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316 PERFORMANCE, STABILITY, DYNAMICS, AND CONTROL
Chb - - 0.006/deg, Se - 1.85 m2, Ce =0.61 m, and Gi - 1.2 rad/m. [Answer:
(a) 9793.4 m, (b) -7.3597 degtg, and (c) -73.4937 N/g.]
3.19 An aircraft weighs 66,825 N and has a wing area of46 m2 and a taillength
of 10.64 m. The center of gravity and wing aerodynamic centers in ternris of mean
aerodynamic chord.are, respectively, at 0.35 and 0.26 from the leading edge of
mac. The lift-curve slope of wing and that of horizontal tail are 0.09/deg and
0.07/deg, respectively. The tail volume ratio is 0.6. Assuming Cm f = O-lCL, € ;
0.3cc, r7, - 0.9, r = 0.5, Chu = -0.003/deg, Ch8 = -0.006/deg, Se = 1.9 IT12,
Ce - 0.55 m, and G } = 1.2 ratVm, determine (a) the stick-fixed maneuver margin
and (b) the increment.al elevator'setting for a coordinated tum with 30 deg bank
at an altitude of 2200 m (u : 0.8). (c) What is the stick force per g? IAnswer:
(a) 0.2402, (b) -0.3932 deg, and (c) 69.0167 N/gJ
3.20 For the airplane configuration shown in Fig. P3.20, the fuselage side area
is 40.5 m2, the maximum fuselage width is 2.5 m, and the ratio of rudder chord
to vertical tail chord is 0.30. The rudder extends from 1.56 to 3.78 m from the
fuselage centerline as shown. Assume that the wing, horizontal tail, and vertical
tail h"a"~Ue NACA 65A006 airfoil section. Determine the following:
(a) The static directional stability parameter (Cnp)rix at M = 0.3 and an altitude
of 3000 m and at M - 2.0 and an altitude of 15,000 m.
(b) The rudder effectiveness Cnbr at low subsonic speeds.
(c) The rudderlunge-moment coefficients Chp and Chlr atlow subsonic speeds,
assuming that the hingeline coincides with the leading edge of the rudder.
(d) The rudder-free directional stability parameter (CnpX at M =0.3.
STATIC STABILITY AND CONTROL
* NACA 65A006 Airtoil.or Wing,
Horizontal & Vertical Tails.
' S8.S = 40-5 mz
~ bt.,ai= 2-Sm, cy : 0-3Cv.
' yi = 1*56m, yo : 3--l8m
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