design data sheet (10 2015)

7/24/2019 Design Data Sheet (10 2015)

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University of TripoliFaculty of Engineering

Aeronautical Engineering

Department

Mr. Adel Ali Kurban

9/30/2015

AERONAUTICAL ENGINEERS

DATASHEETS

AE 465 Aircraft Design


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3/42

- 1 -

1 Weight Estimation

1.1 Initial Weight Analysis

tfocrewPLFETO WWWWWW ++++= (1.1)

tfocrewEOE WWWW ++= (1.2)

TOtfotfo WMW = (1.3)

Mtfo- Relationship Wtfoand WTO(usually around 0.005)

FresFusedF WWW += (1.4)

FusedresFres WMW = (1.5)

Mres - The ratio of reserve fuel and fuel required for the mission

PLFOETO WWWW ++= (1.6)

B

AW

W

=)(log

E

TO

10 (1.7)

See Table 1.7 for A and B values.

=

=

+=ni

i i

i

TO

ffW

W

W

WM

1

11 (1.8)

TOffFused WMW = )1(

(1.9)

TOffresF WMMW += )1)(1( (1.10)

Piston-Propeller AircraftEndurance

=

+1

ln3751

i

i

ltrltrP

P

ltr

ltrW

W

D

L

cVE

(1.11)

ltrltrP

P

ltrltr

D

L

c

VE

i

i

eW

W

+=

375

1

(1.12)

Range

=

+1

ln375i

i

crcrP

Pcr

W

W

D

L

cR

(1.13)

crcrP

P

cr

D

L

c

R

i

i eW

W

+

=375

1

(1.14)


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- 2 -

Jet AircraftEndurance

=

+1

1

i

i

ltrltrj

ltrW

Wln

D

L

cE

(1.15)

(

ltr

ltrltrj

D

L

Ec

i

i eW

W

+

=1

(1.16)

Range

=

+1i

i

crcrj

crW

Wln

D

L

c

VR

(1.17)

crcrj

cr

D

L

c

V

R

i

i eW

W

+

=1

(1.18)

Table 1.1 Recommendation Values for WPLand WCrew

Pay load Weight Short /medium Long distance

Passenger Crew member Passenger Crew member

Weight per passenger 190 -200 Ibs 190-200 Ibs 190-200 Ibs 190-200 IbsWeight per Baggage 30 Ibs 30 Ibs 40 Ibs 40 Ibs

Military 200 Ibs 200 Ibs

Table 1.2Recommendation Values for WTO/WPL

Airplane Type WTO/WPL

Homebuilt 2-8

Single Engine 3-6

Twin Engine 2-5

Agricultural 2-3

Business Jets 3-5

Regional Turboprops 3-4

Transport Jets 3-5

Military Trainers

Fighters 10-18Military Patrol, Bombers, and Transports 3-6

Flying Boats, Amphibious and Float Airplanes 2-4

Supersonic Cruise -


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6/42

- 4 -

Table 1.6Value for L/D, Cj,pand for Cp for Cruise

Aircraft Type:

Cruise

L/D Cj Cp p

lbs/lbs/hr lbs/lbs/hr

1 Homebuilt 8-10 0.6-0.8 0.72 Single Engine 8-10 0.5 -0.7 0.8

3 Twin Engine 8-11 0.5 -0.7 0.82

4 Agricultural 5-7 0.5 -0.7 0.82

5 Business Jets 10-12 0.5-0.9

6 Regional TBPs 11-13 0.4 - 0.6 0.85

7 Transport Jets 13-15 0.5 -0.9

8 Military Trainers 8-10 0.5-1.0 0.4-0.6 0.82

9 Fighters 4-7 0.4-1.4 0.5-0.7 0.820

10 Mil.Patrol Bomb. Transport 13-15 0.5-0.9 0.4-0.7 0.820

11 Flying Boats, Amphibious Float

Airplanes

10-12 0.5-0.9 0.5-0.7 0.820

12 Super Sonic Cruise 4-6 0.7-1.5

Table 1.7 Regression coefficient off A and B

Airplane Type A B

Homebuilt: Personal Fun and

transportation

0.3411 0.9519

Scaled fighters 0.5542 0.8654

Composites 0.8222 0.8050

Single Engine Propeller Driven -0.1440 1.1162

Twin Engine Propeller Driven 0.0966 1.0298

Twin Engine Composites 0.1130 1.0403

Agricultural -0.4398 1.1946

Business Jets 0.2678 0.9979

Regional Turboprops 0.3774 0.9647

Transport Jets 0.0833 1.0383

Military Trainers: Jets 0.6632 0.8640

Turboprops -1.4041 1.4660

Turboprops without item No.2 0.1677 0.9978

Piston/Propellers 0.5627 0.8761

Fighters: Jets ( + external load ) 0.5091 0.9505

Jets (clean) 0.1362 1.0116

Turboprops (+ external load) 0.2705 0.9830

Military Patrol,

Bomber &

Transport:

Jets -0.2009 1.1037

Turboprops -0.4179 1.1446

Flying boats, Amphibious, Float Airplanes 0.1703 1.0083Supersonic Cruise 0.4221 0.9876


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- 5 -

1.2 Weight Analysis methods1.3 Statistical Weight Estimation MethodsStatistical Aircraft Component Methods

Table 1.8 Approximate Empty Weight Build-up

Group Transports

&

Bombers

Fighters General

aviation

Group [Ib] CG location ofgroup

Wwing 10.0 9.0 2.5 SEXPO_Wing[ft2] 40% MAC

WH-tail 5.5 4.0 2.0 SEXPO_H_tail[ft2] 40% MAC

WV-tail 5.5 5.3 2.0 SEXPO_V_tail[ft2] 40% MAC

WFuselage 5.0 4.8 1.4 SEXPO_H_tail[ft2] 40-50%

Fuselage length

WLand_gear 0.043 .033

0.045 Navy

.057 WTO[Ib]

