Revision: Friday, June 07, 2013

BMS FLIGHT MODEL

JA-37D AIRCRAFT
SAAB Aerospace Corporation.

Manual reference: BMS-A1-JA37D-NFM-000

Changes: Draft Version

CAUTION STATEMENT: This document is to be use only for simulation. Do not try to apply the procedures and or advices contained in it if you have the
opportunity to fly this plane in real life. By the way, if you had (or still have) flew this aircraft, your comments, criticism and more are welcome.

LICENSE: This document has been created by TOPOLO for BMS, (http://www.benchmarksims.org/forum/content.php) all the values used to model the aircraft
behavior have been computed by him, like all performance charts presented here. If you want to use these data, or part of it, please contact the author by a
personal message to TOPOLO on benchmarksims forum.

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PART XI: PERFORMANCE DATA

Contents
PART XI: PERFORMANCE DATA ......................................................................................................................................... 2
PART 1: STANDARD DATA ............................................................................................................................................. 3
LIMITATIONS ............................................................................................................................................................. 3
CONFIGURATION DEFINITION ................................................................................................................................... 3
PART 2: CLIMB ............................................................................................................................................................... 6
INTRODUCTION ......................................................................................................................................................... 6
CONSTANT TRUE AIR SPEED CLIMB .......................................................................................................................... 6
SUBSONIC ISO-MACH CLIMB SCHEDULE................................................................................................................... 6
SUBSONIC ISO-CAS CLIMB SCHEDULE ....................................................................................................................... 6
PART 3: CRUISE, RANGE and ENDURANCE.................................................................................................................. 11
INTRODUCTION ....................................................................................................................................................... 11
PART 4: ACCELERATION .............................................................................................................................................. 13
INTRODUCTION ....................................................................................................................................................... 13
SAMPLE PROBLEM .................................................................................................................................................. 13
PART 5: TURNING ........................................................................................................................................................ 16
INTRODUCTION ....................................................................................................................................................... 16
TURN PERFORMANCE SUMMARY ........................................................................................................................... 16
ENERGY MACH DIAGRAM ....................................................................................................................................... 16

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PART 1: STANDARD DATA

the Drag coefficient of a given configuration from the

LIMITATIONS one of the reference configuration (clean).
This section deals with angle of attack (AoA) speed
and load factor limitations. The Drag Index of a configuration is the sum of the
Drag Index of each external load of the configuration.
The JA-37D is limited to an Angle of Attack (AoA) of 26 This means that the interactions between loads are
degrees (true AoA angle), this limitation is enforced by not managed by BMS DRAG INDEX SYSTEM: if the
FLCS in BMS. same load set (pylon, rail, launcher and missile) is
The maximum Indicated Air Speed (IAS) or Corrected installed twice under each wing, the drag contribution
Air Speed (CAS) is 785 Kts (1,450 Km/h) for a clean is twice the drag contribution of one set installed
aircraft. under each wing.

Load factor (Nz) is limited to +7g/-3g when gross Let’s call

weight is below 30,900 lbs (14,000 kg), above this
- DI the drag index of the configuration.
value, maximum allowed load factor is reduced as - CD CONF the Drag coefficient of the aircraft in
follow: the identified configuration
8.00 - CD REF the Drag coefficient of the aircraft in the
7.00 reference (clean) configuration, depending on
Max Load Factor (Nz)

6.00 Mach number and Angle of Attack (AoA)

5.00

4.00
CD CONF = CD REF + DI . R(Mach)
3.00
For the JA-37D, up to Mach 0.9, R(Mach) = 0.0005,
2.00
over Mach 1.0, R(Mach) = 0.001, between these
1.00
25,000 30,000 35,000 40,000 45,000 values, R = 0.0005 + (Mach-0.9).0.005
GW (lbs)
A consequence of this definition is that the Drag
In next sections, performance will be computed in contribution of a configuration does not depend on
assuming a load factor limit of 7G, whatever being the the angle of attack (AoA).
configuration gross weight, as it is the only limitation
STATION DEFINITION
performed by BMS JA37D FLCS.
The external stores of the JA-37D are located on the 7
CONFIGURATION DEFINITION available stations described in the figure bellow:
The performance data are described for various
aircraft configurations (loads, weight…). Each
configuration is defined by the set of loads (internal or
external) and the fuel fraction. For all weapons or
loads, contribution to the aircraft configuration is its
weight and its drag.

