Comprehensive Wing Design Analysis
Bombardier Challenger 650 Business Jet
Aircraft Classification: Business Jet
Scope: Wing Design, Engine Installation, Aerodynamics, Performance
Executive Summary & Aircraft Overview
Twin-engine business jet representing state-of-the-art corporate aviation.
Supercritical wing design optimized for transonic cruise at Mach 0.80.
Max Altitude: 41,000 ft | Cruise: 37,000 ft
Max Speed: Mach 0.85 | Cruise Speed: Mach 0.80
Range: 4,000 nautical miles (NBAA 4-Pax IFR)
Propulsion: 2 × GE CF34-3B Turbofans (41 kN each)
Devanshi
Primary Wing Design Parameters
Parameter | Value |
Wing Reference Area (S) | 45.4 m² (489 ft²) |
Wingspan (b) | 19.61 m (64 ft 4 in) |
Aspect Ratio (A) | 8.46 |
Root Chord (C_root) | 3.706 m (12.16 ft) |
Tip Chord (C_tip) | 0.927 m (3.04 ft) |
Mean Aero Chord (MAC) | 2.595 m (8.51 ft) |
Taper Ratio (λ) | 0.25 |
Wingspan Calculation:
MAC Derivation:
Abhishek
Advanced Wing Configuration
Sweep Analysis
Λ_1/4: 28° | LE: 32° | TE: 18°
A quarter-chord sweep of 28 degrees.
Reduces transonic drag, Enhances lateral stability and critical Mach number.
Taper Justification
Ratio (λ): 0.25
Optimizes lift distribution. Reduced induced drag by 1.3%. Improved stall and weight efficiency.
Supercritical Airfoil
Type: Modified NACA | t/c: 11%
Rounded LE, inverted camber, blunt TE.
M_crit ≈ 0.795 at cruise.
Ganjare Aavishkar (22AE30010)
Three-Dimensional Wing Optimization
Dihedral (5.5°) & Twist (-3.5°)
Roll Stability: Lateral stability via positive roll restoring moment.
Dutch Roll Damping: Improved coordination.
Washout (-3.5°): Root section stalls at 16°, while tip remains at 12.5°.
Aileron Authority: Tips stall AFTER root, preserving control at high AOA.
Apoorva
Aircraft Weight Distribution
Category: Midsize-to-Heavy
CG Range: 25%-35% MAC
Ensures stability, good climb, and short-field capability.
Dheeraj (22AE30009)
Operating Empty Weight (OEW) - 12315kg
Bombardier Challenger 650
Fuel - 9000kg
Maximum Take Off Weight (MTOW) - 21315kg
Interference Drag Analysis
Engine Nacelle Design & Interference Drag
Total Wetted Area: 34.98 m² (Nacelle + Pylon)
Interference Factor: 0.35 | Cf: 0.00269
Contribution represents ~2.4% of zero-lift drag. Smooth blending minimizes separation zones.
Phani Surya (22AE30006)
Component | Dimension | Unit |
Nacelle Diameter | 1.50 | m |
Nacelle Length | 3.20 | m |
Inner Diameter(Max) | 1.52 | m |
Inner Duct Length | 0.65 | m |
Zero-Lift Drag Coefficient Breakdown
TOTAL CD₀: 0.02683 | CD_i: 0.01083 | CD_total: 0.03766
Lift-to-Drag Ratio (L/D): 12.75 at Cruise (CL=0.48)
Phani Surya (22AE30006)
High-Altitude Cruise Flow Characteristics
1.54 × 10⁷
Reynolds Number (Re)
Fully Turbulent Boundary Layer
Condition (37,000 ft/11,277.6 m) | Value |
True Airspeed (V) | 235.7 m/s |
Air Density (ρ) | 0.369 kg/m³ |
Dynamic Pressure (q) | 10.25 kPa |
C_f (Turbulent) | 0.00269 |
Kumar Ashmit Ranjan (22AE30016)
Raked Winglet Configuration & Benefits
Span Efficiency
A_eff: 8.76 (+3.5%)
Δe (Oswald): +4.0%
Weakened vortex strength and decreased wake effects.
