Content .. 82 83 84 85 ..

F16C/D. FLIGHT MANUAL (2002) - page 84

T.O. GR1F16CJ11

Change 7C77

GR1F-16CJ-1-1-6046X37

1000

2000

3000

4000

5000

6000

7000

GROUND ROLL DIST

ANCE 1000 FEET

TITUDE FEET

NOTE:

DATA BASIS ESTIMATED

CONFIGURATION:

CONDITIONS:

ENGINE F100-PW-229/CFT

ALL DRAG INDEXES

SPEEDBRAKES OPEN

DRAG CHUTE DEPLOYED

BELOW 170 KIAS

Short Field Landing Distance With Drag

Chute (Uncorrected)

TOUCHDOWN AT 13 DEGREES AOA

ZERO WIND AND SLOPE

IDLE SELECTED AT TOUCHDOWN

MAX EFFORT BRAKING

DRY CONCRETE RUNWAY

FOR SEC IDLE LANDING, INCREASE UNCORRECTED

GROUND ROLL DISTANCE BY 6 PERCENT. USE SHEET

6 TO DETERMINE CORRECTED GROUND ROLL DISTANCE.

DEPLOYING THE DRAG

DEPLOYING THE DRAG CHUTE AT

AIRSPEEDS GREATER THAN 170

KIAS MAY RESULT IN LOSS OF

THE CHUTE CANOPY.

MLG TIRE LIMIT SPEED

(225 KTS NO WIND)

NLG TIRE LIMIT SPEED

(217 KTS NO WIND)

MAXIMUM BRAKE

ENERGY LIMIT LINE

Figure C72.(Sheet 4)

T.O. GR1F16CJ11

C78Change 7

GR1F-16CJ-1-1-6047X37

DATA BASIS ESTIMATED

CONFIGURATION:

CONDITIONS:

ENGINE F100-PW-229/CFT

TOUCHDOWN AT 13 DEGREES AOA

Short Field Landing Distance With Drag

ALL DRAG INDEXES

SPEEDBRAKES OPEN

IDLE SELECTED AT TOUCHDOWN

MAX EFFORT BRAKING

ENTER CHART WITH UNCORRECTED GROUND

ROLL DISTANCE FROM SHEET 4

CORRECTED GROUND ROLL DISTANCE 1000 FEET

UNCORRECTED GROUND ROLL DIST

ANCE 1000 FEET

BASELINE

2
3

WIND

KNOTS

SLOPE

Chute (Corrected)

DRAG CHUTE DEPLOYED

BELOW 170 KIAS

DEPLOYING THE DRAG

CHUTE AT AIRSPEEDS

GREATER THAN 170

KIAS MAY RESULT IN

LOSS OF THE CHUTE

CANOPY.

Figure C72.(Sheet 5)

T.O. GR1F16CJ11

Change 7C79/(C710 blank)

GR1F-16CJ-1-1-6048X37

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 F100-PW-229/CFT

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 C72.(Sheet 6)

T.O. GR1F16CJ11

Change 7C81

PART 8-COMBAT

TABLE OF CONTENTS

Page

Combat Ceilings and Optimum Cruise

Altitude

C82

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

Level Flight Combat Speeds

and Altitudes

C83

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

Level Flight Combat Speed

C83

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

Fuel Flow (MIL and MAX AB)

C83

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

MIL Acceleration

C83

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

MAX AB Acceleration

C84

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

Turn Performance

C84

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

Deceleration

C85

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

LIST OF CHARTS

Figure

Page

Combat Ceilings and Opti

mum Cruise Altitude

C81

C86

. . . .

Level Flight Combat Speeds

and Altitudes (MIL/MAX

AB)

C82

C87

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

. . . .

Level Flight Combat Speed

(MIL/MAX AB)

C83

C811

. . . . . . . . .

. . . .

Fuel Flow (MIL/MAX AB)

C84

C812

. . .

. . . .

MIL Accelerations-Sea

Level

C85

C813

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

. . . .

MIL Accelerations-10,000

Feet

C86

C817

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

. . . .

MIL Accelerations-20,000

Feet

C87

C821

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

. . . .

MIL Accelerations-30,000

Feet

C88

C824

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

. . . .

MAX AB Accelerations-Sea

Level

C89

C826

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

. . . .

MAX AB Accelerations-

10,000 Feet

C810

C830

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

. . . .

MAX AB Accelerations-

20,000 Feet

C811

C834

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

. . . .

MAX AB Accelerations-

30,000 Feet

C812

C838

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

. . . .

MAX AB Accelerations-

40,000 Feet

C813

C842

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

. . . .