DRAG INDEX SYSTEM

Drag of loads is modeled through the general BMS
Drag Index mechanism: each object has its own Drag
Index value (DI) that is converted into Drag coefficient
(CD) by a ratio specific to the aircraft and depending CONFIGURATION 0
form the Mach number. This allows the definition of This configuration is the reference configuration,
without any external loads, but with 50% or the
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internal fuel, the equipped pilot, and the internal gun Configuration 1
8.00
(KCA 30mm Oerlikon) with all its 126 rounds. 7.00

Max Load Factor (Nz)

6.00

The zero fuel weight of this configuration is 26,289 lbs 5.00

4.00
(11,909 kg). 3.00

2.00

The 50% internal fuel weight is 5,239 lbs (2,373 kg) 1.00
2,000 4,000 6,000 8,000 10,000

with a fuel density of 0.81 kg/l. Remaining fuel (lbs)

The Gross weight of the configuration is 31,528 lbs CONFIGURATION 2

(14,282 Kg). This configuration is defined by external stores being
two short range AA missile (AIM-9M or RB-24J) on
By definition, the Drag Index of this configuration is 0. station 1 and 7, two Skyflash (RB-71) missile on
stations 2 and 6, 50% or the internal fuel, the
The recommended load factor limit (Nz max), based
equipped pilot, and the internal gun (KCA 30mm
on remaining fuel, (initial fuel load is 10,480lbs) is the
Oerlikon) with all its 126 rounds.
following:

Configuration 0
The weight of the two AIM-9M with their pylon, rail
8.00 and launcher is 654 lbs (296 kg).
7.00
Max Load Factor (Nz)

6.00

5.00
The weight of the two Skyflash with their pylon, rail
4.00 and launcher is 1,286 lbs (583 kg).
3.00

2.00

1.00
The zero fuel weight of this configuration is 28,229 lbs
2,000 4,000 6,000
Remaining fuel (lbs)
8,000 10,000
(12,798 kg).

CONFIGURATION 1 The 50% internal fuel weight is 5,239 lbs (2,373 kg)
This configuration is the regular combat configuration, with a fuel density of 0.81 kg/l.
with two short range AA missile (AIM-9M or RB-24J) The Gross weight of the configuration is 33,468 lbs
on station 1 and 7, 50% or the internal fuel, the
(15,161 Kg).
equipped pilot, and the internal gun (KCA 30mm
Oerlikon) with all its 126 rounds. The Drag Index of this configuration is 46.

The weight of the two AIM-9M with their pylon, rail The recommended load factor limit (Nz max), based
and launcher is 654 lbs (296 kg). on remaining fuel, (initial fuel load is 10,480lbs) is the
following:
The zero fuel weight of this configuration is 26,943 lbs
(12,295 kg). Configuration 2
8.00

7.00
The 50% internal fuel weight is 5,239 lbs (2,373 kg)
Max Load Factor (Nz)

6.00

with a fuel density of 0.81 kg/l. 5.00

4.00

3.00
The Gross weight of the configuration is 32,182 lbs 2.00

(14,579 Kg). 1.00

2,000 4,000 6,000 8,000 10,000
Remaining fuel (lbs)

The Drag Index of this configuration is 18.

CONFIGURATION 3
The recommended load factor limit (Nz max), based TO BE DEFINED.
on remaining fuel, (initial fuel load is 10,480lbs) is the
following:

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Level Flight Envelope

DATA BASIS : COMPUTED Aircraft : SAAB JA-37D Viggen

CONDITIONS: Engine :VOLVO-RM8B
Standard Day - ISA
Max A/B

Config. 0

Config. 1

Config. 2

VNE: 785 Kts (IAS)

DATA BASIS : COMPUTED Aircraft : SAAB JA-37D Viggen

CONDITIONS: Engine :VOLVO-RM8B
Standard Day - ISA
MILL Power

Config. 1

Config. 0

Config. 2

VNE: 785 Kts (IAS)

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PART 2: CLIMB

INTRODUCTION This flight profile assumes the climb angle of the flight
This section defines the climb performances of the JA- path is continuously adapted to keep the Mach
37D airplane. number constant along the time.

