Design of an Advanced Turboprop Aircraft for Regional Operations with Ninety Passengers

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DesignofanAdvancedTurbopropAircraftforRegionalOperationswithNinetyPassengers

CONFERENCEPAPER·JANUARY2013

DOI:10.2514/6.2013-24

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3AUTHORS,INCLUDING:

HernánDarioCerón-Muñoz

UniversityofSãoPaulo,EESC,Brazil

17PUBLICATIONS8CITATIONS

SEEPROFILE

Availablefrom:HernánDarioCerón-Muñoz

Retrievedon:28September2015

Design of an Advanced Turboprop Aircraft for

Regional Operations with Ninety Passengers

A. Felipe Giraldo1, Julio E. Parra2, Roy S. Soler3, and Maycol F. Escorcia4

Fundación Universitaria Los Libertadores, Research Group in Aerospace Sciences - GICA, Bogotá, Colombia.

Julian D. Martínez5

Fundación Universitaria Los Libertadores, AERODES&I, Bogotá, Colombia.

Guido A. Fuentes6

PRISM, Denver, Colorado, 80111

and

Hernán. D. Cerón7

São Carlos Engineering School, University of São Paulo-Brazil

The main propose in this paper is a conceptual design of a turbo-prop aircraft, with capable of

carrying ninety passengers on regional flights, following the methodological procedures proposed

by Jan Roskam, in response to the lack an aircraft to bring together those characteristics for the

civilian market, trade, acquiring support argumentative statement on research developed from the

acquisition of information available, and assessment of current conditions of technical operation of

aircraft in force in the international market , to regional transportation services. Therefore it came

to a proposed aircraft called "stylized" in conventional design parameters and make questions

about the efficiency and optimization of the same.

NOMENCLATURA

AAA = Soft ware Advantage Aircraft Analysis

AR = Aspect ratio A, B = Regression line constants

CDo = Parasite Drag Coefficient

Cl max cl = Maximum Clean Lift Coefficient

Cl max to = Maximum Take off Lift Coefficient

Cl max ld = Maximum Landing Lift Coefficient

Cp = Specific fuel consumption

ESFC = Specific fuel consumption

ESPH = Equivalent shaft HP

f = Equivalent Parasite

FAR 25 = Federal aviation regulation; Airworthiness standards: Transport category airplanes

ṁf = Fuel Mass Flow mf = Fuel Weight

Pto = Take off power Shaft

RPM = Revolutions per minute

S = Wing Area

STOFL = Take off field length

Swet = Wetted Area

1Aeronauticalengineer– Universityof San Buenaventura. GICA Researcher (GICA- for its acronym in SpanishGrupo de

Investigación en Ciencias Aeroespaciales). [email protected] 2Master Student in Mechanical Engineering/ National University of Colombia, Aeronautical Engineer.Director of

[email protected]. 3Aeronautical engineer - Fundacion Universitaria Los Libertadores . Junior ResearcherGICA. [email protected]

4Aeronautical engineer – FundaciónUniversitaria Los Libertadores.ResearcherAsistentGICA,[email protected],

5Aeronautical engineer student /FundaciónUniversitaria Los [email protected].

6Director System Safety, Professional Resources in System Management LLC, 6021 South Syracuse Way, Suite 303, Greenwood

Village, CO 80111, Senior Member. [email protected] 7Phd AerodynamicLaboratory/ São Carlos Engineering School, University of São Paulo-Brazil. [email protected]

T = Time

Tto = Take off Thrust

TOP 25 = Take off parameter for Far 25

(W/P) To = Take off power loading

(W/S) To = Take off wing loading

(T/W) To = Take off thrust to weight ratio

X = Rango

Λ = Tapper ratio

λ = Lamda cuartos

σ = Air Density Ratio

I. Introduction

For the development about this paper was made a preview researching about regional aviation where

the relevant aspect were the impact, development and growth. With the results collected was found the

necessity of using turboprop aircraft for mission and increase the operations frequency in the airline

around the world, therefore is necessary designing and building an aircraft with the performance proposed

here.

