From the aerodynamic point of view, spacecraft and launchers are characterized by the wide range of velocity between low speed during start and landing and hypersonic speed in the reentry phase. DNW offers test facilities for the different flight segments up to Mach-number 6.8. Although the speed range is similar, the variety of spacecraft geometries requires test set-ups different to those of usually slender missiles. If aero-thermodynamic effects have to be tested DNW might arrange contacts to the mother institution DLR, which operates a number of specialized facilities.

Owing to the complexity of space and reentry missions, the scope of test methods is wide as well. Typical objectives are:

- configurational design optimization (stability, control, performance)
- aerodynamic data sets
- loads: static and dynamic, acoustic
- stage separation
- wind loads (on launch platform)
- ground effect
- parachute landing
- heat transfer
- dynamic derivatives

DNW is able to offer well established and advanced simulation and measurement techniques as well as experienced personnel necessary to cover these requirements and to assist customers in designing complex test set-ups. Especially the capabilities of unsteady data acquisition, optical surface (PSP, TSP) and flow field (PIV) measurement techniques, acoustic array technique, and high speed quantitative infrared observation qualify DNW to meet the special challenges of spacecraft and launcher testing. In case of sophisticated heat transfer or light weight dynamic derivative wind tunnel models, the customer can benefit from the cooperation of DNW with the specialized DLR and NLR workshops.