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ISM Original Work

STRATOS

Simulation of Thrust, Rate-of-climb, Aerodynamics, and Total Operating States

High-Fidelity Aircraft Performance & Envelope Simulation Environment

Launch Simulator

Project Overview

STRATOS is a physics-based flight performance simulator intended for preliminary aerospace engineering analysis. This custom-built computational tool models the performance of subsonic aircraft using first-principles aerodynamic and propulsion equations.

Real use cases include engineers testing whether proposed aircraft configurations can meet predetermined mission requirements. The simulator outputs plots and key metrics on flight performance, validated against real-world aircraft data with 1.5% accuracy on Boeing 737-800 stall speed calculations.

Technical Specifications

Aircraft Category

Subsonic

Modeling Approach

First-Principles

Atmosphere Model

ISA Standard

Drag Model

Parabolic Polar

Propulsion Types

Jet / Propeller

Altitude Range

0 - 15 km

Four Integrated Subsystems

Working in harmony for comprehensive aircraft performance analysis

ACES
Atmospheric Condition & Standard Earth Systems
Complete
The foundation of the simulator. Computes atmospheric properties as a function of altitude using the International Standard Atmosphere (ISA). Models temperature, pressure, and density from sea level through the troposphere (up to 15 km), covering the operational envelope of most subsonic aircraft.
RLM
Raw Logistic Modulator
Complete
Serves as a liaison between input aircraft values and core physics-based calculations. Takes raw input data (geometry, weight, propulsion, aerodynamic coefficients) and converts them into standardized, numeric variables, preventing physically impossible scenarios.
OSC
Optimal Statistics Calculator
Complete
Extracts meaningful performance metrics from raw numerical outputs. Delivers performance curves, contour plots, and critical metric values including minimum thrust required, maximum level flight speed, and optimal climb rates.
RS
Report Summarizer
In Development
Synthesizes all raw data and statistics into written/visual format for end users. Powered by an AI Language Model for near-instantaneous reports once simulation completes.

Comprehensive Capabilities

Performance Analysis
  • Maximum and cruise speed determination
  • Rate of climb calculations
  • Service and absolute ceiling computation
  • Power required vs. power available curves
Range & Endurance
  • Breguet range equation implementation
  • Maximum range speed optimization
  • Fuel consumption analysis
Aerodynamic Analysis
  • Drag polar generation
  • Lift-to-drag ratio optimization
  • Oswald efficiency factor modeling
Mission Simulation
  • Multi-segment mission profiles
  • Takeoff and landing performance
  • Configuration feasibility validation

Project Documentation

Original Work Proposal
Detailed project proposal outlining objectives, methodology, and timeline
Progress Update #1
Current state of development, completed modules, and next steps