JAWAHARLAL NEHRU TECHNOLOGICAL UNIVERSITY HYDERABAD

Pre-Requisites:

• Low Speed Aerodynamics & High-speed Aerodynamics

Course Objectives:

• Understand the basic skills involved in weight estimation for aircraft conceptual design process.
• Illustrate relevant theoretical knowledge, applicable for initial sizing and configuration layout of aircraft.
• Evaluate basic techniques in literature retrieval and query, also creative and have systematic scientific research methods and working abilities

Course Outcomes:

• Design of aircraft for various application, Effort estimation, Development life cycle

UNIT - I

Overview of The Design Process: Phases of aircraft design, aircraft conceptual design process, project brief / request for proposal, problem definition, information retrieval, integrated product development and aircraft design. initial conceptual sketches, takeoff gross weight estimation, airfoil selection, airfoil design, airfoil design considerations, wing geometry and wing vertical location, wing tip shapes, tail geometry and arrangements, thrust to weight ratio, thrust matching, wing loading performance, constraint analysis.

UNIT - II

Initial Sizing and Configuration Layout: Sizing with fixed engine and with rubber engine. geometry sizing of fuselage, wing, tail, control surfaces, development of configuration lay out from conceptual sketch. the inboard profile drawing, lofting- definition, significance and methods, flat wrap lofting, special consideration in configuration lay out, Isobar tailoring, Sears-Haack volume distribution, structural load paths, radar, IR, visual detectability, aural signature, considerations of vulnerability, crashworthiness, producibility, maintainability, fuselage design, crew station, passengers and payload

UNIT - III

Propulsion, Fuel System Integration, Landing Gear and Baseline Design Analysis – I: Propulsion selection, jet engine integration, propeller engine integration, engine design considerations, engine size estimation, fuel system design and integration, landing gear and sub systems arrangements, guidelines and significance of design layout, report of initial specifications. Estimation of lift curve slope, maximum lift coefficient, complete drag build up, installed performance of an engine, installed thrust methodology, net propulsive force, part power operation, aircraft structures and loads categories, air load distribution on lifting surfaces, review of methods of structural analysis, material selection, weights and moments statistical group estimation method, centre of gravity excursion control.

UNIT - IV

Baseline Design Analysis – II: Estimation of static pitch stability, velocity stability and trim, estimation of stability and control derivatives, static lateral, directional stability and trim. estimation of aircraft dynamical characteristics, handling qualities, Cooper – Harper scale, relation to aircraft dynamic characteristics, performance analysis and constraint analysis– steady level flight, minimum thrust required for level flight, range and loiter endurance, steady climbing and descending flight, best angle and rate of climb, time to climb and fuel to climb, level turning flight, gliding flight, energy maneuverability

R18 B.TECH AERONAUTICAL ENGG. III YEAR

methods of optimal climb trajectories and turns, the aircraft operating envelope, take off analysis, balanced field length, landing analysis, fighter performance measures of merit, effects of wind on aircraft performance, initial technical report of baseline design analysis and evaluation, refined baseline design and report of specifications.

UNIT - V

Cost Estimation, Parametric Analysis, Optimisation, Refined Sizing and Trade Studies: Elements of life cycle cost, cost estimating method, RDT&E and production costs, operation and maintenance costs, cost measures of merit, aircraft and airline economics, DOC and IOC, airline revenue, breakeven analysis, investment cost analysis, parametric analysis and optimization, improved conceptual sizing methods, sizing matrix plot and carpet plot, trade studies, design trades, requirement trades, growth sensitivities, multivariable design optimization methods, measures of merit, determination of final baseline design configuration, preparation of type specification report. case studies on design of DC-3 and Boeing B-707&747; General dynamics F-16, SR-71 Blackbird, Northrop-Grumman B-2 Stealth Bomber

TEXT BOOKS:

• 1. Daniel P. Raymer, ―Aircraft Design: A Conceptual Approachǁ, AIAA Educational Series, USA, 4th edition, 2006.
• 2. J. F. Marchman, L. R. Jenkinson, ―Aircraft Design Projects for Engineering studentsǁ, AIAA Publishers, USA, 2003.
• 3. Ajoy Kumar Kunda, ―Aircraft Designǁ, Cambridge University Press, UK, 2010.

REFERENCE BOOKS:

• 1. E. Torenbeek, ―Synthesis of Subsonic Airplane Designǁ, Delft University Press, New York, 1986.
• 2. E. H Bruhn, ―Analysis and Design of Flight Vehicles Structuresǁ, Jacobs Publishing House, USA, New Edition, 1973.
• 3. E. E Scheler, L.G Dunn, ―Airplane Structural Analysis and Designǁ, John Wiley & Sons, USA, 1963.
• 4. D. Howe, ―Aircraft conceptual Design Synthesisǁ, John Wiley and Sons Publishers, USA, 2005. R18 B.TECH AERONAUTICAL ENGG. III YEAR