Browser-Based Aerospace Engineering

Aerodynamic Design
From Airfoil to Flight Model.

Lumina Dynamic combines airfoil analysis, propeller estimation, CFD preparation, and flight-simulation planning in one browser-based engineering workspace.

Engineering Workflow

One browser workspace for aerodynamic iteration.

Model

Airfoil libraries, custom coordinates, and STL geometry.

Analyze

Run solver-backed polars, propeller estimates, and CFD setup.

Report

Export CSV and PDF outputs for engineering review.

Simulate

Prepare aero databases and mass properties for flight-dynamics runs.

01

Start With Airfoils

Screen NACA, Selig, or custom profiles with NeuralFoil and XFOIL-backed polar generation before committing to a vehicle layout.

02

Build the Aircraft Model

Move from section data into propeller performance, STL geometry review, CFD preparation, and component definitions for the full aircraft.

03

Prepare Flight Simulation

Carry aerodynamic databases, mass properties, and propulsion assumptions toward a flight-dynamics workspace as the simulation pipeline matures.

End-to-End Design Pipeline

Comprehensive Aerodynamic Engineering.

Lumina Dynamic connects today's working airfoil and propeller tools with an active roadmap for CFD execution and flight-dynamics workflows. Start with fast browser iteration, then scale concepts into deeper simulation stages as the platform expands.

Active

Airfoil Studio

Rapidly evaluate 1600+ Selig/NACA profiles or upload custom coordinate geometries (.DAT). Leverage thin-airfoil theory and empirical viscous corrections to generate engineering-grade lift, drag, and pitching moment polars instantly.

Cl/Cd/Cm Polars Viscous Flow
Active

Propeller Studio

Upload your complex STL rotor geometries. Our solver slices the 3D mesh into radial stations and applies advanced Blade Element Momentum Theory (BEMT) to accurately calculate thrust, torque, and overall aerodynamic efficiency.

STL Parsing BEMT Solver
Beta Phase

CFD Studio

OpenFOAM-based CFD preparation and visualization are in beta. Our roadmap targets automated meshing, cloud execution, and richer flow-field diagnostics for uploaded CAD/STL geometries.

Navier-Stokes Auto-Meshing
Beta Phase

Flight Simulation Studio

Build flight-simulation inputs from aerodynamic databases, component selections, and mass-property definitions. The current workspace prepares this pipeline while runtime simulation features continue to mature.

Flight Simulation Stability Analysis
Compute Architecture

Powered by Industry-Standard Engines.

We bring practical aerospace iteration into the browser. By combining classical aerodynamic solvers, AI-assisted interpretation, WebGL visualization, and cloud-connected backend services, Lumina Dynamic reduces local setup while leaving room for higher-capacity simulation workflows.

NeuralFoil & XFOIL

Hybrid 2D solver architecture. We use NeuralFoil for near-instant AI-driven estimations, validated by the time-tested XFOIL 6.99 panel method for high-fidelity viscous and inviscid interactions.

BEMT + Wake Theory

Advanced rotorcraft analytics. Our propeller module uses Blade Element Momentum Theory (BEMT) with practical correction models to estimate thrust, torque, inflow behavior, and tip losses.

OpenFOAM

The backbone of our 3D CFD roadmap. We are building around OpenFOAM for robust, Navier-Stokes computation, automated case preparation, and STL-based meshing workflows.

Cloud & WebGL

A cloud-connected engineering experience. Backend services powered by a FastAPI/Python stack, paired with hardware-accelerated 3D visualization using Three.js.

Available

Airfoil and Propeller Analysis

In Build

CFD and Flight Simulation Pipeline

Expandable

Built for Future Compute Capacity

Pay As You Go

Credit System

No monthly subscriptions. Just buy credits and use the computational power you need, exactly when you need it.

Module Processing Costs

  • Airfoil Studio 2D Free
  • Propeller Studio 3D
    Free / Basic 15 CR / Pro
  • CFD Analyzer Beta Phase TBD
  • Flight Simulator In Dev TBD
Custom Pack

Build Your Bundle

Credits

Total: €50.00

Perfect for running multiple airfoil comparisons, propeller optimizations, and extracting full PDF reports. Minimum 50 credits.