WNose 0.15 0.15 0.15 WLand_gaer[Ib]At point of

attachment

WMain 0.85 0.85 0.85 WLand_gear[Ib] At point ofattachment

Winstalled_engine 1.3 1.3 1.4 WEngine[Ib] 50% of enginelength

Wmise 0.17 .17 .10 WTO[Ib] 40-50%Fuselage length

Table 1.9 Reduction of weight due to use of new materials or new Technology

Structural Component WEnew/ WEold

Composites Al-Li

Primary

Structure Fuselage 0.75-0.85 0.90

Wing, Vertical Tail, Canard or Horizontal Tail 0.75 0.90

Landing Gear 0.88 0.90

Secondary

Structure Flaps, Slats, Access Panels, Fairings 0.70 0.90

Interior Furnishing 0.50 N.A

Air Induction System 0.70 0.90


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- 6 -

Table 1.10 Mass of Some miscellaneous components

No. Component Type, description, details Mass (Ib)

1 Seat Flight deck civil 53-62

2 Fighter pilot (ejection seat) 209-243

3 Passenger economy 29-35

4 Passenger tourist 44-62

5 Troop 9-13

6 Missile and bomb ACM, AGM-129 2756

7 AGM-130 2917

8 HARM, AGM-88 560

9 Harpoon, AGM-84A 1169

10 Hell fire, AGM-114A 101

11 Maverick, AGM-65A 463

12 Penguin 2, AGM-119B 849

13 Sea Eagle 1323

14 Sidewinder, AIM-9J 192

15 Sparrow, AIM-7F 501

16 Stinger, FIM-92 35

17 TOW, BGM-71A/B 42

18 Standard, AGM-78 1356

19 SLAM, AGM-84E 1389

20 Stick, yoke, wheel Side-stick 0.22

21 Stick 1

22 Yoke, wheel 2

23 Parachute Civil 9

24 Military 18

25 Instruments

Compass, tachometer, altimeter, airspeed indicator,

clock, rate of climb, bank angle indicator,accelerometer, GPS, etc.

1-2

26 Gyroscope (x,y,z) 1-4

27 Display 2-9

28 Lavatories Short-range aircraft 0.13N1.3

29 Long-range aircraft 0.5N 1.3 0.5 N1.4

30 Business jet 1.7N 1.3 1.7 N1.5


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- 7 -

2 Constraint Analysis

Rearranged Equations

The referenced equations are rearranged into a format of:

=

S

W

P

W

W

T

TOTOTO

for

2.1

Stall SpeedFAR 23 Single engine airplane Vs< 61 kt at WTO

Multi engine airplane with WTO61kt ( unless meet climb

gradient criteria Par 23.67

FAR 25 No requirements for min Vs

CLVS

WTOmaxS

2

2

1=

TO

(2.1)

2.2

Take-off Distance, FAR 23Propeller driven

=

S

WCLTOP

P

W

TO

TOmax

TO

123

(2.2)

Jet driven:

=

S

W

W

T

TOTOmaxTOFL

TO

CLS.02960

1 (2.3)

Other necessary equations are: speed)off-liftcalledaslo(liftoff@

211

.

CLCL TOmaxTO = (2.4)

2

2323 009094 TOP.TOP.STOG += (2.5)

2

2323 014901348 TOP.TOP.STO += (2.6)

And units onhp

are

ft

lbTOP

f

2

2

23

2.3 Take-off distance, FAR 25

Jet driven:

SCL

S

W

W

T

TOFLTOmax

TO

TO

.

=

537

(2.7)

Propeller driven:

=

S

W

SCL

P

W

TO

TOFLTOmax

TO .93112

(2.8)

Using

PT

=

2000

5750 & 922000

5750 .P

T =

= (2.9)


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- 8 -

2.4 Landing Distance

FAR 23

2265.0SLLG VS = (2.10)

LGL s.s = 9381 (2.11)

SCLkS

WLh@

LTO

max

.

LISA.L

=

7772 (2.12)

When WkW TOLL = Note that units for 0.265 in SLGequation are ft/kt

2

FAR 25

22 507030 SLAFL V.V.S == (2.13)

23042060 SLFLL V.S.S == (2.14)

SCLkS

WFL

LTO

max

.

L

=

81342 (2.15)

Note that units for 0.3 in SFLequation are also ft/kt2

2.5 Climb

FAR 23Rate-of-Climb (RC) [MAXIMUMnotBest],

+

S

W

TO

kRCRCP

kRCp

P

W

TO

(2.16)

( )

=

lb

hp

,

minft/RCRCP

00033 (2.17)

define

=

CD

C/

L

max

kRC

23

19

(2.18)

eACD3CLomaxRC

= (2.19)

CDRC max= 4CDo (2.20)

In addition, for max RC, i.e.

( )

CDo

/

eA/

.

CD

C/

L

max

41

43

3451

23

. =

(2.21)


11/42

- 9 -

Climb Gradient (CGR

+

S

Wk

CC

CGR

C.

P

W

D

L

Lp

3

1

1

9718

(2.22)

WHERE W = k WTOso at take-off k = 1 and at landing select kL

Units for 18.97

hpftlb

2

2

for minimum CGR use CL=CLmax-0.2 or CL@ (CL/CD)max

FAR 25If propeller driven or turbo-prop, use FAR 23 CGR in equation 2.18 with appropriate

power, flap and gear settings. If the aircraft is multi-engine, then the power loading

for One Engine Inoperative (OEI) must be increased by multiplying as shown below.