The researching methodology is divided in five stages. The first is about information acquisition, the

second is a selection of relevant information, the third is an analysis between statistics and mathematic

models (using the design concept given by Dr. Jan Roskam), the fourth part is about the conceptual

design process supported with AAA software which includes all design procedures Dr. Jan Roskam in his

books (Airplane Design) and the last stage is consolidated the general model, where is used a feedback about the information compiled for getting an aircraft preliminary design see Fig. 1.

Figure 1. Stylized concept.

II. Methodology

At the stage of acquisition of information, type information was gathered historical, economic,

commercial and industrial turboprop aircraft that operated or operate in the regional aviation market

worldwide, as shown in Appendix A, This is established of draft form and has the convenience of the

development of our project, the existence of fifty-four (54) different aircraft model, serial and generation, fifteen (15) manufacturers of different nations, as shown in Table 1. Where the information available in

open consultation and discreet group allowed this number of aircraft in an initial data base, later in the

development of the next stage would be subject to selection analysis and data evaluation, assessment

under specific parameters referred the benefit of the project.

Table 1. Manufacturers, models and series, Preliminary Data Base turboprop aircraft

in the past and present transportation or service to passengers on regional flights

After preliminary form the basis of data available to begin the discrimination stage information, which

determined the specific parameters of analysis and data selection, taking into account the objective, the

characteristics of the project and the benefit of the modeling process statistical - mathematical for

development. The data parameters selections were:

Year of manufacture of the aircraft.

The market aircraft operation time.

The market aircraft prevalent.

Aircraft technology.

Number of passengers carrier.

The parameters described in the base allowed the identification of preliminary data, eleven (11)

aircraft that made up the characteristics defined by these, these aircraft are highlighted in Table 1

and are these aircraft which in the next stage are subject to identification, analysis, evaluation

and comparison of their technical aspects, commercial and design. The eleven (11) aircraft that

make up the database of study are: ATR 42-500, ATR 72-500, Bombardier Q400NG , Dornier

Do 328TP, Let Kunovice L 410 UVP-E20 / L 420, Ilyushin IL -114 -300, Avic International

MA60, SAAB 340Bplus With WT, SAAB 2000, Fokker 50, British Aerospaces Bae Jetstream

41. The technical, commercial and design information of these aircrafts is high reliability

because was subtracted for the principal manufactures Table 2.

Technical Aspects Commercial Aspects Design Characteristics Other Aspects

MTOW Crew Overall Length Engine

MLW Passengers Overall Height Manufacturer

MZFW Cargo Per Pass Wing Span Dry Weight Engine

OEW Take-Off Field Length Wing Area Power

MPL Landing Field Length Operating Altitude Take-Off Power

MFL Range

Mcs

Table 2. Relevant aspects. Technical, commercial and design features.

By obtaining a database, started the stage of comparative analysis for statistical modeling -

mathematical. Importantly, the procedures involved in this stage is drawn from the conceptual design process of aircraft developed by Dr. Jan Roskam Fig. 2, which is described in each of the parts of his

work called Airplane design.

MANUFACTURER MODEL AND SERIES

ATR 42 -200 42-300 42-320 42-400 42-500 Series

600 ATR 72-100 72-200 72-210 72-500 Series 600

BOMBARDIER DASH 8Q-100 DASH 8Q-200 DASH 8Q-300 Q-400

FAIRCHILD DORNIER Do328-100 Do328-110 Do328-120 Do328-130 Do328 TP

EMBRAER EMB 110 EMB 120

FOKKER F27-100 F27-200 F27-300 F27-400 F27-500 F27-600

FOKKER FOKKER 50

ANTONOV An -24 An-140

BRITISH AEROSPACE Bae Jetstream 41

Bae ATP

ILYUSHIN IL-114 IL-114-100 IL-114-120 IL-114-300

SAAB Saab 340A Saab 340B Saab 340Bplus Saab 340B

plus WT

Saab 2000

BEECHCRAFT Beechcraft 1900

LET KUNOVICE L 410 UVP-E20/L 420

XIAN AIRCRAFT IND. Xian MA60 Xian MA600

NIHON AIRCRAFT . NAMC YS-11

CESSNA C. CARAVAN

FAIRCHILD

SWEARINGEN.