CONSTANT TRUE AIR SPEED CLIMB The values displayed in these diagram do not take into
For each identified configuration, two main climb account time, distance and fuel required to accelerate
performances are detailed: Constant true air speed to the desired Mach number, nor to rotate from level
climb rate, and climb angle. flight to climb attitude.

The first one is the vertical velocity (in ft/s), of the These diagrams contain performances for various
aircraft when load factor is 1G and true air speed aircraft configurations, assumed to be effective at the
(TAS) is constant, values are given with Maximum start of the climb.
After Burner (Max A/B) and Military Power (MIL).
SUBSONIC ISO-CAS CLIMB SCHEDULE
The second one is the climb angle under the same This kind of diagram describe time, distance and fuel
conditions (angle between the flight path, or velocity required to climb to a given altitude, using maximum
vector, and the horizontal), it is materialized in the Military Thrust and an Iso-CAS flight profile until a
Head Up Display by the position of the Flight Path given Mach number is reached, then an iso-Mach
Marker (FPM) along the vertical scale. flight profile.

Note that these values are lower than Constant Mach This flight profile assumes the climb angle of the flight
Number Climb rate and angle below 36,000ft, as path is continuously adapted to keep the Corrected
sound speed decrease with altitude, a constant Mach Air Speed (CAS) constant along the time, and then
number climb means True air speed decreasing, and Mach number.
consequently allow higher climb rates and angles.
The values displayed in these diagram do not take into
On the opposite, a constant Indicated Air Speed (IAS) account time, distance and fuel required to accelerate
climb provide a much lower climb rate as it request a to the desired Mach number, nor to rotate from level
True Air Speed increase when climb. flight to climb attitude.

In addition, for each configuration, you will find a These diagrams contain performances for various
Climb Schedule Table giving the best climb speed aircraft configurations, assumed to be effective at the
(Mach number, Indicated Air Speed and True Air start of the climb.
Speed) along altitude.

SUBSONIC ISO-MACH CLIMB SCHEDULE

This kind of diagram describe time, distance and fuel
required to climb to a given altitude, using maximum
A/B thrust and an Iso-Mach flight profile.

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DATA BASIS : COMPUTED Aircraft : SAAB JA-37D Viggen

Engine :VOLVO-RM8B

CONDITIONS: CONFIGURATION 1
Standard Day - ISA 2xAIM-9
Max A/B GW=32,182 lbs

Climb Rate at Constant True Air Speed

800

750

700

650
Altitude
600

550 0
Excess Specific Power (ft/s)

500
10,000
450

400 20,000

350
30,000
300

250 40,000

200

150

100

50

0
0.00 0.10 0.20 0.30 0.40 0.50 0.60 0.70 0.80 0.90 1.00 1.10 1.20 1.30 1.40 1.50 1.60 1.70 1.80 1.90 2.00 2.10 2.20 2.30 2.40
Mach

Climb Angle at Constant True Air Speed

90.00

80.00

70.00 Altitude

60.00 0
Climb Angle (deg)

10,000
50.00
20,000

40.00
30,000

30.00 40,000

20.00

10.00

0.00
0.00 0.10 0.20 0.30 0.40 0.50 0.60 0.70 0.80 0.90 1.00 1.10 1.20 1.30 1.40 1.50 1.60 1.70 1.80 1.90 2.00 2.10 2.20 2.30 2.40
Mach

Climb Schedule (maximum climb speed)

Alt (ft) CAS Mach Vz (ft/s) TAS
0 594 0.90 740 594
5,000 549 0.90 645 585
10,000 499 0.90 552 575
15,000 477 0.92 464 576
20,000 446 0.94 386 577
25,000 403 0.94 312 566
30,000 497 1.30 272 766
35,000 525 1.50 220 865
40,000 475 1.50 160 860

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 Revision: Friday, June 07, 2013

