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MATLAB, 461, 488, 507
maximum auainable turn rate (MATR),
136-138
maximum sustained turn rate (MSTR),
127-128. 130-131, 135, 136, 146
Messerschmitt Me 262 jet fighter, 47
microburst, 156-158
MiG 29 aircraft, 674
MiG 31 aircraft, 674
minimum phase system, 452
minor loop compensation, 494
Mimge 2000 aircraf1, 104
Mirage III aircraft, 104, 674, 689
moment feference point, 19-21
motion equations
acceleration expressions, 362~366
aerodynanuc forces and moments, 376-384
force and, 364-372
moving axes theorem, 360-362
overview, 359-360
small disturbances and, 373-384
steadily rolling aircraft, 630-637
steady-st:Ue spin, 649-654
turning flight, 122-123
velocity expressions, 362-366
INDEX
763
vertical flight plane, 70-73
moving axes theorem, 360-362
moving wall effect, 7 t 7-721
MSTR. see maximum sustained tum rate
(MSTR)
Multhopp, H., 170-17 1
Munk, M. M., I70
N
NASNBoeing aircraft, 749
National Advisory Committee for Aeronautics
(NACA), 12-13
natural frequency of system, 448
natural response, 537-540
navigational system, 321, 334-337
neutral points in flight, 201-203, 224-228,
230, 231
Newton's laws of motion, 320, 359
rionrriininium phase systems, 452
nonterminal flight phases, 592
nonunity feedback system, 454
nose balance, 221, 22 5
nose droop, 171-172
Nyquist stability criterion, 473-478
O
oblique wings, 58-59
observability matrix, ~5 I 2-5 I 3
observer, state, 522-525
ogive cylinders, 173-17~5
open-loop system, 168. 439. 463
oscillatory motion, 462-463
oscillatory response, 448-449
Oswald's efficiency factor, 68, 390
overdamped response, 448-449
P
passive aerodynamics, 725-729
path performance, 69-70
pedal forces, 285-286. 287
performance
climbing flight, 104
overview, 67-70
types, 69-70
phase margin, 481-483, 486, 487
phase-variable form, 513-518, 520-521,
523-524, 601-603
Philips, W. H., 628, 643. 637
phugoid mode, 544-545, 547-552, 561, 593
piston engine-propeller. see propeller aircraft
pitch. 203-207
pitch damping, 698-699
pitch displacement autopilot, 612-616,
617, 622
pitch divergence, 628-630, 638
pitch rate, 249-250, 391-392, 614-615
pitch stabilization system. 596-600
pitch trim, 167-168, 203-207, 218
pitch-down, 737-739
pitch-up, 53, 735-736
764
pitching moment, 19-21, 186-193, 390,
395-396,'401-402
pitoustatic sensor, 599
point performance, 69-70
pde placement, 514, 518~520
poststall gyration, 646 .
power, 68-69
effect on stability, 277-278
leveJ flight and, 83-84
range and, 109- 110
specific excess, 100-103
stability and, 198-200, 281-283
Prandtl, 1., 2-5, 6
Prandtl-Glauert rule, 40
pressure drag, 12, 67-68
pressure gradient, 6-7
propeller aircraft
climbing.flight and, 95-97
cruise alticude, 111-113
endUfance of: 115-116
ground run, 148
level flight, 85-87
MATR, 136-137
INDEX
power effect on, 198-200
propulsive characteristics, 68
range of, 109-110
service ceiling, 100
stability and, 277-278
thrust and, 198
tuming flight of, 126-130
proportional-derivafive compensator, 490-491
proportional-integral compensator, 488-490
proportional-integral and der:ivative controller,
492-493
pull-out maneuver, 249-250
pull-up maneuver, 248-254
pulse funaion, 441-442
Q
quatemoins, 344-347
R
radar, 158, 743
range
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PERFORMANCE, STABILITY, DYNAMICS, AND CONTROL4(113)