( )

=

N

N

P

W

P

W

OEI

1

(2.23)

Jet aircraft, One Engine Inoperative (OEI)

+

=

CGR

D

L)N(

N

W

T 1

1 (2.24)

WHERE N = the number of engines

Jet aircraft, All Engines Operating (AEO)

CGR

D

LW

T+

=

1

(2.25)

AND T/W and L/D are for the flight conditions being analyzed! If landing then

substitute W = kL WTO for landing condition to calculate CL (and then CD from

appropriate drag polar) use

CV

VC L

S

TOmax

TO

specblimc

L 2

2

= (2.26)

Since

VCL 2

1

2.6 Time-to-climbFAR 25

+=

D

LV

RC

W

T o

TO

1

60

(2.27)

RCo inmin

ft , V insec

ft


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- 10 -

2.7 Cruise Speed,FAR 23,

Propeller Driven Aircraft

3

S

PIP

= (2.28)

IP

S

W

P

W3

=

(2.29)

Conversion from cruise to sea level take-off conditions

None turbocharged

TOPcr

TO S

W

k

ts

P

W

I

=

3

(2.30)

Wcr= kcr WTO and ts = throttle setting For turbocharger =1

= 77.3 (2.31)

= 0.8 0 .85For retractable gear, cantilever wing

VIP

=

34

2 (2.32)

For fixed gear, cantilever wing

VIP

=

31

2 (2.33)

For biplane, strutted monoplane, with fixed wing

VIP

=

3000

22 (2.34)

NOTEs (1) in Eqn (2.27-2.30) the velocity is mph!

In Eqn (2.27) the constant should be 77.35 and with units P (hp), W (lbs)

and S (ft2) the velocity, V, will be in (ft/sec).

FAR 25

+=

eAq

Dq

ts

S

Wk

S

W

C

W

TTO

cr

TO

TO

o

2

1

(2.35)

Again since Wcr= kcr WTO and assuming Tcr= ts TTO

cr

TO

TO

cr

crTO T

T

W

W

W

T

W

T

=

(2.36)

Units alert: q must have units of lb/ft2! (i.e. in slugs/ft3)For turbo-props use the (without turbo) Eqn (2.26) above.


13/42

- 11 -

Table 2.1 Typical Values for Maximum Lift Coefficients for Clean, Takeoff and

Landing

Airplane Type CLmax CLmaxTO CLmaxL

Homebuilt 1.2 - 1.8 1.2 - 1.8 1.2 - 2.0

Single Engine 1.3 - 1.9 1.3 - 1.9 1.6 - 2.3Twin Engine 1.2 - 1.8 1.4 - 2.0 1.6 - 2.5

Agricultural 1.3 - 1.9 1.3 - 1.9 1.3 - 1.9

Business Jets 1.4 - 1.8 1.6 - 2.2 1.6 - 2.6

Regional Turboprops 1.5 - 1.9 1.7 - 2.1 1.9 - 3.3

Transport Jets 1.2 - 1.8 1.6 - 2.2 1.8 - 2.8

Military Trainers 1.2 - 1.8 1.4 - 2.0 1.6 - 2.2

Fighters 1.2 - 1.8 1.4 - 2.0 1.6 - 2.6

Military Patrol, Bombers, and Transports 1.2 - 1.8 1.6 - 2.2 1.8 - 3.0

Flying Boats, Amphibious and FloatAirplanes 1.2 - 1.8 1.6 - 2.2 1.8 - 3.4

Supersonic Cruise 1.2 - 1.8 1.6 - 2.0 1.8 - 2.2

Table 2.2 Typical Values for Landing Weight to Take-Off Weight Ratio

Airplane Type WL/WTO

minimum Average Maximum

Homebuilt 0.96 1.0 1.0

Single Engine 0.95 0.997 1.0

Twin Engine 0.88 0.99 1.0Agricultural 0.7 0.94 1.0

Business Jets 0.69 0.88 0.96

Regional Turboprops 0.92 0.98 1.0

Transport Jets 0.65 0.84 1.0

Military Trainers 0.87 0.99 1.1

Fighters (Jets) 0.78 1.0

Fighters (TP's) 0.57 1.0

Military Patrol, Bombers, and Transports (Jets) 0.68 0.76 0.83

Military Patrol, Bombers, and Transports (TP's) 0.77 0.84 1.0

Flying Boats, Amphibious and Float Airplanes (Jets) 0.68 0.76 0.83Flying Boats, Amphibious and Float Airplanes (TP's) 0.77 0.84 1.0

Supersonic Cruise 0.63 0.75 0.88


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- 12 -

Requirements FAR 23 Types Normal Utility Aerobatics Commuter

Weight WTO< 12,500 Ibs WTO< 19,000 Ibs

No of pilots 1 pilot 2 pilots

Max No of passenger 10 11-21

Max altitude 25000ft

Requirement Configuration AEO

OEI

Altitude (ft) Climb

speedFlaps gear

Take-off

25.111 Take-off Retracted OEI (35-400) IGE 1.25VTO

25.121 Take-off Extended OEI ground effect VLFV2

25.121 Take-off Retracted OEI Out of ground effect V21.2VTO

25.121 Retracted Retracted OEI Take-off V2=1.25VS

La

nding 25.119 Landing Extended AEO 1.3VS

25121 Approach Extended OEI >1.1 VsL>1.5 VsA


15/42

- 13 -

ategory Requirement Weight

(Ibs)VSO(kt)

Configuration AEO

OEI

Altitude

(ft)C

Flaps gear

Normal

,

Utility,

Aerobatic[N-U-A]

Recip

Takeoff

23.65(a) 6 000 Take-off Retracted AEO S.L.

