The AQUILA A 210 is a
single-engine airplane in fibre composite construction and designed
for cruising, training and aero-tow applications. It is equipped
with two side-by-side seats, low wings and a cruciform tail.
AQUILA Technische Entwicklungen GmbH with its headquarters in
Schönhagen near Berlin is responsible for development and production
of the aircraft.
The wing employs a low-drag
laminar flow airfoil with Fowler flap of the Horstmann-Quast (HQ)
series which was specifically designed for this airplane by DLR
Braunschweig (German Aerospace Center). The triple-tapered plan form
of the wings provides excellent flight and handling characteristics
at minimum drag from cruise speed down to stall speed. The
electrically operated Fowler flap is very efficient and produces
high maximum lift in landing configuration. This results in low
landing speeds and allows short landing distances due to appropriate
drag production. In takeoff configuration it produces sufficient
lift to safely operate the airplane from short, unpaved runways. The
shell structure of the wing is made in GFRP/foam sandwich
construction. Spar and load bearing structures are made of CFRP.
Empennage, flaps and control surfaces are made in GFRP/foam sandwich
construction with CFRP reinforcements.
The fuselage is a GFRP monocoque with CFRP stringers and GFRP/CFRP
Due to the side-by-side arrangement of the seats, the spacious,
enclosed cockpit provides sufficient room even to tall pilots.
Complete glazing of the canopy allows an excellent all-round vision
which is particularly advantageous during instruction and training.
The baggage compartment is located behind the adjustable seats. It
can be easily accessed through a door located on one side of the
fuselage. Baggage compartment capacity is meeting even the highest
The fixed tricycle landing gear consists of the
main gear in sturdy steel strut construction and a conveniently
spring-suspended, steerable nose gear. Three large wheels of the
same size allow aircraft operation even under severe training
conditions as well as operation from uneven runways.
The individually controllable main-wheel brakes as well as the nose
wheel to be operated by the rudder pedals allow narrow taxiing
The hydraulically operated constant speed
propeller of type mt-propeller MTV-21-A/175-05 is driven by a
4-stroke / 4-cylinder piston engine of type ROTAX 912S (100 hp). Two
integral tanks inside the wings with a fuel capacity of 60 l each,
low fuel consumption and a high cruising speed allow a range that is
exceptional in this category of aircraft. The possibility of
operating the engine with unleaded premium automobile gasoline
further improves efficiency. Being well below future noise limits
will allow aircraft operation at any airfield without any problems.
The electrical system is designed for 14-volt
supply including alternator and battery. All electrical loads are
controlled by individual circuits and connected to the supply system
by means of rocker-type switches or circuit breakers respectively.
An ignition switch actuates two separate ignition circuits.
The AQUILA A 210 airplane is certified
according to JAR-VLA allowing unrestricted VFR day operation exept
aerobatics. The aircraft will be also certified for glider towing
Rotax 912S - 100 HP
hydraulic variable pitch MT
2 x 60 litres
1300 Km - 700 Nm
rate of climb
landing distance, ground roll
710 ft / mn
240 Km/h - 130 Knt
limiting and recommended speeds
design manoeuvring speed (Va)
never exceed speed (Vne)
stall, power off (Vsl)
landing approach speed
+4 / -2
305 Km/h - 165 Knt
All specifications are based on manufacturer's