| Technical data | |
|---|---|
| Type | MR-2 |
| Function | Naval Recce |
| Year | 1926 |
| Crew | 2 |
| Engines | 1*450hp Lorraine-Dietrich |
| Length | 13.6m |
| Wingspan | 15.6m |
| Wing area | 56.7m2 |
| Empty weight | 1770kg |
| Loaded weight | 2770kg |
| Wing Load (kg/m2) | 49.0 |
| Power load (kg/hp) | 6.2 |
| Speed at 0m | 179km/h |
| Landing Speed | 82km/h |
| Landing Roll | 15sec |
| Takeoff Roll | 25sec |
| Range | 900km |
| Flight Endurance | 5h |
| Ceiling | 4200m |
| Climb | |
| 1000m | 7min |
| 2000m | 17min |
| 3000m | 34min |
| Armament | |
| Guns | 1...2 ? |
| Bombs | ? |
MR-2 by D.P.Grigorovich
Biplane flying boat, development of the MRL-1, with more powerful engine and increased upper wing span. The hull shape was also improved, less expensive materials were used in construction.
Flight tests started on September 23, 1926. Series of successful flights (naval pilot A.S.Melnitskij) made positive impression on designers and factory trial commetee.
State Acceptance Trials were performed by F.S.Rastegaev, pilot from NII VVS. Since he had no experience with naval aircraft, he performed several training flights on MU-1 and MUR-1 (one flight on each plane).
The very first flight (October 19) ended with catastrophe. On low altitude MR-2 suddenly did lose stability. Longitudinal oscillations with increasing amplitude resulted in steep dive, and aircraft crashed into the water up-side-down.
Investigations of the accident revealed too rear (48%) location of the CG and positive angle of tailplane installation. TsAGI wind tunnel tests proved this configuration catastrophically unstable...
| Predecessors | Modifications |
|---|---|
| MRL-1 |
 MR-3 |
| References | Links |
|---|---|
|
None? |
