2/40

1.06/1.10/1.08

0.97/0.93/0.91

300

0.54

13/1.0/34

16/1.3/42

20/1.6/52

24/1.9/63

30/2.4/77

1.07/1.11/1.08

0.97/0.93/0.92

X =

350

0.63

19/1.7/52

24/2.1/64

29/2.5/78

35/3.0/94

42/3.6/113

1.08/1.12/1.09

0.97/0.93/0.92

400

0.72

26/2.4/72

32/3.0/88

38/3.6/106

45/4.3/127

54/5.1/151

1.10/1.15/1.09

0.96/0.93/0.92

450

0.80

32/3.3/93

39/4.0/114

47/4.8/137

56/5.7/162

66/6.7/191

1.14/1.20/1.11

0.96/0.92/0.92

RAG

500

0.89

38/4.3/116

47/5.2/142

56/6.2/170

66/7.3/200

78/8.5/234

1.18/1.26/1.13

0.95/0.91/0.91

550

0.97

48/5.8/151

58/7.1/184

69/8.4/220

82/9.8/258

96/11.4/300

0.92/0.87/0.89

CMBT SPD

64/8.7/214

76/10.2/255

89/11.9/296

103/13.5/340

118/15.3/387

1.12/1.15/1.02

1.10/1.11/1.14

CMBT SPD

KIAS/MACH

564/1.00

563/1.00

563/0.99

562/0.99

0.97/0.98

1.02/1.02

TIME (SEC)/DISTANCE (NM)/FUEL (LB)

TEMP EFFECT FACTOR

KIAS

MACH

GW 20,000 LB

24,000 LB

28,000 LB

32,000 LB

36,000 LB

+20°C

-20°C

200

0.36

0/0/0

1.00/1.00/1.00

250

0.45

7/0.5/17

9/0.6/21

11/0.8/26

13/1.0/33

17/1.2/41

1.06/1.10/1.08

0.97/0.93/0.91

= 5

300

0.54

13/1.1/35

17/1.3/43

20/1.6/53

25/2.0/65

31/2.4/79

1.07/1.11/1.08

0.97/0.93/0.92

350

0.63

20/1.8/54

25/2.2/67

30/2.6/81

36/3.2/98

44/3.8/118

1.08/1.13/1.09

0.97/0.93/0.92

400

0.72

27/2.6/75

33/3.1/92

40/3.8/111

48/4.5/133

57/5.4/159

1.11/1.16/1.10

0.96/0.93/0.92

450

0.80

34/3.5/99

41/4.3/121

50/5.1/145

59/6.1/172

70/7.1/203

1.15/1.21/1.12

0.96/0.92/0.92

500

0.89

41/4.6/126

50/5.6/154

60/6.7/183

71/7.9/216

84/9.2/253

1.21/1.29/1.16

0.94/0.90/0.91

CMBT SPD

64/8.4/211

76/9.9/251

89/11.6/293

103/13.2/338

119/15.1/386

1.23/1.30/1.13

0.95/0.91/0.95

CMBT SPD

KIAS/MACH

549/0.97

548/0.97

547/0.97

0.98/0.98

1.01/1.01

TIME (SEC)/DISTANCE (NM)/FUEL (LB)

TEMP EFFECT FACTOR

KIAS

MACH

GW 22,000 LB

26,000 LB

30,000 LB

34,000 LB

38,000 LB

+20°C

-20°C

200

0.36

0/0/0

1.00/1.00/1.00

250

0.45

8/0.6/19

10/0.7/24

12/0.9/30

15/1.1/38

20/1.4/49

1.06/1.10/1.08

0.97/0.93/0.91

300

0.54

15/1.2/40

19/1.5/49

23/1.9/60

29/2.3/74

35/2.8/91

1.07/1.11/1.09

0.97/0.93/0.92

EX =

350

0.63

23/2.0/63

28/2.5/77

34/3.0/93

41/3.6/112

50/4.4/135

1.09/1.13/1.09

0.97/0.93/0.92

400

0.72

31/3.0/88

38/3.6/107

46/4.4/128

55/5.2/153

66/6.2/183

1.12/1.17/1.11

0.96/0.93/0.92

450

0.80

40/4.2/117

48/5.0/141

58/6.0/169

68/7.0/199

81/8.3/236

1.17/1.23/1.14

0.96/0.92/0.92

RAG

500

0.89

50/5.6/152

60/6.8/184

71/8.0/218

84/9.4/256

99/11.0/300

1.26/1.36/1.21

0.94/0.90/0.91

CMBT SPD

75/9.8/248

89/11.5/292

103/13.3/338

119/15.1/386

136/17.1/440

1.16/1.20/1.06

0.91/0.87/0.90

CMBT SPD

KIAS/MACH

537/0.95

536/0.95

535/0.95

0.97/0.97

1.01/1.01

Figure B86.(Sheet 1)

Content .. 71 72 73 74 ..

F16C/D. FLIGHT MANUAL (2002) - page 73

F16C/D. FLIGHT MANUAL (2002) - page 73