DATA BASIS : COMPUTED Aircraft : SAAB JA-37D Viggen

Engine :VOLVO-RM8B

CONDITIONS: CONFIGURATION 1
Standard Day - ISA 2xAIM-9
MIL Power GW=32,182 lbs

Instantaneous Climb Rate at Constant True Air Speed

200

Altitude
150

0
Excess Specific Power (ft/s)

10,000

100 20,000

30,000

40,000

50

0
0.00 0.10 0.20 0.30 0.40 0.50 0.60 0.70 0.80 0.90 1.00 1.10 1.20 1.30 1.40 1.50 1.60 1.70 1.80 1.90 2.00 2.10 2.20 2.30 2.40
Mach
Climb Angle at Constant True Air Speed

90.00

80.00

70.00 Altitude

60.00 0
Climb Angle (deg)

10,000
50.00
20,000

40.00
30,000

30.00 40,000

20.00

10.00

0.00
0.00 0.10 0.20 0.30 0.40 0.50 0.60 0.70 0.80 0.90 1.00 1.10 1.20 1.30 1.40 1.50 1.60 1.70 1.80 1.90 2.00 2.10 2.20 2.30 2.40
Mach

Climb Schedule (maximum climb speed)

Alt (ft) CAS Mach Vz (ft/s) TAS
0 356 0.54 147 356
5,000 390 0.64 125 416
10,000 376 0.68 107 434
15,000 401 0.78 90 489
20,000 377 0.80 71 491
25,000 358 0.84 53 506
30,000 324 0.84 21 495

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Iso-Mach Climb Schedule

DATA BASIS : COMPUTED
Aircraft : SAAB JA-37D Viggen
CONDITIONS: Engine :VOLVO-RM8B
Standard Day - ISA
Max A/B Constant Mach number : 0.9

Time to Climb at Iso-Mach

40,000

35,000

30,000

25,000
Altitude (ft)

20,000 Configuration 0
Configuration 1
Configuration 2
15,000

10,000

5,000

0
0 15 30 45 60 75 90 105 120
Time to climb (s)

Distance to Climb at Iso-Mach

40,000

35,000

30,000

25,000
Altitude (ft)

20,000 Configuration 0
Configuration 1
Configuration 2
15,000

10,000

5,000

0
0 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20
Distance to climb (Nm)

Fuel to Climb at Iso-Mach

40,000

35,000

30,000

25,000
Altitude (ft)

20,000 Configuration 0
Configuration 1
Configuration 2
15,000

10,000

5,000

0
0 250 500 750 1,000 1,250 1,500
Fuel to climb (lbs)

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Iso-CAS Climb Schedule

DATA BASIS : COMPUTED
Aircraft : SAAB JA-37D Viggen
CONDITIONS: Engine :VOLVO-RM8B
Standard Day - ISA
MIL Thrust Constant CAS : 365Kts until M0.9

Time to Climb at Iso-CAS until maximum Mach

25,000

20,000

15,000
Altitude (ft)

Configuration 0
Configuration 1

10,000 Configuration 2

5,000

0
0 30 60 90 120 150 180 210 240 270 300 330 360 390 420
Time to climb (s)

Distance to Climb at Iso-CAS until maximum Mach

25,000

20,000

15,000
Altitude (ft)

Configuration 0
Configuration 1

10,000 Configuration 2

5,000

0
0 5 10 15 20 25 30 35 40 45 50
Distance to climb (Nm)

Fuel to Climb at Iso-CAS until maximum Mach

25,000

20,000

15,000
Altitude (ft)

Configuration 0
Configuration 1

10,000 Configuration 2

5,000

0
0 50 100 150 200 250 300 350 400 450 500 550 600 650 700 750
Fuel to climb (lbs)

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PART 3: CRUISE, RANGE and ENDURANCE

required to sustain a given Mach number at a given

INTRODUCTION altitude, the autonomy at a given Mach number and
This section presents the fuel management data altitude (distance, in Nm that can be covered with a
during cruise flight (constant speed and altitude in unit amount of fuel: 1,000lbs), and the endurance at a
Military Thrust). For each aircraft configuration, you given Mach number and altitude (time in minutes that
will find the instantaneous fuel flow (in lbs/h)
can be flew with a unit amount of fuel: 1,000lbs).