Recip &

Turbine

23.65(b) >6 000 Take-off Extendedretracted

6 000 Take-off Retracted OEI 400 V

23.67(b)(2) >6 000 Retracted Retracted OEI 1500

Commuter[C]

23.67(c)(1) Take-off Extended OEI Take-off V

23.67(c)(2) Take-off Retracted OEI 400 V

23.67(c)(3) Retracted Retracted OEI 1500

Landin

23.67(c)(4) Landing Retracted OEI 400

23.77(c) Landing Extended AEO [N-U-A] 23.77(a) 6 000 Landing

retracted6000 Landing Extended AEO


16/42

- 14 -

3 Drag Polar

3.1 The Rapid Drag Estimation Method (First Class)Drag Polar assumed to be parabolic, i.e., equation of the form

eACLCD

cleanoCDOEIFCD ++=

2

Where:OEI

F = Factor accounting for one engine Inoperative OEI

Propulsion FOEI

All-Engines-Operating 1.00

Fixed Pitch Propeller 1.25

Variable Pitch Propeller 1.10

Low Bypass Ratio Turbofan 1.15

High Bypass Ratio Turbofan 1.25

TOwet WdcS 1010 loglog += (3.1)

cd

TOwet WS 10= (3.2)

wetSbaf 1010 loglog += (3.3)

ab

wetSf 10= (3.4)

S

fC cleanD =0

(3.5)

CDCDCD clean += 00 (3.6)

Table 3.1 First Estimation for CDo and e with flaps and gear down

Configuration CD0 e

Clean 0 0.80 - 0.85

Take-off Flaps 0.010 - 0.020 0.75 - 0.80

Landing Flaps 0.055 - 0.075 0.70 - 0.75

Landing Gear 0.015 - 0.025 No Effect

Propeller Wind milling 0.015-0.018 No Effect

Table 3.2 Frist Estimation of Cf

Aircraft Type Cf

Bomber and civil Transport 0.003

Military cargo ( high wing) 0.0035

Fighter 0.0035


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- 15 -

Aircraft Type Cf

Navy Fighter 0.0040

Clean supersonic cruise 0.0025

Light aircraft single engine 0.0055

Light aircraft twin engine 0.0045

Prop seaplane 0.0065

Jet seaplane 0.0040

Table 3.3 Correlation coefficients for Parasite area versus wetted area

Cf A b

0.016 -1.7993 1.0

0.015 -1.8062 1.0

0.014 -1.8633 1.00.012 -1.9243 1.0

0.010 -1.9961 1.0

0.009 -2.0458 1.0

0.008 -2.0969 1.0

0.007 -2.1549 1.0

0.006 -2.2218 1.0

0.005 -2.3010 1.0

0.004 -2.3979 1.0

0.003 -2.5229 1.0

0.002 -2.6990 1.0

Table 3.4 Regression Line Coefficients for take-off Weight Versus Wetted Area

Airplane Type c d

Homebuilt 1.2362 0.4319

Single Engine 1.0892 0.5147

Twin Engine 0.8635 0.5632

Agricultural 1.0447 0.5326

Business Jets 0.2263 0.6977

Regional Turboprops -0.0866 0.8099

Transport Jets 0.0199 0.7531

Military Trainers 0.8565 0.5423

Fighters -0.1289 0.7506

Military Patrol, Bombers, and Transports 0.1628 0.7316

Flying Boats, Amphibious and Float Airplanes 0.6295 0.6708

Supersonic Cruise -1.1868 0.9609

* For these airplanes, wetted areas were correlated with "clean" maximum take-offweight. No stores were accounted for.


18/42

- 16 -

Drag due to Mach number

3.2 Component Drag Build up (second Class)Reynolds number

=

lURe (3.7)

Standard formulation to estimate Friction Coefficient

Complete laminar flow

e

fR

.C

lam

3281= (3.8)

Complete turbulent flow

( ) 58210

4550.

e

fRLog

.C

trb= (3.9)

Accounts for compressibility

( ) ( )

6502582

10 14401

4550..

e

f

M.RLog

.C

comptrb

+

=

(3.10)

Mixed laminar turbulent flow37506250

0 19636

.

e

.

tr

RC

X.

C

X

= (3.11)

80

0

201

0740.

tr

.

e

fC

XX

R

.C

mix

= (3.12)

Wing

0

0.001

0.002

0.003

0.004

0.005

0.4 0.45 0.5 0.55 0.6 0.65 0.7 0.75 0.8 0.85 0.9 0.95 1

Zero

LiftDragRise

Mach Number M


19/42

- 17 -

( ) ( ) Expowingwetww

Lswf

wo SCf

C

t

C

tL

S

RRCD

+

+=

4

1001 (3.13)

Horizontal Tail

( ) ( ) ExpotailHwetH

w

Ls

Ho SCf

C

t

C

tL

S

RCD

+

+=

4

1001 (3.14)

Vertical Tail

( ) ( ) ExpotailVwetV

w

Ls

Vo SCf

C

t

C

tL

S

RCD

+

+=

4

1001 (3.15)

L = 1.2 for maximum t/c located at x 0.3c

L = 2.0 for maximum t/c located at x < 0.3c

Fuselage

( ) bBfB CDCDCD +=o (3.16)

( )( )

( )S

S.CfRCD

fuswet

d

l

d

lfuswfBf f

f

f

f

+

+= 00250

601

3 (3.17)

Figure 3.1 Wing Fuselage Interference Correlation factor

0.8

0.85

0.9

0.95

1

1.05

1.1

1.0E+07 1.0E+08 1.0E+09 1.0E+10

Rwf

Fuselage Reynolds NumberRl Fus

M

0.25

0.4

0.6

0.7

0.8

0.85

0.9

0.25

0.4

M= 0.6 -0.9


20/42

- 18 -

Figure 3.2 Lifting surface correlation factor for wing subsonic

0.80

0.85

0.90

0.95

1.00

1.05

1.10

1.15

1.20

1.25

1.30

1.35

0.50 0.55 0.60 0.65 0.70 0.75 0.80 0.85 0.90 0.95 1.00

RLS

cos (tc)max

M=0.9

M=0.8

M0.25

M=0.6


21/42

- 19 -

( )

=

Bf

f

b

bCD

d

d.

