NAVWEPS OO-BOT-BO
TABLE OF CONTENTS
Landing performance.. . . . . 192
Forces acting on the airplane
Accclanted motion
Factors of technique
Factors affecting landing performance. . . . 196
E&t of gross weight
Effect of wind
Fg; ~~~~~~~;mpcntwc
ro a
Impmtance of handbook performance data. . . 200
CHAPTER 3. HIGH SPEED AERODYNAMICS
GENERAL CONCEPTS AND SUPERSONIC FLOW PATTERNS
NATURE OF COMPRESSIBILITY. ...............................
Definition of Mach number. ........................................
Sttbsonic, traasonic, supersonic, and hypersonic flight regimes. .......
Compressible flow conditions .......................................
Comparison of compressible and incompressible flow. ...............
TYPICAL SUPERSONIC FLOW PATTERNS., ..................
Obliqueshockwave ................................................
Normalshockwave ................................................
Ex nsionwave
E t9”
....................................................
ect on velocity, Mach number, density, pressure, energy. .. : ........
SECTIONS IN SUPERSONIC FLOW. ............................
nowpatterns ......................................................
Pressure distribution. ..............................................
Wavedrag .........................................................
Location of aerodynamic center. ....................................
21s
21s
CONFIGURATION EFFECTS
TRANSONIC AND SUPERSONIC FLIGHT. . 215
Critical Mach ntlm~r 2 15
Shock wave formatton. . . . . . . . . . . . . 218
Shock induced separation.. i..
Porcedivergence...................................................
$2:
Phenomena of transonic flight.. . 218
Phenomena of supersonic Bight.. . 220
TRANSONIC AND SUPERSONIC CONFIGURATIONS. 220
Airfoil sections.. . 220
Transonic sections
Supctsonic sections
Wave drag characteristics
Effect of Mach number on airfoil characteristics
Plaaform effects. ,.......,..... 226
Effect of swcc ack
p” Advantages o swcepback
Disadvantages of sweepback
Effect of nspct ratio and tip shape
Control surfaces. . . . . . . . . . 236
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