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Fuel Flow – Endurance - Autonomy

DATA BASIS : COMPUTED Aircraft : SAAB JA-37D Viggen
Engine :VOLVO-RM8B
CONDITIONS:
Standard Day - ISA CONFIGURATION 1
MIL Thrust 2xAIM-9
GW=32,182 lbs
Fuel Flow for Sustained Mach number

12,500

10,000

7,500
10,000
Flow (lbs / h)

20,000

30,000
5,000

40,000

2,500

0
0.20 0.30 0.40 0.50 0.60 0.70 0.80 0.90 1.00

Mach

Endurance for Sustained Mach number

25.00

20.00
Time (min) for 1,000 lbs KRO

15.00
10,000

20,000

30,000
10.00

40,000

5.00

0.00
0.20 0.30 0.40 0.50 0.60 0.70 0.80 0.90 1.00

Mach

Autonomy for Sustained Mach number

200.00

180.00

160.00
Distance (Nm) for 1,000 lbs KRO

140.00
0

120.00
10,000

100.00 20,000

30,000
80.00

40,000
60.00

40.00

20.00

0.00
0.20 0.30 0.40 0.50 0.60 0.70 0.80 0.90 1.00

Mach

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PART 4: ACCELERATION

Find initial Mach number (0.8) on horizontal axis (A),

INTRODUCTION go vertical up to the curve related to the desired
Performances described in this section are related to altitude: 20,000ft (A’), then go horizontal to find the
level flight (1G) acceleration. It’s organized by
start time (B) : 25s
configuration (all data presented on one figures are
related to the same configuration). The aircraft Find final Mach number (1.3) on horizontal axis (C), go
configuration is assumed to be the one at the vertical up to the curve related to the desired altitude:
beginning of the acceleration run (specifically the 20,000ft (C’), then go horizontal to find the start time
remaining fuel). (D): 80s.

Figures present the time, horizontal distance and fuel Compute difference between final and initial values:
quantity required to accelerate from a give Mach the time required to accelerate from M0.8 to M1.3 at
number to a greater at constant altitude. 20,000 in this configuration is 80 – 25 = 55s.

SAMPLE PROBLEM Same method is to be used to find the horizontal

Use case is to accelerate from M0.8 to M1.3 at distance (in Nm) and the fuel quantity (in lbs) required
20,000ft. to perform the same acceleration.

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Acceleration Schedule
DATA BASIS : COMPUTED Aircraft : SAAB JA-37D Viggen
Engine :VOLVO-RM8B
CONDITIONS:
Standard Day - ISA CONFIGURATION 1
Max A/B 2xAIM-9
GW=32,182 lbs
0 10,000 20,000 Time To Mach

Altitude (ft)

180

165

150

135

120

105
Time (s)

90

75

60

45

30

15

0
0.30 0.40 0.50 0.60 0.70 0.80 0.90 1.00 1.10 1.20 1.30 1.40 1.50 1.60 1.70

Mach

0 10,000 20,000 Distance To Mach

Altitude (ft)

35.0

30.0

25.0

20.0
Distance (Nm)

15.0

10.0

5.0

0.0
0.30 0.40 0.50 0.60 0.70 0.80 0.90 1.00 1.10 1.20 1.30 1.40 1.50 1.60 1.70

Mach

0 10,000 20,000 Fuel To Mach

Altitude (ft)

5,000

4,500

4,000

3,500

3,000
Fuel (lbs)

2,500

2,000

1,500

1,000

500

0
0.30 0.40 0.50 0.60 0.70 0.80 0.90 1.00 1.10 1.20 1.30 1.40 1.50 1.60 1.70

Mach

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Acceleration Schedule
DATA BASIS : COMPUTED Aircraft : SAAB JA-37D Viggen
Engine :VOLVO-RM8B
CONDITIONS:
Standard Day - ISA CONFIGURATION 1
Max A/B 2xAIM-9
GW=32,182 lbs
30,000 35,000 40,000
Time To Mach
Altitude
180