CD

3

0290

(3.18)

( )Bff

flap AC

CCD

= (3.19)

Table 3.5Correlation Coefficients for flap Drag

Flap type A B

Split flap 0.0014 1.5

Plain flap 0.0016 1.5

Single slotted flap 0.00018 2

Double slotted flap 0.0011 1

Fowler 0.00015 1.5

Drag Due to Wind milling Propellers

S

DN.CD

propblades

prop

2001250= (3.20)

Drag Due to Turbojet Engine

S

S

U

VBPR

U

V

U

V

M.S

d.CD noz

bypass

noz

core

noz

core

nozinl

wm

+

++= 11

1601

207850

2

2

(3.22)

Table 3.6 Velocity Ratio

=

U

Vnoz

0.25 for turbojets (no bypass)

0.42 for low by-pass ratio jet engines (BPR < 2.0)

0.12 for the primary airflow of high by-pass jet engines (BPR > 2.0)

0.92 for the fan airflow of high by-pass jet engines (BPR > 2.0)

U

SHP

SqCDwm

33= (3.21)


22/42

- 20 -

Landing Gear Drag

Table 3.7 Drag of Tire Only

Tire Type Tire A Tire B Tire C Tire D

CDS 0.18 0.25 0.23 0.31-0.35

Referance Aera dw dw dw dw

Corresponds to Three Part

Type (GA)

Type III Type III high

floatation

tundra

Old fashioned

disc wheel type

S

w

tire CDS

wdCD

= (3.23)

( )Bff

flap AC

CCD

= (3.24)

Table 3.8 Drag of Tires with wheel Fairings

Fairing Type A1 A2 A3 B C

Tire Type TypeIII (B) TypeIII (B) TypeIII (B) TypeIII (B) TypeIII (B)

CDS (H W) 0.13 0.090 0.044 0.117 0.129

CDS (d w) 0.143 0.119 0.070 0.217 0.188

Sw

fairing CDS

WH

CD

= (3.25)

Table 3.9 Drag of fixed Landing Gear Struts with Tires

Type C B A

CDS See Table 1.112 1.204

Ref. Aera dw dw dw


23/42

- 21 -

Type D E FCDS See Table 1.125 See Table

Ref. Aera dw dw dw

Type I H G

CDS See Table 0.994 See TableRef. Aera dw dw dw

Type L K J

CDS 0.992 See Table See Table

Ref. Aera dw dw dw

Type O N M

CDS See Table 0.315 See Table

Ref. Aera dw dw dw

Type Q P

CDS 1.85 2.1 0.45-0.6

Ref. Aera dw dw


24/42

- 22 -

Table 3.10 Drag of Landing Gear Struts with and without Fairings

Strut Type Tire Type CDS

A 8.5-10 B 1.112

B 8.5-10 B 1.204

C1 8.5-10 + streamline wire B 1.151C2 8.5-10 + tubular support B 1.178

C3 27 inch streamline + tube A 1.082

C4 25x11-4 X-low press + tube C 0.940

C5 30x5 disk wheel hi-press + tube D1 1.779

C6 32x6 disk wheel hi-press + tube D2 1.373

D1 8.5-10 B 1.230

D2 8.5-10 B 1.191

E 8.5-10 B 1.125

F1 8.5-10 B 1.138

F2 8.5-10 + Fairing C B 0.877F3 27 inch streamline tube A 1.014

F4 25x11-4 X-low press + tube C 0.858

F5 30x5 disk wheel hi-press + tube D1 1.628

G1 8.5-10 B 1.151

G2 8.5-10+Fairing A2 B 0.733

H 8.5-10 B 0.994

I1 8.5-10 + Fairing B B 0.536

I2 8.5-10 + Fairing C B 0.484

I4 27 inch streamline + tube A 0.564

I5 27 inch streamline+ tube A 0.496J1 8.5-10 B 0.615

J2 8.5-10 + Fairing A1 B 0.458

J3 27 inch streamline A 0.485

K1 8.5-10 B 0.981

K2 8.5-10 + Fairing C B 0.641

L 8.5-10 B 0.992

M1 8.5-10 + Fairing A1 B 0.484

M2 8.5-10 + Fairing A1 + Expanding fillet B 0.315

N 8.5-10 B 0.315

Drag due to external fuel tanks

Figure 3.3 Drag due to external fuel tanks


25/42

- 23 -

Drag of Streamlined Struts and Landing Gear Pant Fairings

Figure 3.4 Geometric definition of small wing like surface and standard cross sections

Drag of Canopies

Figure 3.5 Canopy styles denoted by A through I

Figure 3.6 Drag of blunt and undercut cockpit windows

w

EBDSEB

S

SCDCD

= (3.26)

w

sfS

SS

ct

ctCCD

+

+=

2

12 (3.27)


26/42


27/42

- 25 -

Figure 3.10Two-dimensional drag coefficients of several cross-sections. Valid only

for 104< Re< 105.

Drag Due to Wing Washout

Ground Effectper IGE

Lift induced drag

Maximum lift to drag ratio

The span (Oswald) efficiency factor is found from

Method 1: Empirical Estimation

For straight wing

( ) 4604501781 680 .A..e . = (3.35)Swept Wing

( ) ( ) 1304501614 150680 .cosA..e .LE

. = (3.36)

Where LE> 30 oCorrection of aspect ratio due to winglets

+= b

h.

AAcorr

91

1 (3.37)

Method 2: USAF DATCOM

( )+

=

RAR

CLR

AR

CL.

e

1

11

(3.38)

=

LER

LER

U

R

l

(3.39)

( )wwashouti i.CD = 000040 (3.31)

( )

( )bh..

bh.

47051

32111

+

= (3.32)

( ) ( )OGEiIGEi

CDCD = (3.33)

( ) ( )

= OGE

IGE

DLDL (3.34)


28/42

- 26 -

LEcos

ARP

=1 (3.40)

LELELER cosMcotRP =22

2 1 (3.41)

If P21.3x105determine R from calculate from the following expression:

( ) ( )( )

++=

200950213018527284 1

2

210210

Psin.Plog.Plog..R (3.42)

If P2>1.3x105determine R from calculate from the following expression:

118

1

1

1011190860

PP..R

+

+= (3.43)


29/42

- 27 -

4 Miscellaneous

4.1 Conversion FactorsLength Mass

1ft 12 in 1 slug 14. 59kg

1 ft 0.3045 m 1kg (mass) 2.205 Ib (weight)

