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wing tip to wing tip. The wing spar passes under the fuselage below
the two front seats and is attached to the fuselage in two locations. Lift
and landing loads are carried by the single carry-through spar, plus a
pair of rear shear webs (one on each wing) attached to the fuselage.
G3 Wingspan is increase by three feet and wing geometry is slightly
changed with an 1° increase in dihedral which allows for the
elimination of the aileron-rudder interconnect system. Because of the
wingspan and geometry changes, aircraft performance data has been
updated and included in Section 5 - Performance.
The main landing gear is moved slightly inboard and the strut angle
increased to achieve an increase in airplane height of 1.5 inches.
Other G3 Wing updates include:
• wing tip with integral, leading edge recognition lights.
• relocation of the fresh air inlets to the engine cowl and related
environmental system changes,
• improved trailing edge aerodynamics
• improved wing root fairings,
• relocation of the stall warning port,
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Section 9 Cirrus Design
Supplements SR20
Figure - 1
74 inches 3-BLADE
188 cm
38.3 ft
11.67 m
9.1 ft
2.8 m
9 inches (minimum)
23 cm (minimum)
26.0 ft
7.92 m
8.9 ft
2.71 m
NOTE:
• Wing span includes
position and strobe lights.
• Prop ground clearance at
3050 lb - 9 inches (23 cm).
• Wing Area = 144.9 sq. ft.
SR20_FM01_2415
Turning Radius
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Cirrus Design Section 9
SR20 Supplements
9.1 ft. (2.77 m)
0.5 ft. (0.15 m)
24.3 ft. (7.41 m)
RADIUS FOR NOSE GEAR 7.0 ft. (2.16 m)
RADIUS FOR OUTSIDE GEAR
RADIUS FOR INSIDE GEAR
RADIUS FOR WING TIP
TURNING RADII ARE CALCULATED USING ONE BRAKE AND
PARTIAL POWER. ACTUAL TURNING RADIUS MAY VARY AS
MUCH AS THREE FEET.
GROUND TURNING CLEARANCE
SR20_FM01_2413
Figure - 2
Airplane Three View
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Section 9 Cirrus Design
Supplements SR20
The Airplane
Fuel
Total Capacity .............................................58.5 U.S. Gallons (221.0 L)
Total Usable ................................................56.0 U.S. Gallons (212.0 L)
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Cirrus Design Section 9
SR20 Supplements
Section 2 - Limitations
Airspeed Limitations
The indicated airspeeds in the following table are based upon Section
5 Airspeed Calibrations using the normal static source. When using
the alternate static source, allow for the airspeed calibration variations
between the normal and alternate static sources.
Speed KIAS KCAS Remarks
VNE 200 204 Never Exceed Speed is the speed limit
that may not be exceeded at any time.
VNO 163 166 Maximum Structural Cruising Speed is
the speed that should not be exceeded
except in smooth air, and then only with
caution.
VO
3050 Lb 130 131
Operating Maneuvering Speed is the
maximum speed at which full control
travel may be used. Below this speed the
airplane stalls before limit loads are
reached. Above this speed, full control
movements can damage the airplane.
VFE
50% Flaps
100% Flaps
119
104
120
104
Maximum Flap Extended Speed is the
highest speed permissible with wing
flaps extended.
VPD 133 135 Maximum Demonstrated Parachute
Deployment Speed is the maximum
speed at which parachute deployment
has been demonstrated.
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Section 9 Cirrus Design
Supplements SR20
Airspeed Indicator Markings
The airspeed indicator markings are based upon Section 5 Airspeed
Calibrations using the normal static source. When using the alternate
static source, allow for the airspeed calibration variations between the
normal and alternate static sources.
Weight Limits
Maximum Takeoff Weight ......................................... 3050 lb (1383 Kg)
Maximum Landing Weight ........................................ 3050 lb (1383 Kg)
Marking
Value
(KIAS)
Remarks
White
Arc
61 - 104 Full Flap Operating Range. Lower limit is the most
adverse stall speed in the landing configuration.
Upper limit is the maximum speed permissible with
flaps extended.
Green
Arc
69 - 163 Normal Operating Range. Lower limit is the
maximum weight stall at most forward C.G. with
flaps retracted. Upper limit is the maximum structural
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