Content .. 57 58 59 60 ..

F16C/D. FLIGHT MANUAL (2002) - page 59

T.O. GR1F16CJ11

Change 7A77

GR1F-16CJ-1-1-5046X37

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

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)

Figure A72.(Sheet 4)

T.O. GR1F16CJ11

A78Change 7

GR1F-16CJ-1-1-5047X37

DATA BASIS ESTIMATED

CONFIGURATION:

CONDITIONS:

ENGINE F100-PW-229

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 A72.(Sheet 5)

T.O. GR1F16CJ11

Change 7A79/(A710 blank)

GR1F-16CJ-1-1-5048X37

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

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 A72.(Sheet 6)

T.O. GR1F16CJ11

Change 7A81

PART 8-COMBAT

TABLE OF CONTENTS

Page

Combat Ceilings and Optimum Cruise

Altitude

A82

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

Level Flight Combat Speeds

and Altitudes

A83

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

Level Flight Combat Speed

A83

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

Fuel Flow (MIL and MAX AB)

A83

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

MIL Acceleration

A83

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

MAX AB Acceleration

A84

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

Turn Performance

A84

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

Deceleration

A85

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

LIST OF CHARTS

Figure

Page

Combat Ceilings and Opti

mum Cruise Altitude

A81

A86

. . . .

Level Flight Combat Speeds

and Altitudes (MIL/MAX

AB)

A82

A87

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

. . . .

Level Flight Combat Speed

(MIL/MAX AB)

A83

A811

. . . . . . . . .

. . . .

Fuel Flow (MIL/MAX AB)

A84

A812

. . .

. . . .

MIL Accelerations-Sea

Level

A85

A813

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

. . . .

MIL Accelerations-10,000

Feet

A86

A815

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

. . . .

MIL Accelerations-20,000

Feet

A87

A817

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

. . . .

MIL Accelerations-30,000

Feet

A88

A819

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

. . . .

MAX AB Accelerations-Sea

Level

A89

A821

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

. . . .

MAX AB Accelerations-

10,000 Feet

A810

A823

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

. . . .

MAX AB Accelerations-

20,000 Feet

A811

A825

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

. . . .

MAX AB Accelerations-

30,000 Feet

A812

A827

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

. . . .

MAX AB Accelerations-

40,000 Feet

A813

A829

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

. . . .

MIL:

Drag index = 0

Turn Performance-Sea

Level

A814

A831

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

. . . .

Turn Performance-5000

Feet

A815

A832

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

. . . .

Turn Performance-10,000

Feet

A816

A833

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

. . . .

Figure

Page

Turn Performance-15,000

Feet

A817

A834

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

. . . .

Turn Performance-20,000

Feet

A818

A835

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

. . . .

Turn Performance-25,000

Feet

A819

A836

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

. . . .

Turn Performance-30,000

Feet

A820

A837

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

. . . .

MIL:

Drag index = 50

Turn Performance-Sea

Level

A821

A838

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

. . . .

Turn Performance-10,000

Feet

A822

A839

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

. . . .

Turn Performance-20,000

Feet

A823

A840

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

. . . .

Turn Performance-30,000

Feet

A824

A841

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

. . . .

MIL:

Drag index = 100

Turn Performance-Sea

Level

A825

A842

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

. . . .

Turn Performance-10,000

Feet

A826

A843

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

. . . .

Turn Performance-20,000

Feet

A827

A844

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

. . . .

Turn Performance-30,000

Feet

A828

A845

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

. . . .

MIL:

Drag index = 150

Turn Performance-Sea

Level

A829

A846

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

. . . .

Turn Performance-10,000

Feet

A830

A847

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

. . . .

Turn Performance-20,000

Feet

A831

A848

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

. . . .

Turn Performance-30,000

Feet

A832

A849

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

. . . .

MIL:

Drag index = 200

Turn Performance-Sea

Level

A833

A850

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

. . . .

Turn Performance-10,000

Feet

A834

A851

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

. . . .

Turn Performance-20,000

Feet

A835

A852

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

. . . .

Turn Performance-30,000

Feet

A836

A853

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

. . . .

T.O. GR1F16CJ11

A82Change 7

Figure

Page

MAX AB:

Drag index = 0

Turn Performance-Sea

Level

A837

A854

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

. . . .

Turn Performance-5000

Feet

A838

A855

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

. . . .

Turn Performance-10,000

Feet

A839

A856

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

. . . .

Turn Performance-15,000

Feet

A840

A857

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

. . . .

