STRATOS
Aircraft Performance
Simulation Environment
(Simulation of Thrust, Rate-of-climb, Aerodynamics, and Total Operating States)
A physics-based flight performance simulator for preliminary aerospace engineering analysis. Model subsonic aircraft performance using first-principles aerodynamic and propulsion equations.
Engineering-Grade Analysis
Comprehensive tools for preliminary aerospace engineering assessment
First-Principles Modeling
Physics-based computational engine utilizing aerodynamic and performance equations for accurate subsonic aircraft analysis.
Performance Plots
Generate comprehensive plots and visualizations of key metrics including drag polars, power curves, and flight envelopes.
Mission Analysis
Evaluate whether proposed aircraft configurations meet predetermined mission requirements with quantitative results.
Envelope Simulation
Compute complete flight envelope boundaries including service ceiling, maximum speed, and operational limits.
Four Integrated Subsystems
Thrust, Rate-of-climb, Aerodynamics, and Total Operating States working in harmony for comprehensive analysis.
Real-Time Calculations
Rapid computation of performance metrics enabling iterative design optimization and trade studies.
Four Integrated Subsystems
Each subsystem works in harmony to deliver comprehensive aircraft performance analysis
ACES
Atmospheric Condition & Standard Earth Systems
The foundation of the aircraft performance simulator. Computes atmospheric properties affecting the aircraft 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.
Key Functions
Comprehensive Capabilities
Full-spectrum analysis tools for preliminary aircraft design
Performance Analysis
- Maximum and cruise speed determination
- Rate of climb calculations
- Service and absolute ceiling computation
- Time to climb analysis
- Power required vs. power available curves
Range & Endurance
- Breguet range equation implementation
- Maximum range speed optimization
- Maximum endurance calculations
- Payload-range trade studies
- Fuel consumption analysis
Aerodynamic Analysis
- Drag polar generation
- Lift-to-drag ratio optimization
- Parasitic drag estimation
- Induced drag calculations
- Oswald efficiency factor modeling
Mission Simulation
- Multi-segment mission profiles
- Takeoff and landing performance
- Cruise segment optimization
- Reserve fuel requirements
- Configuration feasibility validation
Technical Specifications
Real-World Applications
Preliminary Design
Evaluate proposed aircraft configurations against mission requirements during early design phases.
Trade Studies
Conduct parametric analyses to understand how design changes affect overall performance.
Educational Tool
Demonstrate aircraft performance principles with real calculations and visualizations.
Configuration Validation
Verify that aircraft can meet specified range, speed, and altitude requirements.