1 in 2.54 cm Pressure

1 m 3.28084 ft 1 Pa 0.00015 psi

1 mi (statute mile) 5280 ft 1 atm 101325 Pa

1 mi (statute mile) 1.609 km 1 atm 14.7 psi

1 mi (statute mile) 0.868976 nm Angle

1 nm (nautical mile) 6078 ft 1 rad 180/degSpeed Fuel specific weight

1 knot 1.689 ft/s Gasoline 44.9 Ib/ft3(0.72)

1 knot 1.151 mph JP1 49.7 Ib/ft3(0.80)

1 knot 1.852 km/hr JP3 48.2 Ib/ft3(0.775)

1mph 1.457 ft/s JP4 49.0 Ib/ft3(0.785)1mph 1.609 km/hr Kerosene 51.2 Ib/ft3(0.82)

1mph 0.8684 knot Temperature

Power R =1.8 K

1 BHP 33000 ft

Ib/min

R =F + 459.69

1 BHP 550 ft Ib /sec F =1.8 C + 32

1 BHP 745.7 W K =C + 273.16

4.2 Atmosphere propertiesThe standard atmosphere is mathematically defined in two layers from sea level to 20

kmh = altitude above sea level in feet or meters.

T0= Absolute temperature at sea level = 288.15 K = 518.67 R (or 15 C = 59 F)

0= Density of air at sea level= 1.225 kg/m3= 0.07648 lb/ft3= 0.0023769 slug/ft3P0= air pressure at sea level=1Atm=101325 N/m

2=2116.2 lb/ft2=14.696 lb/in2=29.921

in of Hg

a= Speed of Sound =340.3 m/s = 1116.4 ft/s

# Altitudes

up to

English Units

Temperature (R)

Density (slug/ft3)

Pressure (lb/ft2)

Metric Units

(K)

(kg/m3)

(N/m2)h is measured in: Feet meters

1 11 km T = T0(1 h / 145442 ft)

= 0(1 h / 145442 ft)4.255876P = P0(1 h / 145442 ft)

5.255876

T = T0(1 h / 44329 m)

= 0(1 h / 44329 m)4.255876P = P0(1 h / 44329 m)

5.255876

2 20 km T = T0(0.751865)

= 0(0.297076)e((36089-h)/20806)P = P0(0.223361)e

((36089-h)/20806)

T = T0(0.751865)

= 0(0.297076)e((10999-h)/6341.4) P = P0(0.223361)e

((10999-h)/6341.4)


30/42

- 28 -

Table 4.1 Atmosphere properties

Altitude

[ft]

Temperature

[Kelvin]

Pressure

[pascal]

Density

[slug/ft3]

Speed of sound

[ft/s]

Viscosity

[lb.sec/ft2]

0 288.150 101325 0.00237717 1116.45 3.78456x107

1000 286.169 97716.6 0.00230839 1112.61 3.76386 x107

2000 284.188 94212.9 0.00224114 1108.75 3.74310 x107

3000 282.206 90811.7 0.00217539 1104.88 3.72228 107

4000 280.225 87510.5 0.00211114 1100.99 3.70138107

5000 278.244 84307.3 0.00204834 1097.09 3.68041107

6000 276.263 81199.6 0.00198698 1093.18 3.65938107

7000 274.282 78185.4 0.00192704 1089.25 3.63828107

8000 272.300 75262.4 0.00186850 1085.31 3.61710107

9000 270.319 72428.5 0.00181132 1081.36 3.59586107

10000 268.338 69681.7 0.00175549 1077.39 3.57454107

11000 266.357 67019.8 0.00170099 1073.40 3.55316107

12000 264.376 64440.9 0.00164779 1069.40 3.53170107

13000 262.394 61942.9 0.00159588 1065.39 3.51016107

14000 260.413 59523.9 0.00154522 1061.36 3.48856107

15000 258.432 57182.0 0.00149581 1057.31 3.46688107

16000 256.451 54915.2 0.00144761 1053.25 3.44513107

17000 254.470 52721.8 0.00140061 1049.18 3.42330107

18000 252.488 50599.8 0.00135479 1045.08 3.40139107

19000 250.507 48547.6 0.00131012 1040.97 3.37941107

20000 248.526 46563.3 0.00126659 1036.85 3.35735107

21000 246.545 44645.1 0.00122417 1032.71 3.33522107

22000 244.564 42791.5 0.00118285 1028.55 3.31300107

23000 242.582 41000.7 0.00114260 1024.38 3.29071107

24000 240.601 39271.0 0.00110341 1020.19 3.26834107

25000 238.620 37600.9 0.00106526 1015.98 3.24588107

26000 236.639 35988.8 0.00102812 1011.75 3.22335107

27000 234.658 34433.1 0.000991984 1007.51 3.20074107

28000 232.676 32932.4 0.000956827 1003.24 3.17804107

29000 230.695 31485.0 0.000922631 998.963 3.15526107

30000 228.714 30089.6 0.000889378 994.664 3.13240107

31000 226.733 28744.7 0.000857050 990.347 3.10945107

32000 224.752 27448.9 0.000825628 986.010 3.08642107

33000 222.770 26200.8 0.000795096 981.655 3.06330107

34000 220.789 24999.0 0.000765434 977.280 3.04010107

35000 218.808 23842.3 0.000736627 972.885 3.01681107

36000 216.827 22729.3 0.000708657 968.471 2.99344107

37000 216.650 21662.7 0.000675954 968.076 2.99135107

38000 216.650 20646.2 0.000644234 968.076 2.99135107

39000 216.650 19677.3 0.000614002 968.076 2.99135107

40000 216.650 18753.9 0.000585189 968.076 2.99135107


31/42

- 29 -

4.3 The Geometric Properties of Aircraft

Geometry of Lifting Surface

Formulation for the Simple Trapezoidal Planform

Approximation of an Airfoil Cross-Sectional Area

( )

6

3 tCkAairfoil

+= (4.1)

Where: C = Airfoil chord, in ft or m

k = Location of the airfoils maximum thickness as a fraction of C.

t = Airfoil thickness, in ft or m.Approximation of an Airfoil Perimeter

( ) ( )22222

1444

kCtCkt

Sairfoil +++= (4.2)

Wing area

( )tr CCb

S +=2

(4.3)

Aspect ratio

C

b

S

bAR ==

2

(4.4)

Taper ratio

r

t

C

C= (4.5)

Mean Aerodnam!c "#ord (MA")

$#e MA" !s com%&ted 'rom

dyCS

MAC

b

=2

0

22 (4.6)

( )( )+

++=

1

1

3

22

rCMAC (4.7)

Y coordinates for straight tapered wing

( )+

+==

13

21

2

by (4.8)

Sweep Angle

( )

+

=

1

14mn

ARtantan mn (4.9)

Where nor mis sweep angle of the nthor mth constant fraction chord line.