Turn Performance-20,000

Feet

A841

A858

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

. . . .

Turn Performance-25,000

Feet

A842

A859

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

. . . .

Turn Performance-30,000

Feet

A843

A860

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

. . . .

Turn Performance-35,000

Feet

A844

A861

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

. . . .

Turn Performance-40,000

Feet

A845

A862

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

. . . .

Turn Performance-45,000

Feet

A846

A863

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

. . . .

Turn Performance-50,000

Feet

A847

A864

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

. . . .

MAX AB:

Drag index = 50

Turn Performance-Sea

Level

A848

A865

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

. . . .

Turn Performance-10,000

Feet

A849

A866

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

. . . .

Turn Performance-20,000

Feet

A850

A867

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

. . . .

Turn Performance-30,000

Feet

A851

A868

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

. . . .

Turn Performance-40,000

Feet

A852

A869

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

. . . .

MAX AB:

Drag index = 100

Turn Performance-Sea

Level

A853

A870

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

. . . .

Turn Performance-10,000

Feet

A854

A871

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

. . . .

Turn Performance-20,000

Feet

A855

A872

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

. . . .

Turn Performance-30,000

Feet

A856

A873

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

. . . .

MAX AB:

Drag index = 150

Turn Performance-Sea

Level

A857

A874

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

. . . .

Turn Performance-10,000

Feet

A858

A875

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

. . . .

Figure

Page

Turn Performance-20,000

Feet

A859

A876

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

. . . .

Turn Performance-30,000

Feet

A860

A877

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

. . . .

MAX AB:

Drag index = 200

Turn Performance-Sea

Level

A861

A878

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

. . . .

Turn Performance-10,000

Feet

A862

A879

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

. . . .

Turn Performance-20,000

Feet

A863

A880

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

. . . .

Turn Performance-30,000

Feet

A864

A881

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

. . . .

Deceleration -20,000

Feet

A865

A882

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

. . . .

Deceleration -30,000

Feet

A865

A883

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

. . . .

Deceleration - 40,000

Feet

A865

A884

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

. . . .

COMBAT CEILINGS AND OPTIMUM

CRUISE ALTITUDE

Combat ceiling and optimum cruise altitude data is

shown in figure A81. 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 A81.

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 670 feet to MIL combat

ceiling. For MIL service ceiling, add 1340 feet to MIL

combat ceiling.

SAMPLE PROBLEM.

A. GW

= 33,000 pounds

B. Drag index

= 230

C. Cruise altitude

= 33,110 feet

D. MIL combat ceiling

(500 fpm)

= 33,510 feet

MIL cruise ceiling

(300 fpm)

= 34,180 feet

MIL service ceiling

(100 fpm)

= 34,850 feet

T.O. GR1F16CJ11

Change 7A83

LEVEL FLIGHT COMBAT SPEEDS AND

ALTITUDES

Combat speed and altitude envelopes are shown in

figure A82 (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 A82, 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

= 1.87

For nonstandard day, use the adjustments noted in

figure A83 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 A83. 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 A83.

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 A83. 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

= 489 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

= -11 knots

Maximum indicated

airspeed for ambient

temperature of -10

C = 489-(11

5/20) = 486

knots

FUEL FLOW (MIL AND MAX AB)

Fuel flow data for MIL and MAX AB thrust is given

in figure A84. 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 A85, A86, A87, and

A88 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 A85.

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

A84Change 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)

= 157 pounds

N. Temperature effect

factor at +20

= 1.19

O. Fuel at final condi

tion is 1.19

157 for

+20

= 186.8 pounds

P. Fuel at final condi

tion for 7

C is 157 +

(29.8

7/20)

= 167.4 pounds

Q. Fuel consumed

(167.4-31.9)

= 135.5 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 A89, A810, A811,

A812, and A813 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 A814 through A864 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 A837, 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 470 fps or an instantaneous rate of climb of al

most 28,200 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, 0.54

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 3.1g,

0.31 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 7A85

REFER TO FIGURE A837.

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

= 20.5 degrees/second

D. GW

= 24,000 pounds

∆

Turn rate

= -2.0 degrees/second

F. Temp dev from std

day

= +20

∆

Turn rate

= -2.1 degrees/second

H. Corrected turn rate =

20.5-2.0-2.1

= 16.4 degrees/second

(at Ps = 0)

I. Turn radius

= 1873 feet

J. Turn radius factor

= 1.069

K. Corrected turn

radius 1873 feet

1.069

= 2003 feet

DECELERATION

Level 1g deceleration performance is shown in figure

A865 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 A865.