165

150

135

120

105
Time (s)

90

75

60

45

30

15

0
0.70 0.80 0.90 1.00 1.10 1.20 1.30 1.40 1.50 1.60 1.70 1.80 1.90 2.00

Mach

30,000 35,000 40,000 Distance To Mach

Altitude (ft)

45.0

40.0

35.0

30.0
Distance (Nm)

25.0

20.0

15.0

10.0

5.0

0.0
0.70 0.80 0.90 1.00 1.10 1.20 1.30 1.40 1.50 1.60 1.70 1.80 1.90 2.00

Mach

30,000 35,000 40,000 Fuel To Mach

Altitude (ft)

2,500

2,000

1,500
Fuel (lbs)

1,000

500

0
0.70 0.80 0.90 1.00 1.10 1.20 1.30 1.40 1.50 1.60 1.70 1.80 1.90 2.00

Mach

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PART 5: TURNING

maximum possible lift) turn rate (d/s), normal load

INTRODUCTION factor (Ng) and minimum turn radius.
This section is organized by aircraft configurations. For
each of them, you will find the following set of figures: ENERGY MACH DIAGRAM
An Energy Mach Diagram is given per altitude (Turn
TURN PERFORMANCE SUMMARY Rate vs Calibrated Air Speed), with Iso-Ps (Extra
Sustained Turn Rate summary: three figures giving for Specific Power) curves set, and graphical indication of
different altitudes, the maximum sustainable specific performances: maximum reachable
(constant true air speed and altitude) turn rate (d/s), (maximum lift and load factor) turn rate, maximum
normal load factor (Ng) and minimum turn radius. sustainable (Ps=0) turn rate, minimum instantaneous
Maximum Turn Rate summary: three figures giving for and sustainable (Ps=0) turn radius.
different altitudes, the maximum reachable (at

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 Revision: Friday, June 07, 2013

Sustained Turn Summary

DATA BASIS : COMPUTED Aircraft : SAAB JA-37D Viggen
Engine :VOLVO-RM8B

CONDITIONS: CONFIGURATION 1
Standard Day - ISA 2xAIM-9
Max A/B GW=32,182 lbs

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 Revision: Friday, June 07, 2013

Instantaneous Turn Summary

DATA BASIS : COMPUTED Aircraft : SAAB JA-37D Viggen
Engine :VOLVO-RM8B

CONDITIONS: CONFIGURATION 1
Standard Day - ISA 2xAIM-9
Max A/B GW=32,182 lbs

Structural limit = 7G

BMS-Flight Model - JA37D Page - 18 / 26 Section XI

 Revision: Friday, June 07, 2013

Energy Mach Diagram at 0 ft

DATA BASIS : COMPUTED Aircraft : SAAB JA-37D Viggen
Engine :VOLVO-RM8B

CONDITIONS: CONFIGURATION 1
Standard Day - ISA 2xAIM-9
Max A/B GW=32,182 lbs

2G 3G 4G 5G 6G 7G 8G 9G
30.00

28.00

26.00

Max. Instantaneous Turn Rate

24.00 24.0 deg/s @ 310Kts

22.00
Ps = -600ft/s

20.00
Min. Instantaneous Turn Radius
Turn Rate (degrees per second)

1,245ft @ 238Kts
Ps = -400ft/s
18.00

16.00 Ps = -200ft/s
Max. Sustained Turn Rate
13.2 deg/s @ 561Kts
14.00
Min. Sustained Turn Radius
1,319ft @ 165Kts

12.00

Ps = +200ft/s
10.00

8.00
Ps = +400ft/s
MAXIMUM AIR SPEED

6.00
Ps = +600ft/s

4.00

2.00

0.00
0 50 100 150 200 250 300 350 400 450 500 550 600 650 700 750 800

CAS (Kts)

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Energy Mach Diagram at 5,000 ft

