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┃ ┃ ┃ ┃ ┃ ┃ ┃ ┃Ac/4 ┃ ┃
┃.(')-. = 0.4 ┃ ┃ ┃ ┃ ┃ ┃t ┃deg) ┃ ┃
┣━┳━━━━━╋━━╋━━━╋━╋━╋━╋━┫ ┣━━━━━━┫
┃ ┃ ┃ ┃ ┃ ┃ ┃ ┃ ┃o ┃ ┃
┃ ┃ ┃ ┃ ┣━╋━╋━╋━┫ ┃ ┃
┃ ┃/ ┃~- ┃----- ┃ ┃ ┃ ┃ ┃ ┃ ┃
┣━╋━━━━━╋━━╋━━━╋━╋━╋━╋━╋━━━╋━━━━━━┫
┃ ┃ ┃ ┃ ┃ ┃ ┃ ┃ ┃40 ┃ ┃
┃ ┃ ┃ ┣━━━╋━╋━╋━╋━┫ ┃ ┃
┃ ┃V7 ┃--- ┃ ┃ ┃ ┃ ┃ ┃50 ┃ ┃
┣━╋━━━━━╋━━╋━━━╋━╋━╋━╋━╋━━━╋━━━━━━┫
┃ ┃ ┃ ┃ ┃ ┃ ┃ ┃ ┃ ┃ ┃
┣━╋━━━━━╋━━╋━━━╋━╋━╋━╋━╋━━━╋━━━━━━┫
┃ ┃f(r ┃~ ┃ ┃ ┃ ┃ ┃ ┃ ┃ ┃
┃ ┃r ┃ ┃ ┃ ┃ ┃ ┃ ┃60 ┃ ┃
┣━╋━━━━━╋━━╋━━━╋━╋━╋━╋━╋━━━╋━━━━━━┫
┃ ┃ ┃ ┃ ┃ ┃ ┃ ┃ ┃ ┃ ┃
┗━┻━━━━━┻━━┻━━━┻━┻━┻━┻━┻━━━┻━━━━━━┛
NOTE: x is the distance from the c.g. to the a.c., positiye for the a.c. aft of the c.g,
c is the wing mean acrodynamic chord.
Fig.4 29b The parameter (CwlCDO)W for subsoruc speeds.7
PERFORMANCE, STABILITY, DYNAMICS, AND CONTROL
2zrt
b
- M=0.2
- - -. M-0,8
taper raUo=0.5
2bL
b
Flg.4.30 The parameter trpd at subsonic and supersmuc speeds]
0 < A < 3/5 deg. For other configurations not covered here, the reader may refer
to Datcom.
Estimation of qB and Cnp. The major contribution comes from vertical tail
and is given by
(CW)v = (Cyp)v zl COS CL - lz
b ] (4.634)
(CnB)V = -(Cyti)V lv co.S a + Zy sina
b ] (4.635)
Example 4.10
For the tailless aircraft of Examples 3.2 and 3.8, estimate the dynamic stability
parameters at subsonic and supersoruc speeds.
So/ution.
Longitudin,al dynamic stabzVity derivatives.
CLq: Because the girren wing has
the Datcoml method to evaluate the
a low aspect ratio (Ae =2.6893), we use
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