METRO METRO II METRO IVA METRO III METRO

IVC

METRO

23

Figure 2. Description of the conceptual design of an aircraft.

Process developed by Dr. Jan Roskam, subtracted image of his

work Design Airplane Part 1: Preliminary sizing of airplane

III. Preliminary Sizing

With the information collected, was elaborated Dispersion graphics with known variables. See fig 2,

this variables have a specific correlation that was used for behavior identification about every variable in

a reference plane aircraft´s; this is represented in the graphics by a tendency line used for lineal regression

required in the design.

The main features about Stylized are shown in the Table 3. The aspects stabilized are: Autonomy,

Passenger and Crew to transport and the specific weight for this. Weight that was determined used the

average weight about every passenger and their baggage.

Features

Passengers 90 per RANGE 2000 Km / 1080 NM

Flight Crew 2 per Weight Per Passenger 102 kg./ 225 lb.

Cabin Crew 3 per Weight Per Baggage 15.8 kg / 35 lb.

Payload

Weight Total Crew 510 kg / 1125 lb.

Weight Total Passengers 9180 kg / 20250 lb.

Table 3. Inicial Features about Stylized. This represented the inicial

value for the turboprop aircraft

A. Graphics

Using the general features for the Stylized, was accomplished an dispersion diagram and lineal

regression analysis for the base looking for a variance “R2” nearly one, this is necessary to keep design

parameters. Now is shown the dispersion graphics with the equation and a preliminary estimated result.

Figure 3. Regression and results Maximum Load Vs

Fuel Range.

Figure 4. Regression and results Maximum Payload

Vs Take Off Power

Figure 5. Regression and results Maximum Fuel load

Vs Maximum payload

Figure 6. Regression and results Maximum Take Off

Weight Vs Take Off Power

IV. Stylized Conceptual Design Using with Software AAA

Stylized is designed with Roskam’s methodology supported by software AAA (Advantage Aircraft Analysis) which give a clear idea of the features that must have an aircraft to supply the need of carrying

more people at the regional level.

A. Mission

The mission include 1 warmup, 2 taxi, 3 take off, 4 climb, 5 cruise, 6 descent, 7 landing y 8 taxi

Fig.7 Stylized has a range 2000 Km and account with a maximum ceiling of 7620 m -2500 Feet.

Polynomial Eq. = y = 0,0203x2 - 68,776x + 59571

kg Fuel Load 3219 0,0203 -68,776 59571

km Range 2000 81200 -137552 59571

Polynomial Eq. = y = -0,0003x2 + 3,4073x - 958,66

Kg Payload 9180 -0,0003 3,4073 -958,66

SHP Power 5038,634 -25281,72 31279,014 -958,66

Polynomial Eq. = y = -0,0008x2 + 10,443x - 1844,2

Kg MTOW 30463,99 -0,0008 10,443 -1844,2

SHP Power 5038,634 -20310,27 52618,46 -1844,2

Polynomial Eq. = y = -6E-05x2 + 1,1974x - 530,91

kg Payload 9180 -6,00E-05 1,1974 -530,91

kg Fuel Load. 5,40E+03 -5,06E+03 10992,132 -530,91

Figure 7. Mission Profile

B. Weight

Specifying weights are 102 kg per person (86.2 kg and 15.8 kg per person per bag) for a total payload

of 9180 kg, has 5 crew (two pilots and three cabin) with a weight of 510 kg. seen en Table 3.

The empty weight estimation is performed a regression with Basic line aircraft that currently has the

best performance in terms of passengers and range Fig. 8.

The fuel fractions managed to find the value of fuel weight in the mission given are taken from (Ref

48).

