What seems to be a (CGI?) illustration of an MFI test model, somewhat like a Soviet "HIMAT".
DM5.12 MODEL
| Weight range | 480-520 kg |
| Altitude range | 500-7000 m |
| Speed range | 40-150 m/sec |
| Experiment duration | 150 sec |
| Number of recorded parameters | 128 |
- Pneumatic control surfaces actuators;
- Start from a Mi-8MT carrier helicopter;
- Landing with a triple-canopy parachute cluster and airbag shock absorber.
The operations were conducted during 1986-1992.
The models had the modular design concept. The versions of aerodynamic layout permitting to realize controlled high-angle-of-attack flight under the full airflow breakaway were completed with these models. The problems of aerodynamic and gas-dynamic control methods combination, control system structure and laws were investigated during the flight tests at supercritical angles of attack, under the stall and spin conditions.
The obtained research results allowed to receive a series of advanced aerodynamic layouts for high manoeuvering aircraft.
From
http://www.khai.edu/niipfm/english/dm512-en.htm (link now dead)
Pictures showing the SLM-22 first test model for the Sukhoi Berkut. It looks like the inlet design is significantly different.
SLM-22 MODEL
| Weight | 950 kg |
| Altitude range | 1500-5000 m |
| Speed range | 40-120 m/sec |
| Experiment duration | 600 sec |
| Number of recorded parameters | 128 |
- Hydraulic control surfaces actuators;
- Start from a Mi-8MT carrier helicopter;
- Landing with the parachute and hydraulic shock absorber.
The model was created in period from 1986 to 1990 and tested in 1991-92.
The following research programs were performed with the model:
- Research of stability, controllability, stall, spin and methods of spin recovery for an aircraft with the forward-swept wing and different control laws also;
- Research of pressure distribution, air vortexes trajectories and airflow over the surfaces of plane units visualization;
- Research of air consumption through the engine gas flow duct effect to the stability and controllability characteristics.
From
http://www.khai.edu/niipfm/english/slm22-en.htm (link now dead)
SLM-32 MODEL
| Weight | 1200 kg |
| Altitude range | 500-5000 m |
| Speed range | 40-200 m/sec |
| Experiment duration | 600 sec |
| Number of recorded parameters | 128 |
- Power plant - M-601M turbojet;
- Hydraulic control surfaces actuators;
- Start from a Mi-8MT carrier helicopter;
- Landing with the parachute and hydraulic shock absorber.
SLM-32
The model was created in period from 1988 to 1992 and tested till 1999.
The model was the further development of SLM-22 model. It was equipped with turbojet engine.
The following research programs were performed with the model:
- Research of stability, controllability, stall, spin and methods of spin recovery for an aircraft with the forward-swept wing and different control laws also;
- Research of effect of power plant operation mode to the streamlining, stability, controllability, stall and spin characteristics.
(link now dead)
