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airplane will obtain the highest altitude in a given horizontal
distance. The best angle-of-climb speed normally increases
slightly with altitude.
VY Best Rate of Climb Speed is the speed at which the
airplane will obtain the maximum increase in altitude per unit
of time. The best rate-of-climb speed decreases slightly with
altitude.
IMC Instrument Meteorological Conditions are meteorological
conditions expressed in terms of visibility, distance from
cloud, and ceiling less than the minima for visual flight
defined in FAR 91.155.
ISA International Standard Atmosphere (standard day) is an
atmosphere where (1) the air is a dry perfect gas, (2) the
temperature at sea level is 15° C, (3) the pressure at sea
level is 29.92 in.Hg (1013.2 millibars), and (4) the
temperature gradient from sea level to the altitude at which
the temperature is -56.5° C is -0.00198° C per foot and zero
above that altitude.
MSL Mean Sea Level is the average height of the surface of the
sea for all stages of tide. In this Handbook, altitude given as
MSL is the altitude above the mean sea level. It is the
altitude read from the altimeter when the altimeter’s
barometric adjustment has been set to the altimeter setting
obtained from ground meteorological sources.
OAT Outside Air Temperature is the free air static temperature
obtained from inflight temperature indications or from ground
meteorological sources. It is expressed in either degrees
Celsius or degrees Fahrenheit.
Revision A7
1-10 P/N 13772-001
Section 1 Cirrus Design
General SR22
Engine Power Terminology
Performance and Flight Planning Terminology
• Pressure Altitude is the altitude read from the altimeter
when the altimeter’s barometric adjustment has been set to
29.92 in.Hg (1013 mb) corrected for position and instrument
error. In this Handbook, altimeter instrument errors are
assumed to be zero.
• Standard Temperature is the temperature that would be
found at a given pressure altitude in the standard
atmosphere. It is 15° C (59° F) at sea level pressure altitude
and decreases approximately 2° C (3.6° F) for each 1000
feet of altitude increase. See ISA definition.
HP Horsepower is the power developed by the engine.
MCP Maximum Continuous Power is the maximum power that
can be used continuously.
MAP Manifold Pressure is the pressure measured in the
engine’s induction system expressed as in. Hg.
RPM Revolutions Per Minute is engine rotational speed.
• Static RPM is RPM attained during a full-throttle engine
runup when the airplane is on the ground and stationary.
g One “g” is a quantity of acceleration equal to that of earth’s
gravity.
• Demonstrated Crosswind Velocity is the velocity of the
crosswind component for which adequate control of the
airplane during taxi, takeoff, and landing was actually
demonstrated during certification testing. Demonstrated
crosswind is not considered to be limiting.
• Service Ceiling is the maximum altitude at which the
aircraft at maximum weight has the capability of climbing at
a rate of 100 feet per minute.
GPH Gallons Per Hour is the amount of fuel (in gallons)
consumed by the aircraft per hour.
Revision A7
P/N 13772-001 1-11
Cirrus Design Section 1
SR22 General
Weight and Balance Terminology
NMPG Nautical Miles Per Gallon is the distance (in nautical miles)
which can be expected per gallon of fuel consumed at a
specific engine power setting and/or flight configuration.
• Unusable Fuel is the quantity of fuel that cannot be safely
used in flight.
• Usable Fuel is the fuel available for flight planning.
c.g. Center of Gravity is the point at which an airplane would
balance if suspended. Its distance from the reference datum
is found by dividing the total moment by the total weight of
the airplane.
• Arm is the horizontal distance from the reference datum to
the center of gravity (c.g.) of an item. The airplane’s arm is
obtained by adding the airplane’s individual moments and
dividing the sum by the total weight.
• Basic Empty Weight is the actual weight of the airplane
including all operating equipment that has a fixed location in
the airplane. The basic empty weight includes the weight of
unusable fuel and full oil.
MAC Mean Aerodynamic Chord is the chord drawn through the
centroid of the wing plan area.
LEMAC Leading Edge of Mean Aerodynamic Chord is the forward
edge of MAC given in inches aft of the reference datum
(fuselage station).
　
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