Log In

Access your engineering portal

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Book a Technical Demo

See how Lumina Dynamic can scale your aerodynamic workflow.

Settings

Account Profile

Manage your personal information and login credentials.

Billing & Credits

View your balance and top up your account.

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0 CR

Support & Invoices

For professional invoice requests or custom enterprise credit packages, please contact our support team at info@luminadynamic.com

LUMINA DYNAMIC

ENGINEERING CLOUD

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Recent Transactions

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Airfoil Studio 2D

Airfoil analysis.

+ NEW Airfoil Analysis

Recent Airfoils

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Propeller Studio 3D

Propeller performance analysis.

+ NEW Propeller Analysis

Recent Propeller Analysis

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CFD Studio 3D

Cloud CFD Analysis.

+ NEW CFD Analysis

Recent CFD Analysis

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Flight Performance

Trim, hover, endurance, and range estimates.

+ New Study

Recent Performance

  • Start a performance study

Flight Simulator Studio

Simulink-ready flight dynamics workspace.

+ New Simulation

Recent Simulations

  • No flight simulations yet

System Identification

Estimate dynamic models from flight-test and bench data.

+ New Identification

Recent Identifications

  • Start a system identification run

Flight Simulation

3D View X / Y / Z
Integration Console 

                        

                    

                

            


            
            

                

                

                    

                        

                            

                                
Frequency Response Identification

                                
System Identification

                                
Workflow for conditioning measured input/output histories, checking coherence, and fitting flight-dynamics transfer functions.

                            

                            

                                 Local FRF estimator
                            

                        


                        

                            

                                
Model

                                
TF 1P

                            

                            

                                
DC Gain

                                
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Bandwidth

                                
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Coherence

                                
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Frequency Response & Coherence

                                    Build FRF to plot
                                

                                

                                    
                                

                            


                            

                                
Identification Ledger

                                

                                    
No frequency response has been built yet.

                                

                            

                        


                        

                            

                                

                                Identification Console
                            

                            
Ready.

                        

                    

                

            
            
            

                

                

                    

                        

                            

                                
Standalone Module

                                
Flight Performance

                                
Independent sizing estimates for endurance, range, hover thrust, and steady cruise trim.

                            

                            

                                 Not checked
                            

                        


                        

                            

                                
Max Endurance

                                
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Max Range

                                
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Hover Thrust

                                
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Cruise Thrust

                                
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Range Sweep

                                    Run range sweep to plot
                                

                                

                                    
                                

                            


                            

                                
Latest Result

                                

                                    
No calculation has been run yet.

                                

                            

                        


                        

                            

                                

                                Performance Console
                            

                            
Ready.

                        

                    

                

            


            
            


                
                

                
                


                    
                    

                        

                            
                            Backend server is unavailable. Using the browser-side approximation model.
                            Run uvicorn main:app --reload for live solver
                            results.
                        

                    

                    

                        

                            

                            

                                Stall Region
                            

                        

                    


                    
                    

                        
                        
                        
                        
                        
                        
                        

                            Thin
                                Airfoil Theory + Stall Model
                        

                    


                    
                    


                        

                            

                                
                            

                            
Add a profile and run analysis

                            
Select or upload airfoil geometries from the
                                sidebar to execute the solver.

                        


                        

                            
                        


                        

                            

                        


                    

                

            


            
            

                

                

                    

                        

                            
                            
                        


                        

                            


                            
                        


                        

                            

                                
Thrust (T)

                                
0 N

                            

                            

                                
Torque (Q)

                                
0 Nm
                                

                            

                            

                                

                                    Power (P)

                                
0 kW

                            

                        


                        

                            

                                

                                Solver Live Logs
                            

                            

                            

                        


                    

                

            




            
            

                

                

                    

                    

                        
                        

                            

                                

                                    

                                        Surface Field Legend

                                    
                                

                                

                                

                                

                                    -1.0
                                    0.0
                                    +1.0