|Peter Masak ridge soaring the Scimitar on Bald Eagle Mountain near Lock Haven, Pennsylvania|
|National origin||United States|
|Status||Sole example destroyed on 22 May 2004|
|Primary user||Peter Masak|
|Developed from||Schempp-Hirth Ventus|
The aircraft was destroyed and the designer killed in a soaring accident on 22 May 2004.
Design and development
The Scimitar was intended to use new aerodynamic technology to achieve higher performance in a competition sailplane. The aircraft mated a Schempp-Hirth Ventus fuselage with a wing of the same planform as the Schempp-Hirth Discus, outfitted with an electronic boundary layer control system.
The aircraft was involved in a minor accident on 25 April 1998 when trying to land after hitting sinking air while ridge soaring near Scrabble, West Virginia. While landing in a short 450 ft (137 m) length field the pilot ground looped the aircraft to avoid hitting a tree.
The Scimitar was destroyed on 22 May 2004 while flying in the US Nationals near Alexandria, Pennsylvania. Masak was attempting to cross a ridge line and struck a tree, resulting in his death. The US National Transportation Safety Board determined the cause of the accident to be "The pilot's failure to maintain airspeed, which resulted in an inadvertent stall/spin. A factor was the turbulent wind conditions." A "nationally known, locally based glider instructor" who assisted the accident investigation stated that if Masak had successfully crossed the ridgeline, "he would have been the only pilot to do so, and probably would have easily won the day."
- Scimitar I
- Original configuration for the FAI 15-Metre Class, with a wing employing a Wortmann FX 79-K-144 airfoil
- Scimitar II
- Later configuration for the FAI Standard Class, with a wing employing a PM-24 airfoil
Data from Sailplane Directory
- Crew: one
- Wingspan: 49 ft 3 in (15 m)
- Wing area: 113 sq ft (10.5 m2)
- Aspect ratio: 21.4
- Airfoil: Wortmann FX 79-K-144
- Empty weight: 600 lb (272 kg)
- Gross weight: 1,125 lb (510 kg) including 250 lb (113 kg) of water ballast
- Maximum glide ratio: 43:1 at 69 mph (111 km/h)
- Wing loading: 9.96 lb/sq ft (48.6 kg/m2)
- Related lists
- Activate Media (2006). "Scimitar Masak". Retrieved 16 August 2011.
- Federal Aviation Administration (August 2011). "Make / Model Inquiry Results". Retrieved 15 August 2011.
- National Transportation Safety Board (May 2004). "NTSB Identification: LAX75DUJ07". Retrieved 16 August 2011.
- Lednicer, David (2010). "The Incomplete Guide to Airfoil Usage". Retrieved 1 August 2011.
- National Transportation Safety Board (April 1998). "NTSB Identification: NYC98LA098". Retrieved 16 August 2011.