Aircraft Design (Re-cap of Sessions till now)

Mohammad Fazlur Rahman Visiting Lecturer (AERO) Ganesh Institute of Engineering, Chennai –

• Design n Philosophy

• Designing is an art, depends upon the human psyche.

• Need and Scope of Designing

• Design Phases

• Conceptual, Preliminary n Detailed Design

• Pivotal Points for the Conceptual Design

• Air-loads in flight (Performance Loads)

• SSLF, Climbing, Gliding, Take-off, Landing.

• Accelerated Flights (Pull-up, Pull-down, Level Turn)

• Gust Load Factor, V-n diagram, Range & Endurance

• Air-loads in flight (Load Constaints)

• Take-off constraint

• Landing constraint

• Sustainable Turn Rate constraint

• Conceptual Designing…..1

• First Weight Estimation

• T/W ratio determination from historical data (Engine

Selection)

• Second Weight Estimation

• CLmax determination (Airfoil Selection)

• Lift augmentation (Flap Selection)

• Conceptual Designing….2

• Airfoil Selection from historical Data (CLmax Determination)

• Flap Selection (Lift Augmentation)

• Wing Loading Determination (W/S)

• Thrust to Weight Ratio Selection (T/W) from Airfoil information

• Take-off distance consideration

• ROC consideration

• Maximum Speed consideration

The parameters we have agreed on till now are as below.

Maximum lift coefficient 𝑪𝑳𝐦𝐚𝐱= 𝟐. 𝟑𝟒

Maximum lift-to-drag ratio 𝑳

𝑫 𝐦𝐚𝐱= 𝟏𝟔

Wing loading 𝑾

𝑺= 𝟓𝟏𝟔𝟐 𝐍 𝐦𝟐

Thrust Loading 𝑻

𝑾= 𝟎. 𝟑𝟏

These are the parameters which we have found in the process

Take-off gross weight 𝑾𝟎 = 𝟔𝟏𝟕. 𝟓 𝐤𝐍

Fuel Weight 𝑾𝒇 = 𝟗𝟐𝟔𝟐𝟓 𝐍

Fuel Tank Capacity 11.8 m3 (3117.86 gallons)

Wing area 𝑺 = 𝟏𝟐𝟎 𝐦𝟐

High Lift Devices Single-slotted trailing edge flap

Zero-lift drag coefficient 𝑪𝑫𝟎= 𝟎. 𝟎𝟐𝟑

Drag-due-to-lift coefficient 𝒌 = 𝟎. 𝟎𝟒𝟐𝟓

Aspect Ratio 𝑨𝑹 = 𝟏𝟐. 𝟓

Engine Thrust Two engines with 100 kN thrust each

Next Session

(Configuration Layout)