Using NRLMSISE-00 with numerical propagator

Orekit usage
3

Hi @bcazabonne

Thanks alot for the help. So this is how i went about it. Is it right?
File orekitData = new File(“path to orekit data folder”);
DataProvidersManager manager = DataContext.getDefault().getDataProvidersManager();
manager.addProvider(new DirectoryCrawler(orekitData));
// Initialize Solar Activity Provider Data Provider
final CssiSpaceWeatherData cssi = new CssiSpaceWeatherData(CssiSpaceWeatherData.DEFAULT_SUPPORTED_NAMES,manager,timescale);

    // Drag
    final NRLMSISE00 atm  = new NRLMSISE00(cssi,sun,earth);
    IsotropicDrag spacecraft = new IsotropicDrag(area,Cd);

    DragForce drag =   new DragForce(atm,spacecraft);

I have another question, although it might be a silly one. When i use the tlePropagator.getInitialState() method, does it give a state vector computed from the oscullating orbital elements or do i get that after converting the tlePropagator to a numericalPropagator and calling numericalPropagator.getInitialState()?

Thank you