DATA BASIS : COMPUTED Aircraft : SAAB JA-37D Viggen
Engine :VOLVO-RM8B

CONDITIONS: CONFIGURATION 1
Standard Day - ISA 2xAIM-9
Max A/B GW=32,182 lbs

2G 3G 4G 5G 6G 7G 8G 9G
30.00

28.00

26.00

24.00
Max. Instantaneous Turn Rate
22.4 deg/s @ 317 Kts
22.00

20.00
Min. Instantaneous Turn Radius
Turn Rate (degrees per second)

1,453 ft @ 256 Kts

Ps = -600ft/s
18.00

Ps = -400ft/s
16.00

14.00 Ps = -200ft/s
Min. Sustained Turn Radius

Max. Sustained Turn Rate

11.5 deg/s @ 519 Kts
1,590 ft @ 159 Kts

12.00

10.00

Ps = +200ft/s
8.00
MAXIMUM AIR SPEED

6.00 Ps = +400ft/s

4.00

2.00
Ps = +600ft/s

0.00
0 50 100 150 200 250 300 350 400 450 500 550 600 650 700 750 800

CAS (Kts)

BMS-Flight Model - JA37D Page - 20 / 26 Section XI

 Revision: Friday, June 07, 2013

Energy Mach Diagram at 10,000 ft

DATA BASIS : COMPUTED Aircraft : SAAB JA-37D Viggen
Engine :VOLVO-RM8B

CONDITIONS: CONFIGURATION 1
Standard Day - ISA 2xAIM-9
Max A/B GW=32,182 lbs

2G 3G 4G 5G 6G 7G 8G 9G
30.00

28.00

26.00

24.00

22.00

Max. Instantaneous Turn Rate

21.6 deg/s @ 314 Kts
20.00
Min. Instantaneous Turn Radius
Turn Rate (degrees per second)

1,706 ft @ 264 Kts

18.00

Ps = -600ft/s
16.00

Ps = -400ft/s
14.00
Min. Sustained Turn Radius
1,960 ft @ 149 Kts

Ps = -200ft/s
12.00 Max. Sustained Turn Rate
9.9 deg/s @ 471 Kts

10.00

8.00
MAXIMUM AIR SPEED

Ps = +200ft/s

6.00

4.00 Ps = +400ft/s

2.00

0.00
0 50 100 150 200 250 300 350 400 450 500 550 600 650 700 750 800

CAS (Kts)

BMS-Flight Model - JA37D Page - 21 / 26 Section XI

 Revision: Friday, June 07, 2013

Energy Mach Diagram at 15,000 ft

DATA BASIS : COMPUTED Aircraft : SAAB JA-37D Viggen
Engine :VOLVO-RM8B

CONDITIONS: CONFIGURATION 1
Standard Day - ISA 2xAIM-9
Max A/B GW=32,182 lbs

2G 3G 4G 5G 6G 7G 8G 9G
30.00

28.00

26.00

24.00

22.00

20.00
Max. Instantaneous Turn Rate
Turn Rate (degree per second)

18.6 deg/s @ 326Kts

18.00

16.00
Min. Instantaneous Turn Radius
2,013ft @ 255Kts
14.00
Ps = -600ft/s

12.00
Ps = -400ft/s

Ps = -200ft/s
10.00
Max. Sustained Turn Rate
7.9 deg/s @ 439Kts
8.00
Min. Sustained Turn Radius

MAXIMUM AIR SPEED

2,578ft @ 140Kts

6.00
Ps = +200ft/s

4.00

2.00
Ps = +400ft/s

0.00
0 50 100 150 200 250 300 350 400 450 500 550 600 650 700 750 800

CAS (Kts)

BMS-Flight Model - JA37D Page - 22 / 26 Section XI

 Revision: Friday, June 07, 2013

Energy Mach Diagram at 20,000 ft

DATA BASIS : COMPUTED Aircraft : SAAB JA-37D Viggen
Engine :VOLVO-RM8B

CONDITIONS: CONFIGURATION 1
Standard Day - ISA 2xAIM-9
Max A/B GW=32,182 lbs

2G 3G 4G 5G 6G 7G 8G 9G
30.00

28.00

26.00

24.00

22.00

20.00
Turn Rate (degrees per second)

18.00 Max. Instantaneous Turn Rate

17.4 deg/s @ 333 Kts

16.00
Min. Instantaneous Turn Radius
2,392 ft @ 269 Kts
14.00

Ps = -600ft/s
12.00
Ps = -400ft/s

10.00
Ps = -200ft/s

8.00 Max. Sustained Turn Rate

Min. Sustained Turn Radius

7.0 deg/s @ 402 Kts

3,786 ft @ 143 Kts

MAXIMUM AIR SPEED

6.00

4.00 Ps = +200ft/s

2.00

0.00
0 50 100 150 200 250 300 350 400 450 500 550 600 650 700 750 800

CAS (Kts)