Figure 8. Regression Trend Aircrafts Stylized Basic Line

The point of the iteration results in Fig. 9 respond to the following estimate of Empty Weight

192841.48 N equivalent to 19657.64 Kg and Take off about 341 156, 03 N equivalent to 34776.35 Kg.

Figure 9. Iteration by Software AAA to find Takeoff Weight and Empty Weight of Stylized

Is important to take the best engine turbo prop built as a reference for regional aviation by features,

thrust and performance is considered manufactured PW 150A Pratt & Whitney Canada that is

incorporated in Bombardier Q 400, reaching speeds of mach 0.592 is the fastest aircraft in aviation

regional their characteristics are ESHP = 6200; SHP = 5071, Max RPM = 1020 (Ref 45).

An ideal Cp is shown in Eqs (1) (2) (3) advised by [Mechanical Engineer Francisco Gonzalez Cruz]

and estimated using Q400 aircraft parameters table 6 And PA 150A engine (Ref 45). These equations will

result in fuel consumption cruiser. See table 4.

(1)

1162.2 kg/h =2562.2 Lb/h (2)

ESFC= = 0.4132 = Cp PW 150A (3)

The Cp value continues to decline since it was took the maximum speed of the airplane Q 400, the

specific fuel consumption is extremely important to determine the weight of the aircraft fuel. The obtained value is included in a stage of cruising weight fraction and thereby reduces the weight of

fuel calculated through regression.

Mission Profile Begin

Weight

Fuel Used

Weight

Begin Fuel

Weight

1 Warmup 341156,0 3411,6 53085,9

2 Taxi 337744,5 1688,7 49674,3

3 Take-off 336055,8 1680,3 47985,6

4 Climb 334375,5 5015,6 46305,3

5 Cruise 329359,8 38387,2 41289,7

6 Descent 290972,6 1454,9 2902,5

7 Land/Taxi 289517,8 1447,6 1447,6

Table 4. Fuel Consumption at each Stage of the Mission

C. Sensitivity Analysis

This sensitivity analysis is done with Dr. Jan Roskam methods in (Ref 49). This section discloses the

following information:

1) For each unit increase in payload or crew the take off weight should increase in 4 units

2) For each unit increase in the empty weight the take off weight should increase in 1.7 units

3) For each increase or decrease in range (km) the take off will increase or decrease the of take off

weight in 8 units

D. Wing Area

The wing area of Stylized is found with the equation in the graphics Fig.10 where is shown Wing

loading Vs Maximum Takeoff Weight with Stylized Basic line. Resulting the equation S = 67,005. This procedure gives rise to perform geometry wing with values taken from Stylized Basic Line and

determining (GIGA Research Group).

1) AR=12.5

2) λ= 0.45

3) λ = 0

Figure 10. Graphic Trend with Airplane of Stylize Base Line, Maximum Take off Vs Wing

loading

E. Maximum Lift Coefficient.

Is necessary to know the aerodynamic profile for determinate coefficients, investigating the profiles

for turbo-prop aircraft to meet lifting ranges, is decided to employ the NACA 43018 Fig. 11. This is used

by aircraft ATR 72 but modified (Ref 44).

ATR 42

ATR 72

Q 400

Do 328

SAAB 200

Bae Jetstream 41

L 410UVP

y = 0,0099x + 175,24

0

100

200

300

400

500

0 10.000 20.000 30.000 40.000

(W/S

)

MTOW

Series1

Figure 11 Graph Lift Coefficient NACA 43018

Lift coefficient Cl Max cl.=1.9 is given by the profile NACA 43018 with angle of incidence = 3 to Cl

max to: 2.1 is provided in (Ref 10) and Cl max landing: 2.9 we obtain for Single Slotted Flap ( Ref 47)

F. Take off power Loading The value for take off power loading is obtained through the performance equation of Fig. 12 for a

distance STOFL = 1524 m -5000 ft considered Stylized Basic Line, wing loading (W / S) To = 106.33

PSF and σ = 1, resulting in a value of (T / W) to = 0379.