Fuel Savings
ΔCD_i: -4.2% reduction
Annual Saving: ~2,100 kg fuel/year per aircraft based on 500h flight time.
Priyangshu Karmakar (22AE10048)
The winglets effectively extend the wing span from the perspective of induced drag calculations.
The winglets reduce the induced drag by 4% approximately at cruise lift coefficients.
The Bombardier Challenger 650 wing incorporates raked winglets at the wing tips, a feature that improves efficiency through induced drag reduction.
Stabilizer Design & Directional Stability
Horizontal Tail
Area: 9.2 m² | AR: 6.6
Sh / Swing: 0.203 (Standard Range)
Ensures pitch authority across envelope and flare landing performance.
Vertical Tail (Fin)
Area: 5.8 m² | AR: 1.76
Cn_β: -0.0048 per degree
Provides positive directional stability (Negative derivative = Stable).
Meet Raju Meshram (22AE30019)
Spanwise Lift Distribution & Wing Box
Span Location % | Normalized Lift |
Root (0%) | 1.56 |
20% / 40% | 1.48 / 1.56 |
60% / 80% | 1.32 / 0.72 |
Tip (100%) | 0.00 |
Twin-Spar Concept
Front Spar: ~20% MAC (Primary Strength)
Rear Spar: ~60% MAC (Torsion Rigidity)
Fuel System: 5 internal tanks; 9,072L total capacity.
Bending Relief: Distributed fuel load reduces wing bending moments.
Jenish Patel (22AE30014)
Critical Mach Number & Shock Formation
M_crit (Cruise): 0.755 | M_crit (Comp): 0.76
Buffet Onset: Mach 0.82-0.85
Wave Drag: CD_wave ∝ (M - M_crit)⁴
Separation: Shock waves form on upper surface, causing flow separation and drag rise.
Supercritical Benefit: Delays shock to M=0.80 instead of M=0.70.
NACA 00XX-64 series (specifically the NACA 0011-64 at the root and NACA 0010-64 at the tip)
Operational Performance Predictions
Optimum Cruise (Max L/D = 13.72): Occurs at ~Mach 0.65. Current mission profile at Mach 0.80 trades 7% efficiency for higher speeds.
Mission Segment | Parameter | Value |
Cruise (37k ft) | True Airspeed / Fuel Burn | 236 m/s / 267 kg/h |
Climb Profile | Time to FL350 | 32 - 37 minutes |
Takeoff (SL) | V_stall / Dist (MTOW) | 145 kt / 1,720 m |
Landing (SL) | V_ref / Dist (Typ) | 140 kt / 732 m |
Gundla Sanjeev (22AE30011)
Design Summary & Achievements
Design Optimization
References
[1] Anderson, J. D. (2012). Introduction to Flight.
[2] Bombardier. (2024). Challenger 650 Specs.
[3] Raymer, D. P. (2012). Aircraft Design.
[4] NASA. (1998). Supercritical Airfoil Dev.
AR 8.46 balanced with structural weight.
Taper λ=0.25 improves stall and efficiency.
Supercritical wing enables Mach 0.85 capability.
Raked winglets reduce induced drag by 4%.
L/D Ratio of 12.75 facilitates 4,000 NM range.
Image Sources
https://bombardier.com/en/aircraft/challenger-650
Source: bombardier.com
https://bombardier.com/en/aircraft/challenger-650
Source: bombardier.com
https://eaglepubs.erau.edu/app/uploads/sites/4/2022/07/WingTwist.png
Source: eaglepubs.erau.edu
https://i.sstatic.net/U0N1T.jpg
Source: aviation.stackexchange.com
https://upload.wikimedia.org/wikipedia/commons/thumb/6/6d/Transonic_flow_patterns.svg/250px-Transonic_flow_patterns.svg.png
Source: en.wikipedia.org