MIL:

Drag index = 0

Turn Performance-Sea

Level

C814

C844

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

. . . .

Turn Performance-5000

Feet

C815

C845

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

. . . .

Turn Performance-10,000

Feet

C816

C846

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

. . . .

Figure

Page

Turn Performance-15,000

Feet

C817

C847

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

. . . .

Turn Performance-20,000

Feet

C818

C848

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

. . . .

Turn Performance-25,000

Feet

C819

C849

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

. . . .

Turn Performance-30,000

Feet

C820

C850

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

. . . .

MIL:

Drag index = 50

Turn Performance-Sea

Level

C821

C851

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

. . . .

Turn Performance-10,000

Feet

C822

C852

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

. . . .

Turn Performance-20,000

Feet

C823

C853

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

. . . .

Turn Performance-30,000

Feet

C824

C854

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

. . . .

MIL:

Drag index = 100

Turn Performance-Sea

Level

C825

C855

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

. . . .

Turn Performance-10,000

Feet

C826

C856

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

. . . .

Turn Performance-20,000

Feet

C827

C857

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

. . . .

Turn Performance-30,000

Feet

C828

C858

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

. . . .

MIL:

Drag index = 150

Turn Performance-Sea

Level

C829

C859

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

. . . .

Turn Performance-10,000

Feet

C830

C860

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

. . . .

Turn Performance-20,000

Feet

C831

C861

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

. . . .

Turn Performance-30,000

Feet

C832

C862

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

. . . .

MIL:

Drag index = 200

Turn Performance-Sea

Level

C833

C863

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

. . . .

Turn Performance-10,000

Feet

C834

C864

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

. . . .

Turn Performance-20,000

Feet

C835

C865

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

. . . .

Turn Performance-30,000

Feet

C836

C866

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

. . . .

T.O. GR1F16CJ11

C82Change 7

Figure

Page

MAX AB:

Drag index = 0

Turn Performance-Sea

Level

C837

C867

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

. . . .

Turn Performance-5000

Feet

C838

C868

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

. . . .

Turn Performance-10,000

Feet

C839

C869

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

. . . .

Turn Performance-15,000

Feet

C840

C870

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

. . . .

Turn Performance-20,000

Feet

C841

C871

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

. . . .

Turn Performance-25,000

Feet

C842

C872

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

. . . .

Turn Performance-30,000

Feet

C843

C873

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

. . . .

Turn Performance-35,000

Feet

C844

C874

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

. . . .

Turn Performance-40,000

Feet

C845

C875

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

. . . .

Turn Performance-45,000

Feet

C846

C876

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

. . . .

Turn Performance-50,000

Feet

C847

C877

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

. . . .

MAX AB:

Drag index = 50

Turn Performance-Sea

Level

C848

C878

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

. . . .

Turn Performance-10,000

Feet

C849

C879

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

. . . .

Turn Performance-20,000

Feet

C850

C880

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

. . . .

Turn Performance-30,000

Feet

C851

C881

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

. . . .

Turn Performance-40,000

Feet

C852

C882

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

. . . .

MAX AB:

Drag index = 100

Turn Performance-Sea

Level

C853

C883

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

. . . .

Turn Performance-10,000

Feet

C854

C884

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

. . . .

Turn Performance-20,000

Feet

C855

C885

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

. . . .

Turn Performance-30,000

Feet

C856

C886

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

. . . .

MAX AB:

Drag index = 150

Turn Performance-Sea

Level

C857

C887

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

. . . .

Turn Performance-10,000

Feet

C858

C888

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

. . . .

Figure

Page

Turn Performance-20,000

Feet

C859

C889

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

. . . .

Turn Performance-30,000

Feet

C860

C890

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

. . . .

MAX AB:

Drag index = 200

Turn Performance-Sea

Level

C861

C891

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

. . . .

Turn Performance-10,000

Feet

C862

C892

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

. . . .

Turn Performance-20,000

Feet

C863

C893

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

. . . .

Turn Performance-30,000

Feet

C864

C894

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

. . . .

Deceleration -20,000

Feet

C865

C895

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

. . . .

Deceleration -30,000

Feet

C865

C896

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

. . . .

Deceleration - 40,000

Feet

C865

C897

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

. . . .

COMBAT CEILINGS AND OPTIMUM

CRUISE ALTITUDE

Combat ceiling and optimum cruise altitude data is

shown in figure C81. 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 C81.

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 665 feet to MIL combat

ceiling. For MIL service ceiling, add 1330 feet to MIL

combat ceiling.

SAMPLE PROBLEM.