Figure 12 Airplane Design Part 1 Preliminary Sizing of Airplane Peg 98

With the value of (T / W) to identify the pounds force that requires for Stylized take off Tto = 29125.65 Lb and through Appendix B Table 31 we find the equivalent Pto= 1000-1050 Horse Power.

Fig. 13 gives a clear idea what is best for Cl max To for power required in take off.

Figure 13. Effect of Take off Wing Loading and Maximum Take off Lift Coefficient

On Take off Thrust to Weigh Ratio

G. Geometry

Its geometric configuration very similar to the turbo-prop aircraft constructed as reference of higher

rank Q 400, ATR 72/42, this Airplanes are the most influential in its geometric configuration, for

reducing material weight is maximizing the cabin space.

-1

0

1

2

3

4

5

-5 0 5 10 15 20

Lif

t C

eo

fici

en

t

Angle of attack

CL

CL =1,5

CL=1,8

CL=2,1

CL=2,4

0,000

0,200

0,400

0,600

0,800

1,000

1,200

0,0 50,0 100,0 150,0 200,0 250,0

(T/W

)To

(W/S)To - PSF

Using AAA software to find the best geometric configuration of the Stylized aircraft, Following

steps that recommended Dr. Jan Roskam in Airplane Design (Part II: Preliminary Setting of the Design

and Propulsion System Integration) result in Figs. (14, 15, 16, 17, 18, 19, 20).

Figure 14. Wing Geometry

Figure 15. Aileron Position and size

Figure 16 Horizontal Tail Geometry Figure.17. Elevator Size

Figure 18. Vertical Tail Geometry Figure 19. Rudder Size

Figure 20 Fuselage Geometry

H. Weight and balance

Stylized has a similar configuration of the aircraft components Fokker F 27 100/200/500 And

DeHaviland Canada 7-102 that Dr. Jan Roskam provides the weight fractions of component that using

these aircraft Table 5. The Software AAA performs an average of these weight fractions and adds to

Stylized.

Table 5. Statistic Data of Aircraft Weight Fractions into AAA Software

Determining the position of Stylized components, finding volume and gravity center of each component made through solid 3D Fig. 1 values are found Table 6. Datum line is three meters from nose.

Component Weight N Xcg mm Zcg mm

Crew 5003,1 8902 2505

Trapped Fuel and Oil 170,6 18440 4045

Mission Fuel Group 1 53085,9 18440 4045

Passenger Group 1 76090,0 16505 2505

Baggage 13965,0 25500 2505

Fuselage Group 36068,4 17000 2555

Wing Group 36404,8 18440 4045

Empennage Group 8743,9 31560 6485

Landing Gear Group 14629,2 16096 1200

Nacelle Group 7482,7 17087 3399

Power plant Group 37497,7 17087 3399

Fixed Equipment Group 52014,8 16500 2555

Table 6. Stylized Component Weights and its Respective Center of Gravity

Table 6 reveals to us that the empty weight center of gravity is at 22.8% of the mean aerodynamic

chord of the wing and the center of gravity of Stylized take off weight is located 23.6% of the mean

aerodynamic chord.

I. Drag Coefficients

Estimation of parasite drag at low speeds by methodology Dr. Jan Roskam in (Ref 51) where CDo = and where f = 29.65 found through the Appendix B - table 32 with an estimated Swet =688,75

S= 721.2 , CDo is equal to 0.041. Taking values ΔCDo for flap and landing gear extended Table 7. Values are plotted the drag coefficients

in the AAA software Figs. (21, 22, 23).

Table 7. Airplane Design Part 1 Preliminary Sizing of Airplane page (127)

Figure 21. All polar

Figure 22. Graphic Drag Coeficiente with Flap and Gear Up

Figure 23. Graphic Drag Coeficiente with Flap and Gear Down

J. Lift Distribution

The profile used to tip is 43012 and 43018 for root; type of flap to use is Single Slotted Flap and

deflection ith 35 to get the wing lift distribution fig. 24.

