Sizing of Wing Flaps and Control Surfaces Sept 2010 Released

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INDIAN AIRCRAFT DESIGN BUREAUBangalore, India

Technical Report

Issue/Revision :1.0 Document Type: Internal Page 1 / 1112 July 2010

Technical Report_Template_V1This document is the property of IADB. This should not be reproduced or communicated without written authorization

Document No. JTA-125/AERO 003

Title : Sizing of wing planform, high lift devices, empennage andcontrol surfaces

SUMMARYThe aim of this technical report is:

To estimate the wing planform design parameters

To size the high lift devices or flaps based on the design requirement (Ref 1)

To estimate the size of the empennage, control surfaces and their disposition

Co-ordination Group Name Signature and Date

Prepared ByConfigurationAerodynamics

A. ARUN KUMAR

Released on 04thSept 2010

ALVIN ANTHONY

N. BASKARAN

D. MUKUNDAN

Checked By Propulsion R. THAARIQ AHMAD

Approved By Project Management P. S. PREMKUMAR

Coordinated By

Released ByConfigurationAerodynamics


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CONFIGURATION AERODYNAMICS GROUP

Sizing of wing planform, high lift devices, empennage and control surfacesTechnical Report

JTA-125/AERO 003Issue/Revision :1.0

Page 2 / 1112 July 2010

Technical Report_Template_V1

CLASSIFIEDThis document is the property of IADB. This should not be reproduced or communicated without written authorization

DOCUMENT CHANGE RECORD

Issue /Revision

Date Reason for change Change description

1.0 First Issue

INTERNAL DISTRIBUTION

Name Department Number of copiesP. S. Prem Kumar Project Management 1.0

EXTERNAL DISTRIBUTION

Name Company / Department Number of copies


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TABLE OF CONTENTS1. INTRODUCTION ..................................................................................................................................... 52. AIRCRAFT CONFIGURATION TYPE..................................................................................................... 53. WING PLANFORM GEOMETRY AND LATERAL CONTROL SURFACES SIZING ............................. 54. HIGH LIFT DEVICES SIZING ................................................................................................................. 6

4.1 Determination of Clean Airplane CLmax

............................................................................................... 64.2 Sizing of high lift devices .................................................................................................................... 7

5. EMPENNAGE AND CONTROL SURFACE SIZING AND DISPOSITION.............................................. 96. CONCLUSION ...................................................................................................................................... 11

LIST OF FIGURES

Figure 1 Definition of flapped wing area .................................................................................................. 8Figure 2 Wing planform ........................................................................................................................... 9Figure 3 Horizontal tail geometry ........................................................................................................... 10Figure 4 Vertical tail geometry ............................................................................................................... 10

LIST OF TABLES

Table 1 Wing geometric data ................................................................................................................... 5Table 2 Lateral control surface geometry ................................................................................................ 6Table 3 Design point requirements (Ref 1) .............................................................................................. 6Table 4 Wing airfoil parameters (based on the airfoil lift coefficients) ..................................................... 7Table 5 Required maximum lift coefficients to be produced by the high lift devices ............................... 7Table 6 Required sectional lift coefficient to be generated by the flaps .................................................. 8Table 7 Empennage design parameters ............................................................................................... 11


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REFERENCES

S.No Reference Version Title

1. JTA-125/AERO 002 2.0 (JUNE 2010)Design point estimation fromSizing parameters

2. 125A 00 00001 00 000 1.0Three view and generalarrangement

3. Aircraft Design Vol. 2Preliminary configuration designand the integration of propulsionsystem

4.

5.

TERMS & ABBREVIATIONS

A/C Aircraft

cf/c Flap chord to wing chord ratio

f Flap deflection

HT, H.T. Horizontal tail

I/B Inboard

O/B Outboard

S Wing area

Swf Flapped wing area

VT, V.T. Vertical tail


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1. INTRODUCTION

This report provides the preliminary estimation of the wing planform design, flap size,

empennage and control surface size and disposition. The wing planform is designed based

on the data available for the similar class of aircraft. The flap is sized based on the design

requirement from Ref 1.

The empennage and control surfaces and their respective locations are too sized based on

the data available for the similar class of aircraft.

2. AIRCRAFT CONFIGURATION TYPE

The configuration of JTA-125

Low wing

Low horizontal tail

Engine installed in nacelles under the wing

Wing mounted spoilers

Landing gear retraction into wing/fuselage intersection

Tricycle landing gear layout (nose type)

3. WING PLANFORM GEOMETRY AND LATERAL CONTROLSURFACES SIZING

The wing geometric data is arrived based on the data available for the similar class of

aircraft. Table 1 shows the planform design characteristics of the wing. The wing area (S)

and the Aspect ratio (AR) are 123 m2 and 9.5 respectively (Ref 1). The wing is cantilever type

with the overall wing/fuselage arrangement as the low wing type.

