曝光台 注意防骗
网曝天猫店富美金盛家居专营店坑蒙拐骗欺诈消费者
Israel Lavi, 674, 689
J
jet aircraft
climbing flight, 97-99, 101-102
cruise altitude, J II-I I3
endurance of, I 14-t 15
ground run, 148
Ievel flight, 85, 87-90
power effects on, 200
range, 107-109
service ceiling, 100
stability and, 278 .
turning performance, 130-134
K
Karm5n vortices, 7-1 J, 692, 719
KC135 aerial-tanker aircraft, 31
INDEX
L
laminar flow, 9-t 1, 12, 719-720
landing
crosswinds and, 281-282
hazards during, 156-158
sequences of, l52-t53
Laptace transform, 440-446
lateral control departure parameter (LCDP),
732-735
lateral stability
control, 304-309
elemenrs of, 294-295
evaluation of, 295-304
overview, 293-294
lateral-directional response
approximatians, 572-577
frequency response, 588-591
overview, 564-572
transfer functions, 577-588
latend-directional stability augmentation
system, 607-611
LCDP. see Iatexal control departure parameter
(LCDP)
Iead/lag compensator, 492
Ieading edges. 23. 47-49
corrcction factor, 178, 182-183
shapes, 219-220
wings, I71-I73
Ieading-edge extensions (LEX), 674, 686-690
level flighi, 81-94, 230-235
LEX..ue Ieading-edge extensions (LEX)
Lidar devices, 158
Iift, 6, I 7-19, 42-43, 2 t I
lift-curve slope, l73-t 86, 390. 396
liRing line theory, 26-31
lifting surface theories, 26-31
limit cycle oscillation, 705
linear systems
Laplace r.ransform, 440-445
overview, 439
Ioad factor. 126, 129-130, 133-134, 248-256
loiter, 106-107
Jongicudinal control, 206-213
longitudinal response
frequency response. 562-564
overview, 537-545
short period approxinwian, 545-547
static stability effect on, 551-. 557
transfer function and. 557-562
longitudinal stability, 630
aerodynamic balancing, 219-224
analysis of, 200-201
ccrUer of gravity and, 213-215
fuselage conmibution to, 169-173
ground effecrs of, 215, 2J 6, 217
longitudinal control, 206-213
neutral points in flight. 230, 231
power effect on, t98-200
stick force in, 230-235
stick-fixed neutral poim, 20J-203, 230
sOck-free, 215-218
stick-free margin, 228
stick-free neutral point and, 224-228, 230,
231
tail and, 194-198
tail lift, 203-207
trim tab, 228-230
wing and, 173-183 '
wing-fuselage and, 183-193
longitudinal stability derivatives, estimation of,
390-403
M
Mach cone. 36-37, 39, 47, 54
Mach numbers
compressibility delay effects, 45-59
definition, ;1-2
freestream, 40-45
vortex breakdown and, 685-686
Mach wedge, 36
magnitude crossover frequency, 590
Magnus effect, 717-719
major-loop compensation, 493-494
Maneuver Technology Demonstrator, 674
maneuvers
coning morion, 139
horizontal plane, 254-256
pitch-down, 737-739
pitch-up, 735-736
pull-out, 249-250
pull-up, 248-254
rolling, 628-637
stability in, 248-256
stick force gradient, 253-254
stick-fixed, 251
stick-free, 252-253
mapping, 473-478 .
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PERFORMANCE, STABILITY, DYNAMICS, AND CONTROL4(112)