Figure 24. Lift Distribution in the Wing Span

The selected profile is 43018 throws lift coefficients that fall in the range of turbo prop aircraft.

Established by intensive and extensive clean lift, with flap down the lift coefficient Increasing to

proportions given for regional turbo prop aircraft in (Ref 50) see figure 25.

Figure 25. Graphic Lift Coefficients with Effect Flap Down

V. Stylized Configuration The streamlined configuration is characterized by the dimensioning of its major components.

According to the characteristics of the Stylized (Figs .20, 21, 22, 23, 24, 25, 26) your body should be able

to accommodate 90 passengers in the other areas that it therefore requires a predetermining factor for

sizing the passenger is aware of the Dimensions and volumes required for carrying luggage, chairs, doors,

corridors, bathrooms, kitchens and loading zone, influencing do directly in transverse and longitudinal

section as shown in Fig. 26 and 27 respectively.

Figure 26. Cross section, the Stylized passengers cabin

Figure 27. longitudinal section, the Stylized passengers cabin

This concept considered a high-wing aircraft, streamlined fuselage, allowing an efficient

aerodynamics designed to keep down the specific fuel consumption; given the configuration of five seats

online is possible to keep the landing gear in it.

This paper shows the first stage of design in a conceptual framework. This has followed, progress has been made seeking to define the materials and manufacturing methods specified in order to reduce weight

and improve the performance thereof. A proposed distribution of materials is shown in Fig 28

Figure 28. Stylized Concept.

Based on the dimensioning made from the linear regressions and the estimated geometry in AAA

software, has come to propose an aircraft as shown in Fig. 29, 30, 31 also is described more clearly in

Appendix C.

Figure 29. Stylized concept.

Figure 30. Stylized Concept

.

Appendix

Appendix A: Technical database for the dispersion of baseline

Appendix B: Graphical de Airplane Design

Appendix C: Attachments to document pdf.

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Ottawa, Kansas 1985pp 12, (Table 2.1). 49Jan Roskam ,Airplane Design Part 1 Preliminary Sizing of Airplane, Roskam Aviation and Engineering

Corporation, Ottawa, Kansas 1985, pp. 68-79 50Jan Roskam , Airplane Design Part 1 Preliminary Sizing of Airplane, Aviation and Engineering Corporation,

Ottawa, Kansas 1985 pp. 91. Table 3.1 51Jan Roskam , Airplane Design Part I Preliminary Sizing of Airplane, Aviation and Engineering Corporation,

Ottawa, Kansas 1985 pp. 118-127.

