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The turning flight can be broadly classified in two categories: 1) steady tuming
flight in a horizontal plane and 2) general tuming flight. In a steady or constant-
velocity turning fiight in a horizontal plane, the airplane is at a constant altitude,
whereas the general turning fiight may involve a gain orloss of altitude. The routine
flights of commercial transport and general aviation airplanes usually belong to the
first category. The examples of the second category are the turning flight of a glider
and that offighter aircraft performinglimiting turns exploiting the full aerodynamic
and structural capabiMes. We will also discuss a new concept in turning known
as the Herbst maneuver, which is said to exceed the best performance attainable
by the conventional tuming maneuvers of category 1) and 2):
2.8.1 Equations of Motion for Turning Flight
The forces acting on an airplane in a steady, constant-velocity turn with bank
angle ,u, and sideslip p are shown iri Fig. 2.26. The aircraft has to bank or sideslip
to generate the necessary centripetal force. The following equations govern the
steady turning flight.
Along the flight path,
Tcosp - D - W siny - 0
Along the principal normal,
L cos V. - .W cos y - O
(2.190)
(2.191)
AIRCRAFT PERFORMANCE
-S = zr--J .
┏━━━━┳━━━━━━┓
┃ ┃ ┃
┃ ┣━━━━━━┫
┃WcosY / ┃w ┃
┃ 4-; ┃ ┃
┗━━━━┻━━━━━━┛
WSin y
/
\
/
--
Lsin p
// D
123
g (-)
y2cos2 Y
R
Fig. 2.26 Aircraftin turning flightin a horizontal plane.
Along the binormal,
W \/2 COS2 )
Tsinp+L.sinp,- Ly)=o (2.192)
gR
where bt, is the bank angle, p is the sideslip angle, y is the fiight path angle, and R
is the radius of turn,
The kinematic equations are
x - V cos y (2.193)
h : V sin y (2.194)
2.8.2 Turning Fkghtin a Horizontal Plane
Let us consider a steady turrung flight in horizontal plane so that y = 0. For
simplicity, let us ignore the variation of the weight because of fuel consumption
dul:ing the turn. Then, Eqs. (2.190-2.192) take the following form:
T cos p - D = O (2.195)
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PERFORMANCE, STABILITY, DYNAMICS, AND CONTROL1(71)