+

+=

1

114

ARtantan /cLE (4.10)

+

+=

1

122

ARtantan /cLE (4.11)


32/42

- 30 -

( )( )2

22

1

1540

+

++= rFw c/t

b

S.V (4.12)

( )( )( )

+++=

112512 C

t

oexpwet.SS (4.13)

rfwexp CwSS = (4.14)

( )

( )t

r

ct

ct= (4.15)

Volume of pyramid

( )21213

SSSSl

Volume +++= (4.16)

Cg Location

Volume of obelisk

+++=

23

122121

babaSS

lVolume (4.18)

Wing wet area

Engine wet area

a1

b1

S2 a2

b2

ll

S2

S1

S1

( )

2121

2121 23

4

1

SSSS

SSSSl

cg++

++= (4.17)

( )( )

( )

+

++=

14

125012 C

t

oexpwet

.SS (4.19)


33/42

- 31 -

Wetted area of fan cowling

Wetted area of gas generator

Wetted area for plugs

Bodies of revolution for >4.5Volume

Wetted area for cylindrical mid-section:

Wetted area for streamlined fuselage without cylindrical mid-section

Dp

Deg

Dg

Def

Dh

Dn

ln

ln

lg

lp

Fan Cowling

Max. Diameter

Gas-generatorCowling

Plug

( )

++++=

n

ef

n

hnn

D

D

.D

D..Dl 1151803502 (4.20)

=

3

5

113

11

g

g

g

eg

ggl

D

D

DDl (4.21)

ppDl. = 70 (4.22)

( )

=

ff

ffDl

lD2

14

2 (4.23)

( ) ( )

+

= 2

32

2 1

1

2

1ffff

ffDlDllD (4.24)

( )( )( )

++=

51

322 3001511351050.

ff

ffffDl

..Dl..lD (4.25)


34/42

- 32 -

Wetted area of fuselage

Component Approximate Wetted Area

= 2.4 2.5

FUSF SD

=4

D/L=0.15to 0.25

= 2

= 2.4 !!

= 2.3 "" "# $!!

= 2.7 !!

= 2.85 "" "# $!!

+=

2

topside

wetF

AAS (4.26)

{ }

44 844 76876

4444444 84444444 76 ConeCylinder

Paraboloid

.

DL

DDL

DDDL

L

D

+

++

+

=

424844

12

22

32

2351

22

12

1

(4.27)


35/42

- 33 -

Passenger SeatingThe following tables show seating standards and baggage volume allowances

representing a typical airline 1-class high-density configuration. Typical 2-class

short-range seating rules are also included.

1-Class

High

Density

2-Class Short-RangeFirst

Class

(FC)

Economy

Class

(YC)

Seat Ratio Nominal % 100 8 Remainder

- Allowable % - 6-10 Remainder

Seat Pitch inch 28/29 36 32

Seat Depth inch 20 22 20

Minimum legroom for first row behind a wall inch 18 22 18

Minimum recline for last row in front of a wall inch 5 8 5

Seat Width Single inch 20 28.5 22- Double inch 40 57 42

- Triple inch 59 n/a 62

Maximum number of excuse-me seats to get

to an aisle- 2 1 2

Minimum Aisle Width inch 19 23 23

Passenger BaggageThe following tables show seating standards and baggage volume allowances

representing a typical airline 1-class high-density configuration. Typical 2-class

short-range seating rules are also included.

1-Class

High

Density

2-Class Short-Range

First

Class

(FC)

Economy

Class

(YC)

Carry-on baggage volume ft/pax5.5 (Note 1)

2 1.5

Checked-in baggage volume ft/pax 5 4

Notes:1) The 1-class high-density rules do not differentiate passenger baggage as carry-on or

checked-in. Instead, the specified total baggage volume must be provided as any

combination of carry-on and checked-in baggage.

CateringThe following table shows the rules used to determine the number of food trays

required.

1-Class

High

Density

2-Class Short-Range

First Class

(FC)

Economy

Class

(YC)

Trays per Passenger - 1.0 3.0 1.5


36/42

- 34 -

The following table shows the rules used to determine the number of trolleys required

along with key trolley/galley parameters.

Whole

trolley

Half

trolley

Galley

unit

Trays per Trolley - 28 14Trolley length inch 31.7 15.8

Trolley width inch 12.7 12.7

Overall galley depth, including rear structure inch 34 17.4

Galley end structure inch 1.35

Galley intermediate structure (3) inch 1.1

Minimum aisle width between galley units inch 26

Minimum space required in front of galley for

manoeuvring trolleys

inch 36 20

Notes:1) First class and economy class meals must be stored in separate trolleys.2) It is a requirement that no economy trolleys need to be moved through the first class

section during the flight. It is preferable that no first class trolleys need to be moved

through the economy section during the flight.

3) Galley units more than four trolleys wide require sub-dividing with a hard partition insuch a way that there are no more than three trolleys per compartment.

4) The following drawings show examples of full-, half- and mixed-trolley galleyarrangements.

34.0

15.4 28.1 40.8 53.5 67.3

17.4

15.4 28.1 40.8 53.5 67.3

53.5

34.0

28.1 29.5

14.1


37/42

- 35 -

LavatoriesThe following table shows the rules used to determine the number lavatories required.

