sizing of wing flaps and control surfaces sept 2010 released
TRANSCRIPT
-
7/31/2019 Sizing of Wing Flaps and Control Surfaces Sept 2010 Released
1/11
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
-
7/31/2019 Sizing of Wing Flaps and Control Surfaces Sept 2010 Released
2/11
CLASSIFIED
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
-
7/31/2019 Sizing of Wing Flaps and Control Surfaces Sept 2010 Released
3/11
CLASSIFIED
CONFIGURATION AERODYNAMICS GROUP
Sizing of wing planform, high lift devices, empennage and control surfacesTechnical Report
JTA-125/AERO 003Issue/Revision :1.0
Page 3 / 1112 July 2010
Technical Report_Template_V1
CLASSIFIEDThis document is the property of IADB. This should not be reproduced or communicated without written authorization
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
-
7/31/2019 Sizing of Wing Flaps and Control Surfaces Sept 2010 Released
4/11
CLASSIFIED
CONFIGURATION AERODYNAMICS GROUP
Sizing of wing planform, high lift devices, empennage and control surfacesTechnical Report
JTA-125/AERO 003Issue/Revision :1.0
Page 4 / 1112 July 2010
Technical Report_Template_V1
CLASSIFIEDThis document is the property of IADB. This should not be reproduced or communicated without written authorization
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
-
7/31/2019 Sizing of Wing Flaps and Control Surfaces Sept 2010 Released
5/11
CLASSIFIED
CONFIGURATION AERODYNAMICS GROUP
Sizing of wing planform, high lift devices, empennage and control surfacesTechnical Report
JTA-125/AERO 003Issue/Revision :1.0
Page 5 / 1112 July 2010
Technical Report_Template_V1
CLASSIFIEDThis document is the property of IADB. This should not be reproduced or communicated without written authorization
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
-
7/31/2019 Sizing of Wing Flaps and Control Surfaces Sept 2010 Released
6/11
CLASSIFIED
CONFIGURATION AERODYNAMICS GROUP
Sizing of wing planform, high lift devices, empennage and control surfacesTechnical Report
JTA-125/AERO 003Issue/Revision :1.0
Page 6 / 1112 July 2010
Technical Report_Template_V1
CLASSIFIEDThis document is the property of IADB. This should not be reproduced or communicated without written authorization
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.
-
7/31/2019 Sizing of Wing Flaps and Control Surfaces Sept 2010 Released
7/11
CLASSIFIED
CONFIGURATION AERODYNAMICS GROUP
Sizing of wing planform, high lift devices, empennage and control surfacesTechnical Report
JTA-125/AERO 003Issue/Revision :1.0
Page 7 / 1112 July 2010
Technical Report_Template_V1
CLASSIFIEDThis document is the property of IADB. This should not be reproduced or communicated without written authorization
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
-
7/31/2019 Sizing of Wing Flaps and Control Surfaces Sept 2010 Released
8/11
CLASSIFIED
CONFIGURATION AERODYNAMICS GROUP
Sizing of wing planform, high lift devices, empennage and control surfacesTechnical Report
JTA-125/AERO 003Issue/Revision :1.0
Page 8 / 1112 July 2010
Technical Report_Template_V1
CLASSIFIEDThis document is the property of IADB. This should not be reproduced or communicated without written authorization
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
-
7/31/2019 Sizing of Wing Flaps and Control Surfaces Sept 2010 Released
9/11
CLASSIFIED
CONFIGURATION AERODYNAMICS GROUP
Sizing of wing planform, high lift devices, empennage and control surfacesTechnical Report
JTA-125/AERO 003Issue/Revision :1.0
Page 9 / 1112 July 2010
Technical Report_Template_V1
CLASSIFIEDThis document is the property of IADB. This should not be reproduced or communicated without written authorization
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.
-
7/31/2019 Sizing of Wing Flaps and Control Surfaces Sept 2010 Released
10/11
CLASSIFIED
CONFIGURATION AERODYNAMICS GROUP
Sizing of wing planform, high lift devices, empennage and control surfacesTechnical Report
JTA-125/AERO 003Issue/Revision :1.0
Page 10 / 1112 July 2010
Technical Report_Template_V1
CLASSIFIEDThis document is the property of IADB. This should not be reproduced or communicated without written authorization
Figure 3 Horizontal tail geometry
Figure 4 Vertical tail geometry
-
7/31/2019 Sizing of Wing Flaps and Control Surfaces Sept 2010 Released
11/11
CLASSIFIED
CONFIGURATION AERODYNAMICS GROUP
Sizing of wing planform, high lift devices, empennage and control surfacesTechnical Report
JTA-125/AERO 003Issue/Revision :1.0
Page 11 / 1112 July 2010
Technical Report_Template_V1
CLASSIFIED
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.