Appendix A

TECHNICAL DATABASE FOR THE DISPERSION OF BASELINE

Abbreviation

MCS = Maximum Cruise Speed

MFL = Maximum Fuel Load

MPL = Maximum Payload

MLW =Maximum Landing Weight

MTOW = Maximum Take-Off Weight

MZFW = Maximum Zero Fuel Weight

OEW = Operative Empty Weight

Table 7. Aspects Technical of the Aircrafts Elected to the Database

Table 8. Aspects Commercial of the aircrafts chosen for the database

kg lb kg lb kg lb kg lb kg lb kg lb

15480.85 lb15.900 35.053 lb 6.500 14.330 7022

2.580 5.690 lb

12.120

12.177 4.030 8.884 lb

7.500

4.250 9.370 lb

12.520

6.622

44.090 lb 14.500 31.970 lb 5.50020.000

27.602 lb

14.600 lb

18.900

9.707

44.160 lb 20.03045.900 lb 20.820

10.886 24.000 lb 10.569 21.400 lb23.300 lbBae JETSTREAM 41

SAAB 2000

FOKKER 50

26.500 lb 8.62028.500 lb

23.000 50.700 lb 22.000 48.500 lb

19.20047.620 lb21.60048.028 lb21.800

340Bplus With WT 13.155 29.000 lb 12.925

L 410 UVP-E20 / L 420

IL -114 -300

MA60

30.843 lb 13.230 29.167 lb 12.61013.990

23.500 51.808 lb 23.500

6.06014.109 lb6.40014.550 lb6.600 3.968 1403

4.890 10.781 lb27.800 lb 9.100

3093,0813.360 lb 4.150 9.150 lb 1.800

4.710 lb

Do 328 Turbo-prop

58.000 lb 17.819 39.284 lb 8.489 18.716 2.13629.574 65.200 lb 28.123

20.062 lb 3.510 7.738

62.000 lb

5.450

49.604 22.350 49.272 20.500

Q400 26.308

22.500

40.344 lb

ATR 72 -500

MLW

18.300

MTOW

ATR 42-500

MODEL & SERIAL

9.920 lb36.817 lb 11.250

MZFW OEW MPL

24.802 lb 12.015 4.50016.700

MFL

28.550 7.550 16.645 5.000 11.02345.194 12.950

5.50030.204lb13.70042.291 lb

874 US gal27776.8003.084

9.090 lb 4.12013.2286.000

12.020 19.000 lb 3.400

41.665 lb

51809 lb

41.005lb 18.600

kg lbCREW PASSENGERS

2 50.

2 74

3 80

3 34

214

209

209

97

95

95

100

85

97

187

214

102

95

102

102

2 19

2 52.

2 56

ATR ATR 42-500

MANUFACTURER MODEL & SERIAL

BOMBARDIER Q400

ATR ATR 72 -500

DORNIER Do 328 Turbo-prop

LET AIRCRAFT INDUSTRIES L 410 UVP-E20 / L 420

ILYUSHIN IL -114 -300

AVIC INTERNATIONAL MA60

SAAB 340Bplus With WT

SAAB

FOKKER

BRITISH AEROSPACES Bae JETSTREAM 41

SAAB 2000

FOKKER 50 602 58

3 30

52

58

33

362 34

2 50

CREW + PASSENGERS

52

76

83

37

21

54

CARGO per PAX

225

209

225

225

220,46

Table 9. Design Features and Commercial Aspects of the Aircrafts selected for the database.

Table 10. Design features of the aircrafts chosen for the database.

