Global InformationTM65 information
| Country of origin |  Denmark |
|---|---|
| Designer | Copenhagen Suborbitals |
| Manufacturer | Copenhagen Suborbitals |
| Application | lower stage booster |
| Predecessor | XLR-3A, XLR-3B [1] |
| Status | In development |
| Liquid-fuel engine | |
| Propellant | LOX / Ethanol |
| Mixture ratio | 75 % vol Ethanol / 25 % water[2] |
| Cycle | Gas-generator |
| Configuration | |
| Chamber | L* = 200 cm |
| Nozzle ratio | 1:4.5 |
| Performance | |
| Thrust, vacuum | 85 kN (19,000 lbf) |
| Thrust, sea-level | 65 kN (15,000 lbf)[3] |
| Thrust-to-weight ratio | 75:1 |
| Chamber pressure | 1.2 MPa (12 bar)[4] |
| Specific impulse, vacuum | 230 seconds (2.3 km/s)[4] |
| Specific impulse, sea-level | 200 seconds (2.0 km/s)[4] |
| Burn time | 100 sec as used in HEAT 2X launch vehicle |
| Dimensions | |
| Length | total 1700 mm |
| Diameter | chamber 400 mm |
| Dry weight | 75 kg |
| Used in | |
| Planned use in HEAT 2X launch vehicle | |
TM65 is a rocket engine developed by Copenhagen Suborbitals. TM65 uses Ethanol and liquid oxygen as propellants in a pressure-fed power cycle.
- ^ "A rocket is born (Danish)". Archived from the original on 2013-02-12.
- ^ "TM65 in numbers (Danish)". Archived from the original on 2012-12-21.
- ^ "TM65 Liquid propellant rocket engine". Archived from the original on 2012-05-16.
- ^ a b c Cite error: The named reference
ingdk1was invoked but never defined (see the help page).