A. GW

= 33,000 pounds

B. Drag index

= 230

C. Cruise altitude

= 33,045 feet

D. MIL combat ceiling

(500 fpm)

= 33,430 feet

MIL cruise ceiling

(300 fpm)

= 34,095 feet

MIL service ceiling

(100 fpm)

= 34,760 feet

T.O. GR1F16CJ11

Change 7C83

LEVEL FLIGHT COMBAT SPEEDS AND

ALTITUDES

Combat speed and altitude envelopes are shown in

figure C82 (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 C82, 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

= 0.94

MAX AB

= 1.78

For nonstandard day, use the adjustments noted in

figure C83 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 C83. 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 C83.

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 C83. 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

= 486 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

= -10 knots

Maximum indicated

airspeed for ambient

temperature of -10

C = 486-(10

5/20) =

484 knots

FUEL FLOW (MIL AND MAX AB)

Fuel flow data for MIL and MAX AB thrust is given

in figure C84. 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 54,340 pounds of fuel per hour or (54,340

60) = 906 pounds of fuel every minute.

MIL ACCELERATION

MIL acceleration performance from 200 KIAS to com

bat speed is given in figures C85, C86, C87, and

C88 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 C85.

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

C84Change 7

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)

= 31 pounds

J. Temperature effect

factor at +20

= 1.08

K. Fuel at initial condi

tion is 1.08

31 for

+20

= 33.5 pounds

L. Fuel at initial condi

tion for 7

C is 31 +

(2.5

7/20)

= 31.9 pounds

M. Fuel at final condi

tions (STD)

= 158 pounds

N. Temperature effect

factor at +20

= 1.19

O. Fuel at final condi

tion is 1.19

158 for

+20

= 188 pounds

P. Fuel at final condi

tion for 7

C is 158 +

(30

7/20)

= 168.5 pounds

Q. Fuel consumed

(168.5-31.9)

= 136.6 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 C89, C810, C811,

C812, and C813 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 C814 through C864 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 fi

gure C837, 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 420 fps or an instantaneous rate of climb of al

most 25,200 fpm. At the same load factor, however,

turn radius can be reduced by making the turn at 0.7

mach while still maintaining airspeed and altitude

(Ps = 0). The quickest turn occurs at about 8g, 0.55

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 3.6g,

0.35 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 8C85

REFER TO FIGURE C837.

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

= 20.9 degrees/second

D. GW

= 24,000 pounds

∆

Turn rate

= -1.7 degrees/second

F. Temp dev from std

day

= +20

∆

Turn rate

= -2.1 degrees/second

H. Corrected turn rate =

20.9-1.7-2.1

= 17.0 degrees/second

(at Ps = 0)

I. Turn radius

= 1841 feet

J. Turn radius factor

= 1.069

K. Corrected turn

radius 1841 feet

1.069

= 1968 feet

DECELERATION

Level 1g deceleration performance is shown in figure

C865 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 C865.

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

= 26,000 pounds

D. Fuel used

= 97 pounds

E. Distance

= 17.4 nm

F. Time

= 1.88 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

= 97-6.9 = 90.1 pounds

H. Distance

= 17.4-3.1 = 14.3 nm

I. Time

= 1.88-0.45 = 1.43

minutes

T.O. GR1F16CJ11

C86Change 7

1F-16CJ-1-1-1046X37

DATA BASIS ESTIMATED

STANDARD DAY

CONDITIONS:

ENGINE F100-PW-229/CFT

OPTIMUM CRUISE MACH NUMBER

OPTIMUM CRUISE ALTITUDE

Combat Ceilings and Optimum Cruise

Altitude

COMBAT CEILING (500 FPM)

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 665 FEET.

FOR MIL SERVICE CEILING (100 FPM),

INCREASE ALTITUDE 1330 FEET.

NOTE: FOR ALL DRAG INDEXES

+20 C OR -20 C OFF

STANDARD TEMPERATURE

EFFECTS ARE NEGLIGIBLE.

MACH

0.84

0.82

100

150

0.80

0.75

200

250

300

DRAG INDEX

OPTIMUM CRUISE

GW 1000 POUNDS

0.71

350

0.68

400

Figure C81.

T.O. GR1F16CJ11

Change 7C87

1F-16CJ-1-1-1047X37

DATA BASIS ESTIMATED

ENGINE F100-PW-229/CFT

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 C8-3 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 C82.(Sheet 1)

T.O. GR1F16CJ11

C88Change 7

Level Flight Combat Speeds and Altitudes

(MIL/MAX AB)

DATA BASIS ESTIMATED

ENGINE F100-PW-229/CFT

NOTES:

FOR NONSTANDARD DAY, REFER
TO FIGURE C8-3 TO ADJUST AIR-
SPEED BELOW 30,000 FEET. ABOVE
30,000 FEET, REFER TO TEXT.
REFER TO SECTION V FOR
AIRSPEED LIMITATIONS.