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

= 96 pounds

E. Distance

= 16.4 nm

F. Time

= 1.75 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

= 96-6.6 = 89.4 pounds

H. Distance

= 16.4-2.9 = 13.5 nm

I. Time

= 1.75-0.43 = 1.32

minutes

T.O. GR1F16CJ11

A86Change 7

1F-16CJ-1-1-1046A

DATA BASIS FLIGHT TEST

STANDARD DAY

CONDITIONS:

ENGINE F100-PW-229

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 670 FEET.

FOR MIL SERVICE CEILING (100 FPM),

INCREASE ALTITUDE 1340 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 A81.

T.O. GR1F16CJ11

Change 7A87

1F-16CJ-1-1-1047A

DATA BASIS FLIGHT TEST

ENGINE F100-PW-229

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 A8-3 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 A82.(Sheet 1)

T.O. GR1F16CJ11

A88Change 7

Level Flight Combat Speeds and Altitudes

(MIL/MAX AB)

DATA BASIS FLIGHT TEST

ENGINE F100-PW-229

NOTES:

FOR NONSTANDARD DAY, REFER
TO FIGURE A8-3 TO ADJUST AIR-
SPEED BELOW 30,000 FEET. ABOVE
30,000 FEET, REFER TO TEXT.
REFER TO SECTION V FOR
AIRSPEED LIMITATIONS.

1F-16CJ-1-1-1048A

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 A82.(Sheet 2)

T.O. GR1F16CJ11

Change 7A89

Level Flight Combat Speeds and Altitudes

(MIL/MAX AB)

DATA BASIS FLIGHT TEST

ENGINE F100-PW-229

NOTES:

FOR NONSTANDARD DAY, REFER
TO FIGURE A8-3 TO ADJUST AIR-
SPEED BELOW 30,000 FEET. ABOVE
30,000 FEET, REFER TO TEXT.
REFER TO SECTION V FOR
AIRSPEED LIMITATIONS.

1F-16CJ-1-1-1049A

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 A82.(Sheet 3)

T.O. GR1F16CJ11

A810Change 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 FLIGHT TEST

ENGINE F100-PW-229

NOTES:

FOR NONSTANDARD DAY, REFER
TO FIGURE A8-3 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-1-1-1050A

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 A82.(Sheet 4)

T.O. GR1F16CJ11

Change 7A811

Level Flight Combat Speed

(MIL/MAX AB)

DATA BASIS FLIGHT TEST

CONDITIONS:

ENGINE F100PW229

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

634

616

603

592

581

565

546

5,000

597

578

564

554

544

534

517

-5

10,000

559

541

527

517

509

499

489

-15

15,000

523

503

489

477

468

460

448

-25

20,000

460

447

437

429

424

-35

25,000

420

407

396

-44

30,000

INDICATED AIRSPEED - KNOTS

1/-14

1/-15

3/-22

3/-35

6/-41

10/-42

5,000

8/-15

9/-14

9/-12

9/-15

11/-23

13/-34

22/-36

10,000

23/-14

11/-14

9/-12

7/-13

5/-17

8/-23

7/-30

15,000

13/-16

4/-11

3/-11

3/-9

2/-11

3/-16

5/-22

20,000

2/-8

1/-8

0/-7

-1/-12

25,000

-1/-6

-1/-5

0/-3

30,000

MAX AB

STANDARD

INDICATED AIRSPEED - KNOTS

STANDARD

TEMPERATURE

°C

ALTITUDE

FEET

DRAG

INDEX0

100

150

200

250

300

+15

**800

756

680

654

641

631

621

5,000

**800

761

692

619

603

593

584

-5

10,000

**800

776

686

594

565

554

545

-15

15,000

**800

773

684

611

525

512

503

-25

20,000

**800

758

661

587

486

470

462

-35

25,000

795

732

641

427

420

-44

30,000

755

698

385

378

INDICATED AIRSPEED - KNOTS

**0/**0

10/-49

5/-21

3/-11

2/-12

3/-10

5,000

**0/-8

14/-63

18/-72

13/-18

6/-14

5/-14

5/-13

10,000

**0/-8

**24/-88

35/-95

70/-32

18/-15

8/-14

7/-13

15,000

**0/-29

**27/-93

57/-86

56/-85

78/-14

8/-11

7/-9

20,000

**0/-53

**42/-100

101/-79

64/-95

90/-15

6/-8

4/-7

25,000

**0/-77

**68/-93

104/-81

3/-6

2/-7

30,000

**45/-72

82/-78

3/-5

2/-5

TEMPERATURE DEVIATION FROM STANDARD = -20

C/+20

LIMIT AIRSPEED

Figure A83.

