SM-2 and SM-2P experimental ekranoplans by R.E.Alexeiev
| General Information | |
|---|---|
| Type | SM-2P |
| Function | Experimental |
| Year | 1962 |
| Crew | 3 |
| Powerplant | |
| Type | |
| Power at m | |
| Size (m) | |
| Length | 20.0 |
| Height | ? |
| Wingspan | 11.5 |
| Wing area (m2) | ? |
| Weights (kg) and loads | |
| Empty | ? |
| Loaded | |
| Wing Load (kg/m2) | ? |
| Power load (kg/hp) | ? |
| Speed (km/h) | |
| Takeoff | 160 |
| Maximum | 270 |
| Maneuverability | |
| Turn time | sec |
| Roll | |
| Landing | m sec |
| Takeoff | m sec |
| Range | |
| Practical | km |
| Flight Endurance | hmin |
| Ceiling | |
| Ceiling | m |
| Seaworthiness | |
| Wave height | 0.5m |
| Payload | |
| Fuel | ?kg |
;)
|
Experimental ekranoplan (WIG vehicle) SM-2 was built at the same time as SM-1 and had almost identical construction. It was damaged in a hangar fire. Trials of the SM-1 revealed shortcomings of the tandem configuration, and SM-2 was restored as a SM-2P.
New aircraft had single rectangular (priamougolnoe in Russian, so the P in designation) wing with aspect ratio 1.2 and a high T-tail. Single engine of the SM-2P was installed in the extreme tail, with air intake at the tail fin root.
Handling was better than of the SM-1, but takeoff run was still un-practical. For the lift, aircraft relied entirely on the dynamic air cushion . To achieving sufficient lift without power augmentation, SM-2P had to accelerate to
| Predecessors | Modifications |
|---|---|
| SM-1 | SM-2P7 |