Table 1 Wing geometric data


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The wing incidence angle and the twist angle are not specified in Table 1 and these design

parameters can be estimated at later phase of design based on the requirement.

Table 2 shows the typical inboard, outboard aileron and spoiler dimensions. For more detail

see Ref 2.

Table 2 Lateral control surface geometry4. HIGH LIFT DEVICES SIZING

The type and the size of high lift devices needed for the airplane is found by its capability to

meet the requirements for CLmaxTO and for CLmaxL. The first step is to find whether or not the

selected wing geometry parameters are consistent with the required value of clean CLmax.

Table 3 shows the design point requirements obtained based on the landing and takeoff field

length requirements (Ref 1).

Table 3 Design point requirements (Ref 1)

4.1 Determination of Clean Airplane CLmax

Table 4 shows the available wing lift parameters especially the CLmaxW (clean maximum lift

coefficient available from the wing).

From Table 3 and Table 4 it is concluded that the clean required maximum lift coefficient is

7% higher than the available lift coefficient from the wing. According to Ref 3, if the wing

planform cannot meet the required value of clean maximum lift coefficient within 5% then it is

necessary to redesign the wing planform and/or to select different airfoil until it does. For the

time being it is assumed that the wing planform remains the same as mentioned in Table 1

until a correct type of airfoil is chosen for JTA-125.


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Note: Hence a detailed study on the airfoil type has to be done to obtain a realistic value of

airfoil sectional lift coefficient. Since the values of airfoil sectional lift coefficient at root and tip

1.9 and 1.7 (Ref 3) seem too high (Table 4).

Table 4 Wing airfoil parameters (based on the airfoil lift coefficients)

4.2 Sizing of high lift devices

Based on the assumption in 4.1, the high lift devices are sized based on the same wing

planform geometric data (Table 1). For this class of aircraft fowler flaps can be used as a

trailing edge high lift device. Table 5 shows the incremental values of maximum lift

coefficients for takeoff and landing need to be produced by the high lift devices.

Table 5 Required maximum lift coefficients to be produced by the high lift devices

Based on the required incremental values of maximum lift coefficients, it is possible to

compute the required incremental section maximum lift coefficients (ClmaxTO_reqd &

ClmaxL_reqd) using the factor K and Swf/S (ratio of flapped wing area to the total wing area,

see Figure 1). The required value of incremental section lift coefficient Cl_TO_reqd and

Cl_L_reqd is computed using a factor K which is related to the flap type, flap chord ratio (where

K = 0.94, for fowler flaps with cf/c = 0.3). Table 6 shows the values of required incremental

section lift coefficient which the flaps must generate based on the design requirement for

various values of Swf/S. Based on the high lift requirements FOWLER FLAPS are chosen as


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the primary high lift device. The available incremental section lift coefficient from the fowler

flaps are (cf/c = 0.3):

For take-off (f = 25 deg) : 1.86

For landing (f = 40 deg) : 2.46

The above available lift coefficient are independent of Swf/S. For Swf/S = 0.9 the available

section lift coefficient by the fowler flaps is 12% higher than the required section lift coefficient

based on the design requirement (landing). There is sufficient lift available for takeoff as

compared to the required value.

Figure 2 shows the overall wing geometry.

Figure 1 Definition of flapped wing area

Table 6 Required sectional lift coefficient to be generated by the flaps


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Figure 2 Wing planform

5. EMPENNAGE AND CONTROL SURFACE SIZING AND DISPOSITION

Table 7 shows the empennage design parameters. The airplane configuration is conventional

(tail aft arrangement). Horizontal and vertical tail volume coefficient is 1.14 and 0.077

respectively. The tail volume coefficients are the average of coefficients for aircrafts similar to

JTA-125 (Ref 3). Figure 3 and 4 show the H.T. and V.T. geometry.


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Figure 3 Horizontal tail geometry

Figure 4 Vertical tail geometry


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Table 7 Empennage design parameters

6. CONCLUSION

The available incremental section lift coefficient from the fowler flaps is 12% higher than the

required section lift coefficient for Swf/S = 0.9 (landing). To conclude a detailed study on the

wing airfoil is required in order to achieve realistic values of lift coefficients for this aircraft.

Initial 2-D studies on the sectional lift and drag coefficients to be carried on the airfoils

available for aircrafts similar to JTA-125.

Documents

Sizing of Wing Flaps and Control Surfaces Sept 2010 Released