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   see also wings
airplane response, 537
  see abo lareral-directional response;
          longitudinal response
altitude, 108, 109, 1{0, 111-113
altitude-hold autopilor, 616-622
angle of attack
   definition, 2
    roll angle and, 695, 696
   sideslip and, 695, 696
    wing rock and, 695-710
     see also high angles of attack
Angla-French Concorde, 55, 208
angular momentum, 368~372
area ruling, 59-60
aspect ratio, 45, 46, 299-304
asymmetric power, 281, 283
759
asymmetr:ic stall, 646
asymptotes, 470
attached flow, 676
Index
 autopilots, 563, 588, 595, 61 J -622
autorotation characteriscics, 640-645
autothrottle, 157
axes systems
    body axes, 321-322, 328-330, 336-337
    Earth fixed, 321-322
   inertial, 320, 326-328
    nayigational, 321, 334-337
   overview, 320
axes transformation
    direction cosine matrix, 337-344
      Euler an. gles,  322-337
   quatemoins, 344-347
B
B*,l aircraft, 50, 60, 106
 B-52 aircraft, 106, 234
 balanced field length, 151
bank angle, 124, 570, 572
BemouIJi's theOfem. 6
Bode plot, 483
body axes system, 321-322. 328-330,
 336-337
Boeing 707 aircraft, 234
Boeing 747 aircraft, 60, 106
Boeing 747-400 aircraft, 32
Boeing 757 aircrafi, 34
boundary layer, 42, 53
    circular cylindef fluid flow and, 7-li
    control of, 26
    fluid flow and, 2-7
Breguet range formula, 109, 113
Bryan, G. H., 319, 376
buffeting, 42, 674
Busemann's supersonic swept-wing
           theory, 47
C
C-I40 JetStar airCfafi, 26
canard aircraft, 174, 205, 689
canard deflector, 689-690
center of gravity
     effect on longitudinaJ response, 555-556
    elevator deflection and, 213
     most forwafd location of, 213-2 ! 4
    permissible, 214-215
     shift in, 208
    stability and, 201-203
    stick-free margin. 228
chordline, 12- 13, 17, 20
760
INDEX
circular cylinder
     drag af bodies and, 12
    fluid velocity and, 2-3, 7-11
    pressure disrribution over, 9-10
circulation control, 26
climbing flight
    absolute ceiling, 99-100
    aircraft performance, 104    .
   energy climb method, 100-104
    jet aircraft, 97-99, 101-102
    propeller aircraft, 95-97
    service ceiling, 99-100
    steady climb, 94-99
    subsonic aircraft, 102
    supersonic aircraft, 102~104
close-coupled canards, 689
closed-loop systems, 439, 537          '
     autopilots, 563, 588, 595, 611-622
     full-state feedback, 599-604, 607-611
    gain margin, 481-483
    Nyquist srability cn:terion, 473-478
     overview, 595-596
     phase margin, 481-483
    pitch stabilization, 596-600
     root-locus method, 467-470
    Routh's stability criterion, 463-465
     stability of, 461-465
     yaw damper, 604-607
Coanda effect, 725
combat aircraft, 136-137
compensators
     design, 487-488
     lead/lag, 492
     overview, 486-488
    proportional-derivative, 490-491
     proportional-integral, 488-490
compressibility, 19, 45-59
computational fluid dynamics (CFD), 389-390
cone-cylinders, 173-174
coning motion, I39
constant ampWude sinusoid, 448
constant-alritude flight, 113, t 15-116
 constant-velocity flighr,  I J 0,  113,  115-116
 controllability matrix, 5 12
controller, proportional-integral and derivative,
492-493
Convair B-58 aircraft, 60
Convair F- 102 aircraft, 59-60
Convair F-I06 aircraft, 60
　
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