1F-16CJ-1-1-1048X37

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 C82.(Sheet 2)

T.O. GR1F16CJ11

Change 7C89

Level Flight Combat Speeds and Altitudes

(MIL/MAX AB)

DATA BASIS ESTIMATED

ENGINE F100-PW-229/CFT

NOTES:

FOR NONSTANDARD DAY, REFER
TO FIGURE C8-3 TO ADJUST AIR-
SPEED BELOW 30,000 FEET. ABOVE
30,000 FEET, REFER TO TEXT.
REFER TO SECTION V FOR
AIRSPEED LIMITATIONS.

1F-16CJ-1-1-1049X37

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 C82.(Sheet 3)

T.O. GR1F16CJ11

C810Change 7

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 ESTIMATED

ENGINE F100-PW-229/CFT

NOTES:

FOR NONSTANDARD DAY, REFER
TO FIGURE C8-3 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-1-1-1050X37

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 C82.(Sheet 4)

T.O. GR1F16CJ11

Change 7C811

Level Flight Combat Speed

(MIL/MAX AB)

DATA BASIS ESTIMATED

CONDITIONS:

ENGINE F100PW229/CFT

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

630

613

602

592

581

565

544

5,000

592

575

562

553

543

533

516

-5

10,000

554

538

525

516

509

499

488

-15

15,000

516

500

486

476

468

459

447

-25

20,000

473

457

445

436

429

423

-35

25,000

434

417

405

395

387

-44

30,000

INDICATED AIRSPEED - KNOTS

1/-13

2/-12

1/-15

2/-23

2-36

6/-42

11/-41

5,000

8/-15

9/-13

9/-11

9/-15

11/-23

14/-34

23/-36

10,000

16/-13

10/-13

8/-11

6/-12

4/-18

7/-24

8/-30

15,000

8/-13

3/-12

3/-10

2/-9

2/-11

4/-16

5/-21

20,000

3/-9

1/-7

0/-7

0/-12

25,000

-1/-10

-1/-6

-1/-4

0/-3

0/-2

30,000

MAX AB

STANDARD

INDICATED AIRSPEED - KNOTS

STANDARD

TEMPERATURE

°C

ALTITUDE

FEET

DRAG

INDEX0

100

150

200

250

300

+15

**800

728

671

651

638

629

620

5,000

**800

735

647

613

600

590

582

-5

10,000

**800

741

662

583

562

552

543

-15

15,000

**800

735

650

582

520

510

501

-25

20,000

**800

719

633

562

480

468

461

-35

25,000

767

703

531

425

418

-44

30,000

729

383

376

INDICATED AIRSPEED - KNOTS

**0/**33

10/-43

4/-17

2/-11

3/-10

2/-11

5,000

**0/-49

11/-74

40/-34

10/-15

6/-13

5/-13

10,000

**0/-57

27/-82

34/-83

60/-25

13/-15

7/-13

7/-12

15,000

**0/-67

59/-89

60/-96

60/-62

17/-12

7/-11

7/-9

20,000

**0/-90

**81/-93

81/-76

57/-78

64/-11

5/-8

4/-8

25,000

**33/-80

81/-97

51/-86

3/-6

30,000

**71/-73

3/-4

3/-3

TEMPERATURE DEVIATION FROM STANDARD = -20

C/+20

LIMIT AIRSPEED

Figure C83.

T.O. GR1F16CJ11

C812Change 7

Fuel Flow (MIL/MAX AB)

DATA BASIS ESTIMATED

ENGINE F100-PW-229/CFT

STANDARD DAY

CONDITIONS:

1F-16CJ-1-1-1051X

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 C84.

T.O. GR1F16CJ11

Change 7C813

MIL Accelerations Sea Level

DATA BASIS ESTIMATED

CONDITIONS:

