Survey of European and Major ISC Facilities for Supporting Mars and Sample Return Mission Aerothermodynamics and Tests Required for Thermal Protection System and Dynamic Stability

Table 2

Capabilities of some available European installations for investigation of aerothermodynamics during a Martian entry.

Facility	Running time	Flow regime	Mach	P0 (Pa)	T0 (K)	Heat flux (MW/m^2)	Re	Comments
HEG, DLR	1 to 5 ms	High enthalpy	8.4 to 10.7 (4.6–6.2 km/s)	35 to 90 × 10^6	6600 to 9700	1–22	0.2 to 1.1 × 10^6	High enthalpy condition: ℎ0= 11–23 MJ/Kg DLAS
L3K, DLR	Up to 30 mn	High enthalpy, laminar flow	5 to 10	0.15 to 1.8 × 10^6	Up to 7000	Up to 4	Up to 10^5	Enthalpy up to 25 MJ/Kg DLAS
TH2, RWTH	2 to 10 ms	Cold hypersonic	6 to 12	4 to 60 × 10^4	1500 to 7400	0.7 to 20	Up to 10^7	Detonation driver mode for high enthalpy condition; No DLAS
Longshot, VKI	25 to 70 ms	Cold hypersonic	10 to 20	1 to 4 × 10^8	1500 to 3500	n.a.	At 𝑀=14, 5 × 10^3 to 15 × 10^6	No DLAS
F4, ONERA	Up to 200 ms	High enthalpy	7 to 21	2 to 10 × 10^7	1500 to 7500	n.a.	5 × 10^6 (𝑀=10) to 10^6 (𝑀=21)	DLAS
SIMOUN, ASTRIUM	Up to 5 mn	High enthalpy	4 (flat plate)–4.5 stag. point	Up to 10^4	n.a.	Up to 1.3 (stag. point)–0.7 (flat plate)	n.a.	DLAS
HHK, HTG	100 ms	Cold hypersonic	7 (5.7 km/s)	30 to 350 × 10^2	Up to 900	n.a.	3 to 5 × 10^6	No DLAS
STA-STB, ISL	4 ms	Hypersonic, low enthalpy	3.5 to 10 (3.5 km/s)	Up to 10^6	n.a.	Up to 10	10^6 for 𝑀=10	Higher Mach number possible; No DLAS
HST2, UMIST	Up to 10 ms	Hypersonic, low enthalpy	5.75 to 12	n.a.	n.a.	n.a.	n.a.	No DLAS