T.O. GR1F16CJ11

A812Change 7

Fuel Flow (MIL/MAX AB)

DATA BASIS FLIGHT TEST

ENGINE F100-PW-229

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 A84.

T.O. GR1F16CJ11

Change 7A813

MIL Accelerations Sea Level

DATA BASIS FLIGHT TEST

CONDITIONS:

ENGINE F100PW229

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

9/0.5/33

1.15/1.19/1.08

0.95/0.91/0.93

300

0.45

8/0.5/31

10/0.7/37

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

19/1.6/78

23/1.9/93

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

28/2.6/120

33/3.0/140

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

35/3.4/149

41/4.0/174

47/4.6/201

1.25/1.31/1.12

0.89/0.85/0.92

550

0.83

29/3.1/127

35/3.8/155

42/4.4/183

49/5.1/213

56/5.9/244

1.29/1.36/1.14

0.88/0.84/0.91

600

0.91

35/4.1/157

43/4.9/190

51/5.8/225

59/6.7/261

67/7.7/299

1.35/1.44/1.19

0.89/0.85/0.91

CMBT SPD

56/7.6/256

66/9.0/303

77/10.4/351

87/11.7/399

99/13.1/449

1.24/1.27/1.09

0.90/0.87/0.91

CMBT SPD

KIAS/MACH

635/0.96

634/0.96

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

23/1.9/96

27/2.3/113

32/2.6/132

1.22/1.27/1.10

0.93/0.89/0.93

450

0.68

20/1.9/86

25/2.3/105

30/2.7/125

35/3.1/146

40/3.6/169

1.24/1.30/1.11

0.91/0.87/0.92

500

0.76

25/2.5/109

31/3.0/133

37/3.6/157

43/4.2/184

49/4.8/212

1.27/1.34/1.13

0.89/0.84/0.92

550

0.83

31/3.4/137

38/4.1/166

45/4.8/196

52/5.6/228

60/6.4/262

1.32/1.41/1.17

0.87/0.83/0.91

600

0.91

39/4.7/177

48/5.7/214

56/6.7/252

65/7.7/293

75/8.8/335

1.53/1.69/1.35

0.87/0.83/0.90

CMBT SPD

55/7.3/251

65/8.6/298

76/9.9/345

86/11.3/393

97/12.6/443

1.26/1.29/1.10

0.90/0.86/0.91

CMBT SPD

KIAS/MACH

616/0.93

0.98/0.98

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

5/0.3/17

6/0.3/21

7/0.4/26

8/0.5/31

10/0.6/37

1.15/1.19/1.08

0.95/0.91/0.93

300

0.45

9/0.6/35

11/0.8/43

13/0.9/51

15/1.1/61

18/1.3/72

1.18/1.22/1.09

0.94/0.91/0.93

350

0.53

13/1.0/55

16/1.2/66

19/1.5/78

23/1.7/92

27/2.0/108

1.20/1.25/1.10

0.94/0.91/0.93

EX =

400

0.60

18/1.5/76

22/1.8/91

26/2.2/108

30/2.5/126

35/2.9/146

1.23/1.29/1.11

0.93/0.89/0.93

450

0.68

24/2.2/100

28/2.6/120

33/3.0/141

39/3.5/164

45/4.0/189

1.26/1.32/1.13

0.90/0.86/0.92

500

0.76

30/3.0/128

36/3.5/153

42/4.2/180

49/4.8/209

56/5.5/240

1.30/1.37/1.16

0.88/0.83/0.91

RAG

550

0.83

37/4.1/164

45/4.9/196

52/5.7/230

61/6.6/266

69/7.5/304

1.39/1.49/1.23

0.86/0.82/0.89

600

0.91

53/6.6/239

63/7.8/284

73/9.1/331

84/10.4/381

96/11.8/434

0.85/0.80/0.87

CMBT SPD

60/7.8/275

71/9.2/323

82/10.5/373

93/11.9/424

105/13.3/477

1.38/1.44/1.20

0.88/0.85/0.90

CMBT SPD

KIAS/MACH

603/0.91

0.98/0.98

1.00/1.00

Figure A85.(Sheet 1)

Content .. 57 58 59 60 ..

F16C/D. FLIGHT MANUAL (2002) - page 59

F16C/D. FLIGHT MANUAL (2002) - page 59