ENGINE F100PW229/CFT

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

4/0.2/15

5/0.3/19

6/0.4/23

7/0.4/27

8/0.5/32

1.15/1.19/1.08

0.95/0.91/0.93

300

0.45

8/0.5/31

10/0.7/37

11/0.8/45

14/0.9/54

16/1.1/63

1.17/1.21/1.08

0.94/0.91/0.93

= 0

350

0.53

12/0.9/47

14/1.1/57

17/1.3/69

20/1.5/81

23/1.8/95

1.19/1.24/1.08

0.94/0.91/0.93

400

0.60

16/1.3/64

19/1.6/79

23/1.9/94

27/2.2/110

31/2.5/128

1.21/1.26/1.09

0.93/0.89/0.93

450

0.68

20/1.8/83

24/2.2/101

29/2.6/120

33/3.0/141

39/3.5/163

1.23/1.29/1.10

0.91/0.87/0.93

G I

500

0.76

24/2.4/104

29/2.9/126

35/3.4/150

41/4.0/175

47/4.6/201

1.25/1.31/1.12

0.89/0.85/0.92

550

0.83

29/3.1/128

35/3.8/155

42/4.5/184

49/5.2/213

56/5.9/245

1.29/1.36/1.14

0.88/0.84/0.91

600

0.91

35/4.1/158

43/5.0/191

51/5.9/226

59/6.8/262

68/7.7/300

1.35/1.45/1.19

0.89/0.85/0.91

CMBT SPD

55/7.4/250

65/8.7/297

75/10.1/344

86/11.4/392

97/12.8/440

1.22/1.25/1.07

0.90/0.87/0.91

CMBT SPD

KIAS/MACH

631/0.95

630/0.95

0.98/0.98

1.00/1.00

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

TEMP EFFECT FACTOR

KIAS

MACH

GW 36,000 LB

40,000 LB

44,000 LB

+20°C

-20°C

200

0.30

0/0/0

1.00/1.00/1.00

250

0.38

8/0.5/32

10/0.6/39

12/0.8/47

1.17/1.21/1.10

0.94/0.91/0.92

300

0.45

16/1.1/63

19/1.3/74

22/1.5/88

1.19/1.23/1.10

0.94/0.91/0.92

= 0

350

0.53

23/1.8/95

27/2.1/110

32/2.4/128

1.21/1.26/1.10

0.94/0.90/0.92

400

0.60

31/2.5/128

36/2.9/147

41/3.4/170

1.23/1.28/1.11

0.93/0.89/0.93

450

0.68

39/3.5/163

44/4.0/187

51/4.5/214

1.25/1.30/1.12

0.91/0.87/0.92

G I

500

0.76

47/4.6/201

54/5.2/230

62/5.9/263

1.27/1.33/1.13

0.89/0.85/0.92

550

0.83

56/5.9/245

64/6.7/279

73/7.6/317

1.30/1.37/1.15

0.88/0.84/0.91

600

0.91

68/7.7/300

77/8.8/341

87/9.8/385

1.36/1.46/1.20

0.88/0.84/0.91

CMBT SPD

97/12.8/440

108/14.1/491

120/15.6/546

1.23/1.25/1.07

0.90/0.87/0.91

CMBT SPD

KIAS/MACH

630/0.95

629/0.95

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

4/0.2/15

5/0.3/19

6/0.4/23

7/0.4/28

9/0.5/33

1.15/1.19/1.08

0.95/0.91/0.93

300

0.45

8/0.5/31

10/0.7/38

12/0.8/46

14/1.0/55

16/1.1/64

1.17/1.21/1.08

0.94/0.91/0.93

= 5

350

0.53

12/0.9/48

15/1.1/59

17/1.3/70

21/1.6/83

24/1.8/97

1.19/1.24/1.09

0.94/0.91/0.93

400

0.60

16/1.3/66

20/1.6/81

23/1.9/97

27/2.3/113

32/2.6/132

1.22/1.27/1.10

0.93/0.89/0.93

450

0.68

20/1.9/87

25/2.3/105

30/2.7/125

35/3.1/146

40/3.6/169

1.25/1.30/1.12

0.91/0.87/0.92

500

0.76

25/2.5/110

31/3.1/133

37/3.6/158

43/4.2/184

49/4.8/212

1.27/1.34/1.14

0.89/0.84/0.92

550

0.83

31/3.4/137

38/4.1/167

45/4.8/197

52/5.6/229

60/6.4/263

1.33/1.41/1.18

0.87/0.83/0.91

600

0.91

40/4.7/178

48/5.7/216

57/6.7/254

66/7.8/295

76/8.9/337

1.56/1.73/1.38

0.87/0.83/0.90

CMBT SPD

53/7.1/244

64/8.3/290

74/9.6/336

84/10.9/384

95/12.2/433

1.28/1.32/1.11

0.89/0.86/0.91

CMBT SPD

KIAS/MACH

614/0.93

613/0.93

0.98/0.98

1.00/1.00

Figure C85.(Sheet 1)

Content .. 82 83 84 85 ..

F16C/D. FLIGHT MANUAL (2002) - page 84

F16C/D. FLIGHT MANUAL (2002) - page 84