Flight Simulator GUI: Physics-Based Aircraft Simulation with Real-Time Rendering
A 60Hz physics engine with 6-DOF dynamics and ImGui instrumentation

I built a fully functional flight simulator from scratch using C++, OpenGL, and ImGui. This isn't just a simple visualization—it's a physics-accurate simulation that models real aircraft behavior using 6-degree-of-freedom (6-DOF) dynamics. The simulator runs at 60 Hz with a 4th-order Runge-Kutta (RK4) integrator to ensure numerical stability and accuracy, just like professional flight simulation software.

The system features a complete cockpit instrument panel including an airspeed indicator, altimeter, attitude indicator, heading indicator, vertical speed indicator, and turn coordinator—all rendered in real-time using ImGui's DrawList API. The 3D visualization provides a pilot's perspective with an artificial horizon, ground reference, and compass tape.

Flight Simulator in Action

Real-time 60Hz physics simulation with full cockpit instrumentation and 3D visualization


System Architecture

┌─────────────────────────────────────────────────────────┐
│                     Main Loop (60 Hz)                    │
│                      (main.cpp)                          │
└────────────┬────────────────────────────┬────────────────┘
             │                            │
             ▼                            ▼
    ┌────────────────┐          ┌─────────────────┐
    │ Input Handler  │          │   Renderer      │
    │                │          │  (OpenGL +      │
    │ - Keyboard     │          │   ImGui)        │
    │ - Controls     │          │                 │
    └────────┬───────┘          └────────┬────────┘
             │                           │
             ▼                           │
    ┌────────────────┐                  │
    │    Aircraft    │◄─────────────────┘
    │                │         (renders)
    │ - State        │
    │ - Properties   │
    │ - Aero Coeff   │
    └────────┬───────┘
             │
             ▼
    ┌──────────────────┐
    │ Flight Dynamics  │
    │                  │
    │ - Forces         │
    │ - Moments        │
    │ - RK4 Integration│
    └────────┬─────────┘
             │
             ▼
    ┌──────────────────┐
    │   Atmosphere     │
    │                  │
    │ - ISA Model      │
    │ - ρ, P, T, a     │
    └──────────────────┘
                

Data Flow Pipeline

User Input ──► InputHandler ──► Aircraft State
                                      │
                                      ▼
                            FlightDynamics.update()
                                      │
                    ┌─────────────────┴─────────────────┐
                    │                                   │
                    ▼                                   ▼
            calculateForces()                  calculateMoments()
                    │                                   │
                    └─────────────────┬─────────────────┘
                                      │
                                      ▼
                            RK4 Integration (4 steps)
                                      │
                                      ▼
                          Update Aircraft State
                                      │
                    ┌─────────────────┴─────────────────┐
                    │                                   │
                    ▼                                   ▼
            Instruments.render()              Renderer.render3D()
                

Core Components

Aircraft Module

Purpose: Manages aircraft state and aerodynamic properties

  • Position in NED frame (x, y, z)
  • Velocity in body frame (u, v, w)
  • Angular rates (p, q, r)
  • Euler angles (roll, pitch, yaw)
  • Control surfaces (elevator, aileron, rudder)

Flight Dynamics

Purpose: Physics integration using RK4

  • Force calculations (lift, drag, thrust)
  • Moment calculations (roll, pitch, yaw)
  • 4th-order Runge-Kutta integration
  • Ground collision detection

Atmosphere Model

Purpose: ISA atmospheric properties

  • Temperature, pressure, density
  • Speed of sound calculation
  • Troposphere & stratosphere modeling
  • Altitude-dependent properties

Instruments

Purpose: Real-time cockpit display

  • Airspeed indicator (0-200 knots)
  • Altimeter (0-10,000 feet)
  • Attitude indicator (artificial horizon)
  • Heading indicator (compass)
  • Vertical speed indicator (±2000 fpm)

Technologies Used


Aerodynamic Model

The simulator uses a complete 6-degree-of-freedom aerodynamic model with stability derivatives:

Forces (Body Frame):
X = -D·cos(α) + L·sin(α) + T - mg·sin(θ)
Y = Y_side + mg·sin(φ)·cos(θ)
Z = -D·sin(α) - L·cos(α) + mg·cos(φ)·cos(θ)
Moments (Body Frame):
L_roll = ½ρV²S·b·Cl (Rolling moment)
M_pitch = ½ρV²S·c·Cm (Pitching moment)
N_yaw = ½ρV²S·b·Cn (Yawing moment)
Aerodynamic Coefficients:
CL = CL₀ + CLα·α + CLδe·δe
CD = CD₀ + K·CL²
Cm = Cm₀ + Cmα·α + Cmδe·δe + Cmq·q̂
Cl = Clβ·β + Clδa·δa + Clδr·δr + Clp·p̂
Cn = Cnβ·β + Cnδa·δa + Cnδr·δr + Cnr·r̂

RK4 Integration Method

The simulation uses 4th-order Runge-Kutta integration for superior numerical accuracy compared to Euler or midpoint methods. This is the industry standard for flight simulation.

k₁ = f(t, y)
k₂ = f(t + dt/2, y + k₁·dt/2)
k₃ = f(t + dt/2, y + k₂·dt/2)
k₄ = f(t + dt, y + k₃·dt)

y_new = y + (k₁ + 2k₂ + 2k₃ + k₄)·dt/6

Advantages:


Control Mapping

Keyboard        →    Aircraft Control
──────────────────────────────────────
W/S, ↑/↓        →    Elevator (pitch)
A/D, ←/→        →    Aileron (roll)
Q/E             →    Rudder (yaw)
Z/X, PgUp/PgDn  →    Throttle
Space           →    Center controls
P               →    Pause/Resume
R               →    Reset
ESC             →    Exit
                

Coordinate Systems

The simulator uses two primary coordinate frames:

NED (North-East-Down)

Inertial reference frame

     North (x)
       ↑
       │
       │
       └────► East (y)
      ╱
     ╱
    ↓ Down (z)
                        

Body Frame

Aircraft-fixed reference

     Forward (x)
       ↑
       │ (nose)
       │
       └────► Right (y)
      ╱
     ╱
    ↓ Down (z)
                        

Transformations between frames use rotation matrices R(φ,θ,ψ) based on Euler angles.


Performance Characteristics

                            
#include "aircraft.hpp"
#include "flight_dynamics.hpp"
#include "renderer.hpp"
#include "input_handler.hpp"
#include <chrono>

int main() {
    // Initialize systems
    Renderer renderer;
    Aircraft aircraft;
    FlightDynamics dynamics(&aircraft);
    InputHandler input(&aircraft);
    
    // Main loop at 60 Hz
    const double dt = 1.0 / 60.0;
    double accumulator = 0.0;
    
    auto lastTime = std::chrono::high_resolution_clock::now();
    
    while (!renderer.shouldClose()) {
        auto currentTime = std::chrono::high_resolution_clock::now();
        double frameTime = std::chrono::duration<double>(
            currentTime - lastTime).count();
        lastTime = currentTime;
        
        accumulator += frameTime;
        
        // Physics update with fixed timestep
        while (accumulator >= dt) {
            input.processInput();
            dynamics.update(dt);
            accumulator -= dt;
        }
        
        // Render frame
        renderer.render(aircraft);
    }
    
    return 0;
}
                            
                        

Extension Possibilities

The modular architecture makes it easy to extend the simulator:


Key Takeaways

This project demonstrates:

Building this flight simulator taught me the fundamentals of physics-based simulation, real-time systems, and the mathematics behind aircraft flight. The project combines aerospace engineering principles with software engineering practices to create a realistic and performant simulation.