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Cooper-Harper scale, 591
corner velocity turn, 138~139, 146
critical Mach number, 40-45
criLical speed, l50
critically damped, 448-449
crosswinds
    Janding and, 281-282
    takeoff and, 150, 281-282, 297
cruise altitude, 109, lll-t I3
cruise climb, 109, 113-114
cruise flight, 616
cruise range, 106
E
damped frequency, 448
damped oscillation, 462, 541, 544-547
damping ratio, 448-449, 486, 487
damping-in-pitch derivatrve, 395
damping-in-roll, 407
damping-in-yaw, 697
Data Compendium (Datcom), 168
delta wings, 54-55, 676-686
    free-tO-foll, 700-701, 711
    leading-edge extensions, 686-690
    roll attractor, 710-713
    sideslip and, 710
    stall and, 678-686
    voncx breakdown and, 678-686, 708-710
    wing rock, 695-710
derivatives
    estimation of, 389-390
    Weral-directional, 404-420
     longitudinal acceleration, 398-403
     longitudinal rotary, 391~398
     longitudinal stability, 390-403
dihedral effect, 261-266, 293-297, 305
Dirac delta function, 442-443
direction cosines, 337-344, 339-340
directional stability        .
     control of, 279-285
    evaluation of, 261-277
    nose shape and, 693-694
         overview,  25 8-260
     pedal forces, 285-286, 287
     power effect on, 277-278
     reqrnrements fOf, 260
     rudder lock, 286-287
     rudder-fixed, 279
    rudder-firee, 283-285
disturbed motion, 372-384, 630
     aerodynamic forces and, 376-384
    lateral-directional equations of, 383-384
    longitudinal equations of, 379-383
    longitudinal response and, 570-571
    see aLvo motion equations
 diverging oscillation, 54 I
dorsal fin, 287       .
downstream obstacle, 684-685
downwash, 173, 194-198
drag, 6, 11-12, 17-19, 42-46, 50-51
Durch roll, 568-569, 573-576, 586-588,
            590-594, 604-607
E
Earth
     fixed axes system, 321- 322, 326
    navigaoonal system and, 321, 327,
334-336
   as reference, 320
eigenvalues, 510-5 12, 542-553
efgenvectors, 5 10-5 f 2
elevator control, 208-219
elevator deflection, 252
end plates, 31, 33
endurance, 106-107
   definition, 114
   jet aircraft, 114-t15
     propeller aircraft, 115-116
energy height, 100-104
equilibrium, 165-168
equivalent linear system, 440
Ericson, L. E., 717-721, 723-725
Euler angles, 322-337, 339-340, 344-357
European Fighter Aircraft, 674, 689
excess thrust, 102-103
expansion comer, 37-38
expansion wave, 37
exponential decay, 448, 462
exponential divergence, 462
F
F-4 aircraft, 104
F-5 aircraft, 696, 697
F-8 Crusader aircrafr, 59, 734
 F- t4 aurcraft, 50,  104
F-I5 aircraft, 104,  l26, 674. 684          '
F-I5 STOL aircraft, 674
F- t6 aircrafr,  104,  126, 674, 689, 739,
744-747
F-I6XL aircraft, 677
F-I02 aircraft, 60, 734
F-I04 :rircraft, 673
F-I05 aircraft, 673               .
F-I06 aircraft. 677, 734
F-I J I aircraft, 50, 104
F/A-I8 aircraft, 674. 684, 689, 749 '
Fairey Delta aircrafi, 627-628
FAR Part 23, 663
Federal Aviation Administration (FAA),
              157, 646
feedback
      compensation, 493-494          .
     nonunity feedback system, 454
     pitch rate, 613-615
        roll  rate, 73 I
     systems. 599-604, 607-6t1, 638
 fighter aircraft, 126
 finite wings, 26-31, 39, 52, 68
 first-order systems, 446-447, 452
 fixed axes system, 321-322, 326
　
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