1-Class

High

Density

2-Class Short-Range

First Class

(FC)

Economy

Class

(YC)

Passengers per Lavatory - 75 20 75

The following table shows some key lavatory parameters.

Lavatory

Cubicle

Minimum cubicle footprint inch 1650

Minimum cubicle dimension in length

or width

inch 29

Minimum aisle width between lavatory

cubicles

inch 26

Notes:

1) First- and economy passengers must be provided with separate lavatories.

2) First class lavatories must be directly accessible from the first class section.

Economy class lavatories must be directly accessible from the economy class section.

3) It is preferable that no passenger has a direct view into a lavatory when in their

seat.

The following drawings show examples of outer wall lavatories cubicles. Different

shape cubicles of equivalent area are permissible.

The following drawings show examples of centre cabin lavatories cubicles. Different

shape cubicles of equivalent area are permissible.

Inner WallOuter Wall

Floor Line

45.7

36.6

29

57

38

44


38/42

- 36 -

The following drawings show examples of centre cabin lavatory blocks.

AttendantsThe number of attendants is determined by the number required for passengers

services or by the manning of emergency exits (see Exits section), whichever is the

greater. The following table shows the required passenger servicing requirements:

1-Class

High

Density

2-Class Short-Range

First Class

(FC)

Economy

Class

(YC)

Passengers per Attendant - 50 16 50

The following drawings show standard attendant seat sizes, usually positioned near

exits.

The following drawings show minimum attendant to passenger spacing.

44 26

58

57

76

44

17.3

5

18.2

35

25.8

Wall Mounted:

17.3

8.4

22

35

25.8

Floor Mounted:

1

43.8

60

21.95

22

54.8

42.8

60

20.9

5

22

56.2

Floor Mounted Opposite Economy Seats:

8.4

Wall Mounted Opposite Economy Seats:

5


39/42

- 37 -

(attendant-passenger spacing, continued)

Cross-SectionThe following rules apply as minimum standards when determining the aircraft cross-

section:

1-Class

High

Density

2-Class Short-Range

First Class

(FC)

Economy

Class

(YC)

Minimum distance to sidewall for window seat

passenger

- at head (A) mm 60 100 60

- at shoulder (B) mm 30 60 30

- at armrest (C) mm 20 20 20

- at foot (D) mm 40 40 40

Minimum standing height mm

- in aisle mm 2100 2100 2100

- under side bins mm 1700 1700 1700

- under centre bins mm 1700 1700 1700

The following table lists the approximate anthropometric dimensionsfor the reference person seated naturally on a 400mm high seat.

2020 95%

US Male

Floor to top of head (E) mm 1380

Upper head radius (F) mm 80

Floor to shoulder (G) mm 1030

Width across shoulders (H) mm 530

Floor to elbow (armrest) (I) mm 590

Width across feet (J) mm 350

5

41.8

60

19.28 22

55.2

Wall Mounted Opposite Business Class Seats:

8.4

42.8

60

18.2

8

22

56.6

Floor Mounted Opposite Business Class Seats:

J

H

I

G

E

F

A

B

C

D


40/42

- 38 -

ExitsCS-25 (25.803 & Appendix. J) States that the aircraft must be capable of being

evacuated in 90 seconds using only half the side exits on the aircraft.

The following table lists key parameters for standard floor-level exit sizes.

Type

A

Type

B

Type

C

Type

I

Type

II

Passenger exit rating - 110 75 55 45 40

Number of attendants - 2 2 1 1 1

Clear opening height inch 72 72 48 48 44

Clear opening width inch 42 32 30 24 20

The following table lists key parameters for standard over wing exit sizes.

Type

II

Type

III

2x

Type

III

Type

IV

Passenger exit rating - 40 35 65 9

Number of attendants - 1 0 0 0

Clear opening height inch 44 36 - 36

Clear opening width inch 20 20 - 19

Maximum step-up from cabin

floor

inch 10 20 20 29

Maximum step-down onto wing inch 17 27 27 36

The following drawings show acceptable minimum assist space, passageway and

cross-aisle for Type A and B exits:

The following drawings show acceptable minimum assist space, passageway and

cross-aisle for Type C, I and II exits:

20

6036

Type A/B - Assist Space & Passageway

FloorLine

Overlapminimum 50%cross-aislewidth

20

Type A/B Cross-Aisle (End of Cabin)

Cross-aisle mustbe within 36passageway(100%overlap) 20

Type A/B Cross-Aisle (Mid-Cabin)

20

3220

Type C/I/II - Assist Space & Passageway

FloorLine

Type C/I/II Cross-Aisle

Minimum 1(5%cross-aisle width)

20

Passagewaymust be withindooropening(100% overlap)

Assist space can be forwardor aft of the passageway


41/42


42/42

(Adjacent Type III over wing exit options, continued)

Under floor Cargo

The following table lists commonly used under floor cargo containers.

Common name LD1 LD2 LD3 LD3-45W LD3-46

ULD convention name AKC APA AKE AKH AKG

Examples of current

aircraft applicability

- B747 B767 A330/340

A380

B777

A320 A320 (alsofits A330

etc.)

Container Type - Half width Half width Half width Full width Half width

Volume m 5.2 3.4 4.53 3.5 3.10

Tare Weight kg 70 60 70 82 No dataMax. Gross Weight kg 1588 1225 1588 1588 1588

The following drawings show simplified dimensions of these containers:

Double Type III Over wing (Option 3) - Passageway

Hatch widths= Door widths+ 2 per side(= 24)

20

Single Type III Over wing (Option 3) Cross-Aisle

Permissiblerange forcross-aisle

= No Recline

6

6

6

61.5

LD1 Container

60.4

64

92

47

LD2 Container

60.4

64

61.5

61.5

LD3 Container

60.4

64

79

45

61.5

LD3-46 Container

60.4

45

79

61.5

LD3-45W Container

60.4

96.2

design data sheet (10 2015)

Documents