PRELIMINARY DESIGN REVIEW

Conceptual Design of a �Business Class Jet

Course: Aircraft Design & Optimisation

Prepared by: Group 3 (Business Jet)

DESIGN 1

Primary Mission Specs:

Core Weight Assumptions:

•

Passenger Capacity: 8 (Business Class)

•

Design Range: 3,000 km (≈ 1,620 nmi)

•

Cruise: Mach 0.75 @ 41,000 ft

•

Takeoff Field Length: ≈ 1,500 m

• Standard Pax/Crew: 90 kg

• Checked Baggage: 20 kg per pax

• ISA Atmospheric Conditions

MISSION REQUIREMENTS & ASSUMPTIONS

Dantu Phani Surya

Low Swept Wing

Optimized for structural efficiency, retractable landing gear housing, and fuel volume capacity.

Rear Turbofans

Rear-mounted twin engines ensure clean airflow over the wing and reduced interior cabin noise.

T-Tail Design

Keeps the horizontal stabilizer in clean airflow, free from wing wake and engine exhaust turbulence.

CONFIGURATION SELECTION LOGIC

Dantu Phani Surya

PAYLOAD WEIGHT CALCULATION

Dantu Phani Surya

Cumulative Mission Ratios:

• Start & Taxi: 0.990

• Cruise (3000 km): 0.6

• Reserve & Loiter: 0.970

MISSION FUEL FRACTION SUMMARY

0.44

Priyangshu Karmakar

0.41

W_e/W₀

Component Selection Logic:

•

High usage of composite airframe primary structures.

•

Pressurized cabin integration for high-altitude cruise.

•

Advanced executive avionics and interior outfitting.

•

Modern high-bypass turbofan nacelle weight.

EMPTY WEIGHT STATISTICAL SIZING

Priyangshu Karmakar

(Baseline for initial performance sizing and propulsion integration)

6000kg

Converged Maximum Takeoff Weight (MTOW)

TOTAL GROSS WEIGHT ESTIMATION

= 6000 kg

Priyangshu Karmakar

THRUST SIZING ANALYSIS

Constraint Diagram Analysis:

Target T/W = 0.30 to meet takeoff field length and climb gradient requirements.

Sizing Result: Twin turbofans @ 6.25 kN each.

N

Dheeraj

Wing loading (W/S) impacts takeoff speed, cruise efficiency, and stall safety margins.

WING LOADING COMPARATIVE STUDY

Dheeraj

Corrected Area (S): 12.0 m²

Aspect Ratio (AR): 8.5

Wing Sweep (\Lambda): 25°

INITIAL WING PLANFORM DESIGN

Dheeraj

3,000 km mission range supported by fuel fraction W_f/W_0 approx 0.44.

MISSION ALTITUDE PROFILE TREND

Abhishek Lakhera

CONCEPTUAL LAYOUT SKETCH

Preliminary 3-view blueprint

incorporating all major design choices:

•

Pressurized Cabin for 8 Pax.

•

Rear Mounted Twin Turbofans.

•

T-Tail Empennage Unit.

•

Retractable Tricycle Landing Gear.

Abhishek Lakhera

DESIGN 2

Primary Mission Specs:

Core Weight Assumptions:

•

Passenger Capacity: 18 (Business Class)

•

Design Range: 5677 km (≈ 3527 miles)

•

Cruise: Mach 0.75 @ 41,000 ft

•

Takeoff Field Length: ≈ 3500 m

• Standard Pax/Crew: 95 kg

• Checked Baggage: 20 kg per pax

MISSION REQUIREMENTS & ASSUMPTIONS - 2

Meet Raju Meshram

Wing position: Low

Low wing selected for structural efficiency, high fuel volume, shorter landing gear, and improved cruise aerodynamics (higher L/D).

Rear Turbofans

Rear-mounted turbofans selected for clean wing aerodynamics, lower cabin noise, and reduced wing structural penalties.

Cruciform Design

Cruciform tail chosen to keep the horizontal stabilizer in clean airflow, avoiding wing wake and engine exhaust effects.

CONFIGURATION SELECTION LOGIC

Meet Raju Meshram

PAYLOAD WEIGHT CALCULATION

Wpayload = 1710 + 180+ 360 = 2260 kg

Meet Raju Meshram

Cumulative Mission Ratios:

• Start & Taxi: 0.990

• Cruise (3000 km): 0.77

• Reserve & Loiter: 0.970

MISSION FUEL FRACTION SUMMARY

Fuel Fraction

​

0.28

​

Wf/Wo =1.06(1−0.99×0.77×0.97) = 0.28

Meet Raju Meshram

0.50

W_e/W₀

Component Selection Logic:

• Aluminum semi-monocoque structure for durability and certification reliability.
• Pressurized circular cabin enabling efficient high-altitude cruise.
• Rear-mounted medium-bypass turbofans for low cabin noise and clean wing aerodynamics.
• Integrated glass cockpit avionics optimized for single-pilot operations.�

EMPTY WEIGHT STATISTICAL SIZING

Jenish Patel

(Baseline for initial performance sizing and propulsion integration)

10701 kg

Converged Maximum Takeoff Weight (MTOW)

TOTAL GROSS WEIGHT ESTIMATION

Wo = 2250/(1-0.28-0.50) = 10701 kg

Jenish Patel

Corrected Area (S): 18.0 m²

Aspect Ratio (AR): 7.5

Wing Sweep (\Lambda): 27°

Airfoil: NACA 23014

INITIAL WING PLANFORM DESIGN

34.37

Jenish Patel

THRUST SIZING ANALYSIS

Constraint Diagram Analysis:

Target T/W = 0.25 to 0.45 required for Business jet to meet takeoff field length and climb gradient requirements.