Table 11. Characteristics of the aircrafts engines chosen for the database

KM NM Meters feets Km/h knots Meters feets Meters feets

RANGE

8401556

7551.400

1.1342.100

1649

1.878

1.352

ATR ATR 42-500

MANUFACTURER MODEL & SERIAL

890

BOMBARDIER Q400 1.014

ATR ATR 72 -500

DORNIER Do 328 Turbo-prop 731

LET AIRCRAFT INDUSTRIES L 410 UVP-E20 / L 420

ILYUSHIN IL -114 -300

AVIC INTERNATIONAL MA60 1.600 863

435805SAAB 340Bplus With WT

925

774

SAAB

FOKKER

BRITISH AEROSPACES Bae JETSTREAM 41

SAAB 2000

FOKKER 50 1.106

1713

2055

1433

OPERATING ALTITUDE

7.000 21.000 ft

7.000 21.000 ft

7.620 25.000 ft

7.620 21000 ft

6.100 20.000 ft

7.600 24.934 ft

7.620 25.000 ft

7.620 25.000 ft

9.450 31.000 ft

7620 25.000 ft

7925 26.000 ft

MCS

560 300 kt

512 276 kt

667 360 kt

620 334.5 kt

386 208 kt

500 270 kt

514 280 kt

524 283 kt

685 370 kt

526 284,02 kt

546 294,82 kt

TAKE OFF FIELD LENGTH

1.165 3.822 ft

1.290 4,232 ft

1.468 4.819 ft

1.088 3.570 ft

565 1.854 ft

750 2.460 ft

1.100 3.600 ft

1.125 3.685 ft

1.220

503 1.650 ft

550 1.804 ft

1.460 4.790 ft

1.395 4.580 ft

1.525 5.005 ft

LANDING FIELD LENGTH

1.126 3.694 ft

1.067 3.500 ft

1.290 4.232 ft

1.075 3.525 ft

1120 3674,54 ft

1290 4232 ft

4.005 ft

1050 3450 ft

1433 4701 ft

Meter Inchsv&ft Meter Inch or feet Meter Inch or feet m2 ft2

7095,15 ft29

SAAB

FOKKER

BRITISH AEROSPACES

27,28 ft

Bae JETSTREAM 41 19,3 63,2 ft 5,7 18,8 ft

SAAB 2000 27,28 89 ft 6 in 7,73 25 ft 4 in

FOKKER 50 25,25 82,83 ft 8,32

600 sq. Ft24,76

32,4

754 sq. Ft

81 ft 3 in 55,7

348 sq. Ft18,4 60,4 ft

SAAB 340Bplus With WT 19,73 64 ft 9 in 6,97 22 ft 11 in 22,75 74 ft 8 in 41,8 450 sq. ft

81 ft 0.6 in 8,853 29 ft 0.5 in 29,2 95 ft 9.3 in 74,98

ILYUSHIN IL -114 -300 26,87 88,17 ft 9,32 30,59 ft 30

807,08 sq.ftAVIC INTERNATIONAL MA60 24,71

LET AIRCRAFT INDUSTRIES L 410 UVP-E20 / L 420 14,42 47,30 ft 5,83 19,10 ft 19,98 65,55 ft 35.18 378 sq .ft

430,5 sq .ft

98,42 ft 81,9 881,56 sq. ft

DORNIER Do 328 Turbo-prop 21,11 69,26 ft 7,24 23,75 ft 20,98 68,83 ft 40

656,6 sq .ft

BOMBARDIER Q400 32,8 107 ft 9 in 8,4 27 ft 5 in 28,4 93 ft 3 in 64 689 sq . ft

ATR ATR 72 -500 27,166 89 ft 2 in 7,56 25 ft 1 in 27,05 88 ft 9 in 61

OVERALL LENGHT OVERALL HEIGHT WING SPAN WING AREA

80 ft 7 in 54,5 586 sq. ftATR ATR 42-500 22,67 74 ft 5 in 7,59 24 ft 11 in 24,57

MANUFACTURER MODEL & SERIAL

TAKE OFF POWER

DATA OPERATOR SHP kg lb

DRY WEIGHT ENGINE

480.8

480.8

689.9

415.49

178.72

530

480

807

1060

1060

1521

916

394

1168.45

1060

1779.13

751

3000

2160

2475

5071

2180

751

2500

POWER

DATA MANUFACTURER SHP

2400

2750

5071

2180

ATR ATR 42-500

MANUFACTURER MODEL & SERIAL

BOMBARDIER Q400

ATR ATR 72 -500

DORNIER Do 328 Turbo-prop

LET AIRCRAFT INDUSTRIES L 410 UVP-E20 / L 420

ILYUSHIN IL -114 -300

AVIC INTERNATIONAL MA60

SAAB 340Bplus With WT

SAAB

FOKKER

BRITISH AEROSPACES Bae JETSTREAM 41

SAAB 2000

FOKKER 50

PW-127J

1500

Pratt & Whitney Canada

Honeywell 1650

1060

1395.53

480.8

633

MANUFACTURER ENGINE

Pratt & Whitney Canada

Pratt & Whitney Canada

Pratt & Whitney Canada

Pratt & Whitney Canada

Walter Aircraft Engines

Klimov

Pratt & Whitney Canada

ENGINE

MODEL

PW127E

PW127F

PW150A

PW119B/C

M 601-E

TV7 - 117SM

2475

1870

4152Rolls - Royce

General Electric

2750

1870

4152

GE CT7-9B

Allison AE2100A

PW127B

TPE331-14GR/HR

730 1610

27502750

Appendix B

GRAPHICAL DE AIRPLANE DESIGN

Figure 31. Graphical Airplane Design Part 1 Preliminary Sizing of Airplane Peg (100).

Figure 32. Graphical Airplane Design Part 1 Preliminary Sizing of Airplane peg (120).