BMS-Flight Model - JA37D Page - 23 / 26 Section XI

 Revision: Friday, June 07, 2013

Energy Mach Diagram at 25,000 ft

DATA BASIS : COMPUTED Aircraft : SAAB JA-37D Viggen
Engine :VOLVO-RM8B

CONDITIONS: CONFIGURATION 1
Standard Day - ISA 2xAIM-9
Max A/B GW=32,182 lbs

2G 3G 4G 5G 6G 7G 8G 9G
30.00

28.00

26.00

24.00

22.00

20.00
Turn Rate (degrees per second)

18.00

Max. Instantaneous Turn Rate

16.00
15.7 deg/s @ 340 Kts
Min. Instantaneous Turn Radius
2,871 ft @ 246 Kts
14.00

12.00
Ps = -600ft/s

10.00 Ps = -400ft/s

8.00 Ps = -200ft/s
Min. Sustained Turn Radius

Max. Sustained Turn Rate

5,674 ft @ 168 Kts

MAXIMUM AIR SPEED

5.8 deg/s @ 363 Kts

6.00

4.00

Ps = +200ft/s
2.00

0.00
0 50 100 150 200 250 300 350 400 450 500 550 600 650 700 750 800

CAS (Kts)

BMS-Flight Model - JA37D Page - 24 / 26 Section XI

 Revision: Friday, June 07, 2013

Energy Mach Diagram at 30,000 ft

DATA BASIS : COMPUTED Aircraft : SAAB JA-37D Viggen
Engine :VOLVO-RM8B

CONDITIONS: CONFIGURATION 1
Standard Day - ISA 2xAIM-9
Max A/B GW=32,182 lbs

2G 3G 4G 5G 6G 7G 8G 9G
30.00

28.00

26.00

24.00

22.00

20.00
Turn Rate (degrees per second)

18.00

16.00

Max. Instantaneous Turn Rate

14.00 14.0 deg/s @ 357 Kts
Min. Instantaneous Turn Radius
3,488 ft @ 234 Kts
12.00

10.00
Ps = -600ft/s

Ps = -400ft/s
8.00
Min. Sustained Turn Radius

Ps = -200ft/s
8,293 ft @ 206 Kts

6.00
MAXIMUM AIR SPEED

Max. Sustained Turn Rate

4.7 deg/s @ 329 Kts

4.00

2.00
Ps = +200ft/s

0.00
0 50 100 150 200 250 300 350 400 450 500 550 600 650 700 750 800

CAS (Kts)

BMS-Flight Model - JA37D Page - 25 / 26 Section XI

 Revision: Friday, June 07, 2013

Energy Mach Diagram at 35,000 ft

DATA BASIS : COMPUTED Aircraft : SAAB JA-37D Viggen
Engine :VOLVO-RM8B

CONDITIONS: CONFIGURATION 1
Standard Day - ISA 2xAIM-9
Max A/B GW=32,182 lbs

2G 3G 4G 5G 6G 7G 8G 9G
30.00

28.00

26.00

24.00

22.00

20.00
Turn Rate (degrees per second)

18.00

16.00

14.00
Max. Instantaneous Turn Rate
12.8 deg/s @ 357 Kts
12.00
Min. Instantaneous Turn Radius
4,287 ft @ 239 Kts
10.00

8.00 Ps = -600ft/s
Min. Sustained Turn Radius

Ps = -400ft/s
12,174 ft @ 228 Kts

6.00 Ps = -200ft/s
MAXIMUM AIR SPEED

Max. Sustained Turn Rate

4.00 3.7 deg/s @ 295 Kts

2.00

Ps = +200ft/s
0.00
0 50 100 150 200 250 300 350 400 450 500 550 600 650 700 750 800

CAS (Kts)

BMS-Flight Model - JA37D Page - 26 / 26 Section XI