Sizing Result: Twin turbofans @ 13.12 kN - 23.62 kN each.

T = 0.25 * 10701* 9.81 = 26244.2 N

T = 0.45 * 10701* 9.81 = 47239.6 N

Jenish Patel

DESIGN 3

GULFSTREAM G800

​

Overview of Design/Sizing Parameters

max

Sanjeev

Maximum lift to drag ratio trends

The maximum L/D ratio of our a/c is taken from this graph

max

cruise

Sanjeev

Aircraft Weights

Payload

Empty

Crew

Fuel

0

Key Definitions:

Weight Breakdown of Business Jet

Wpayload​: Represents the weight of passengers, baggage, and other cargo

Wcrew​: Accounts for the flight crew's weight

Wempty​: Covers the aircraft's structural weight without fuel, payload, or crew

Wfuel​: The calculated fuel weight required to

meet mission demands

W0​ (Initial Gross Weight): The total weight of the

aircraft at the beginning of the mission, including all components: empty weight, crew, payload, and fuel

Sanjeev

Calculated Wing Parameters

Wet

ref

ref

Wet

2

2

2

2

Sanjeev

Mission Segment Weight Fractions

Mission Profile

Breguet Range Equation

Nandini

Weight Fraction Calculations

Nandini

Gross Weights during different Missions

Nandini

Fuel Fraction during different Missions

*A fuel margin of 6 % is kept for emergency & reserve purposes

fx

0

Nandini

Conceptual Sketch

Top View of Aircraft

​

​

​

​

​

​

​

Front View of Aircraft

Sanjeev,Nandini

Conceptual Sketch

Side View of Aircraft

Sanjeev,Nandini

Conceptual Sketch

Isometric View of Aircraft

Sanjeev,Nandini

Conceptual Sketch

Front View of Cabin Cross-Section

Sanjeev,Nandini

DESIGN 4

Executive Summary

This jet is a modern business jet optimized for medium-range corporate missions, emphasizing fuel efficiency and passenger comfort.

DESIGN GOAL

To bridge the gap between light jets and intercontinental cruisers with a cost-effective platform.

Praveen Tiwari

Mission Requirements

SAFETY MARGIN

Reserve fuel calculated per standard ICAO/FAA regulations for commercial operations.

Takeoff

5 min max thrust� Climb to 41,000 ft

Cruise

4,500 km range� @ Mach 0.80

Reserves

30 min loiter� + 6% fuel reserve

Praveen Tiwari

Initial Weight Estimation

Gross Weight Calculation:

Empty Weight Fraction:

● Empty (59%) ● Fuel (28%) ● Payload (13%)

Empirical constants A=1.59, C=-0.10 for Jet Trainers/Business Jets.

Apoorva

Fuel Fraction Analysis

The cruise segment dominates fuel consumption. Calculated using the Breguet Range Equation:

Where R=Range, C=SFC, V=Velocity, L/D=Lift-to-Drag.

RESULT

Wf / W0 = 1 - 0.722 = 0.278 (approx 28%)

Apoorva

Aerodynamic Design

Wing Configuration

Equivalent Aspect Ratio:

Used to estimate L/D max of 15.

Sweep: 25° (Transonic efficiency)

Aspect Ratio: 6.6

Airfoil: Supercritical RAE 2822

JUSTIFICATION

Supercritical airfoils delay shockwave formation, allowing higher cruise speeds (Mach 0.80).

Ashmit

Schematic of Business Jet

Ashmit

Propulsion System

Type: 2x High-bypass Turbofan

Thrust: 32 kN each (64 kN Total)

SFC: 0.8 kg/(N·hr)

Mount: Rear Fuselage

INTEGRATION

Rear mounting allows for a clean wing aerodynamic surface and reduced cabin noise.

Ashmit

Engine Mounting

Ashmit

Performance Estimates

Thrust-to-Weight Ratio Calculation:

Speed

Cruise: Mach 0.80� Max: Mach 0.85

Runway

TO: 1,650 m� LND: 1,350 m

Climb

� Ceiling: 45,000 ft

G Aavishkar

Configuration

Fuselage: Circular cross-section (2.1m dia) for pressure efficiency.

Empennage: T-Tail to clear engine wake.

Landing Gear: Tricycle retractable.

FINENESS RATIO

Fuselage fineness ratio of 9.6 selected to minimize skin friction drag while ensuring adequate internal volume.

G Aavishkar

Fuselage Cross Section

G Aavishkar

Systems & Avionics

Key Systems

Avionics: Glass cockpit, Fly-by-wire.

ECS: 8,000 ft cabin alt @ FL450.

Power: 2x 28V DC Generators.

PASSENGER COMFORT

HEPA filtration and low cabin altitude reduce fatigue on long missions.

Apoorva

Conclusion

This jet design meets all preliminary performance targets.

Range: 4,500 km (Achieved)

Efficiency: L/D 15 (Verified)

Cost: Competitive DOC

RECOMMENDATION

Proceed to CFD analysis and scale model wind tunnel testing.

Apoorva

Q&A

Thank you for your attention.

Aircraft Design and Optimisation Lab, GROUP - 3 (Business Jet)

Preliminary Design Phase: COMPLETE

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Source: aircraftgeometrycodes.wordpress.com

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Source: eaglepubs.erau.edu

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Source: www.dassault-aviation.com

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