design of supersonic transport (a-sst)

8/6/2019 Design of Supersonic Transport (A-SST)

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Submit

Submit

Submis

ed to:

Mr.

ed by:

Ah

Aer

080

sion date:

July

her Afga

ad Ali A

-07

01028

14, 2011

Instit

nsari

te of S

pace T

echnol

gy


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I dedicate this report to my Parents who remain with me through

My thick and thin and always supported me.

And

To my friends who have been with me so long and changed my every

Distress into a smile


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1-Introduction: ................................................................................................................................ 8

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**1$#+,!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!0

2- Assessment of existing aircrafts ............................................................................................... 10

3- Design Procedure ...................................................................................................................... 12

.............................................................................................. 13

4-Sizing from a Conceptual Sketch: ............................................................................................. 13

)*23,!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!*

)424,!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!*

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)2,!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!*1

))25,!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!*6

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5-Airfoil and Geometry Selection:................................................................................................ 19

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16.,!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!0

1-2,!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!0

1,!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!


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1

6-Thrust-to-Weight Ratio and Wing Loading ............................................................................... 32

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7-Geometry Sizing ........................................................................................................................ 38

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62,!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!-

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13-Propulsion analysis .................................................................................................................. 74

14-Structural Analysis .................................................................................................................. 76*)*>?.,!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!6;

*)87,!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!6;

15-Performance and Flight Mechanics ......................................................................................... 79

*1*#+A,!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!60

*1./!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!-,!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!-*

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17-Cost Analysis ........................................................................................................................... 99

References: .................................................................................................................................. 101Appendix-I .................................................................................................................................. 102

Appendix-II ................................................................................................................................. 106

Appendix-III ............................................................................................................................... 107

Appendix-IV ............................................................................................................................... 110

Appendix-V................................................................................................................................. 114

Appendix-VI ............................................................................................................................... 116


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Aircraft wetted area (Swet), the total exposed surface area, can be visualized the area of the external partsof the aircraft that would get wet if it were dipped into water. The wetted area must be calculated for drag

estimation, as it is the major contributor to friction drag.

Since thickness to chord (t/c) ratio of is less than 0.05, therefore following assumption can be adopted to

calculate wetted area of wing or tail.

X ! ?MXS'Component

l{vln

l ssMl{vln

Wing 6535.072 13089.749

Canard 450.106 901.562

Vertical Tail 872.676 1747.97

Table 12.1 Summary of Exposed Area Values of A-SST

For the estimation of fuselage wetted area, following formula can be used,

X ? ;M 'L! Following values have been estimated from drawing

'L !$$>[email protected],

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The necessary calculation for estimating the above values is given as,


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design of supersonic transport (a-sst)

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