- Mislim da se apsolutno uklapa u temu. Savremeni aerodizajn, primenjena dokazana aerodinnamička rešenja su
TEMELJ svakog daljeg koraka u avioindstriji, bilo civilnoj ili vojnoj ! Postaviću link gde magistar nauka ulazi u srž aerodizajna, svestranom pristupu konstrukcije aviona kako sa zapada, sa šematskim prikazima opstrujavanja oko različitih avio profila itd. U punom smislu prikazan osnov-temelj aerodinamike i aerodizajna g-na Ray Whitford C.Eng MRAeS. Svima koji vole i prate primenjeni avio dizajn i aero inženjering savetujem da pročitaju ovu elektronsku knjigu dostupnu za skidanje u PDF formatu Janes - editiion. Mada je bogat tekst na engleskom, puno šematsskih i slikovnih prikaza puno toga objašnjavaju u oblasti aerodimike. U istom linku je i više svrsishodnih linkova koji tretiraju istu tematiku.
1.
http://scilib.narod.ru/Avia/DAC/index.html - Avio rečnik, da ga nazovem "shortcut" najčešće korišćenih avio-inženjering a i generalno trermina :
- A, AH aspect ratio, b2/S,
A nozzle area,
AB afterburner, reheat,
AC aerodynamic centre,
ACT active control technology,
AFCS automatic flight control system,
AGARD Advisory Group for Aeronautical Research and Development,
AIAA American Institute of Aeronautics and Astronautics,
AOA angle of attack,
ARI aileron/rudder interconnect,
ASW aft-swept wing,
a lift curve slope, dCL/dα,
a speed of sound,
BAe British Aerospace,
BLC boundary-layer control,
BPR bypass ratio,
b wing span, tip to tip,
CASJ Canadian Aeronautics and Space Journal,
CCV control-configured vehicle,
CD drag coefficient,
CDv vortex drag coefficient,
CDmin minimum drag coefficient,
CD0 zero-lift drag coefficient,
CDw wave drag coefficient,
CG centre of gravity,
CLma - maximum lift coefficient,
CP centre of pressure,
Cp pressure coefficients,
Ct tip chord length,
cr root chord length,
c wing chord length,
c mean geometric chord,
c mean aerodynamic chord,
D drag,
D0 zero-lift drag,
DLC direct lift control,
EAP Experimental Aircraft Programme (BAe),
ECM electronic countermeasures,
FBW fly-by-wire,
FSW forward-swept wing,
g gravitational acceleration,
H0 stagnation pressure,
h altitude,
ICAS International Council for Aeronautical Sciences,
IR infra-red,
Ix moment of inertia about rolling axis,
Iz moment of inertia about yawing axis,
KIAS knots indicated airspeed,
L rolling moment,
L total lift on aircraft,
LF foreplane lift,
Lw wing lift,
LT tail lift,
L/D lift-to-drag ratio,
LE leading edge,
LEX leading-edge extension,
LERX leading-edge root extension,
lF vertical tail moment arm length,
lT horizontal tail moment arm length,
M pitching moment,
M Mach number,
Mcrit critical Mach number,
MD drag-rise Mach number,
INM increment in Mach number,
MAC mean aerodynamic chord,
MBB Messerschmitt-Bolkow-Blohm GMBH,
dm/dt mass flow rate,
N yawing moment,
NACA National Advisory Committee for Aeronautics,
NASA National Aeronautics and Space Administration,
NP neutral point,
n Normal acceleration (in units of g) = normal load factor – 1,
PACT Precision Aircraft Control Technology,
p rate of roll,
p static pressure,
pb static back pressure,
pe static exit pressure,
pr total pressure recovery,
pt throat pressure,
p0 stagnation, total pressure,
q dynamic pressure,
qv dynamic pressure at vertical tail,
Re Reynolds number,
RAE Royal Aircraft Establishment.
RAeS Royal Aeronautical Society,
RoC rate of climb,
R&D research and development,
RMS root mean square,
RSS relaxed static stability,
S,Sw wing area,
SAFE Safety and Flight Equipment Manufacturers Association,
SF vertical tail area,
ST tailplane area,
SEP specific excess power,
SF shear force,
SFC specific fuel consumption,
SM static margin,
s stagnation point,
s wing semi-span,
T propulsive thrust,
T torque,
TE trailing-edge,
TFX Tactical Fighter Experimental,
TOD take-off distance,
T/W thrust/weight ratio,
t thickness,
t/c thickness/chord ratio,
u velocity parallel to surface in boundary layer,
V velocity,
VFE variable-flap ejector nozzle,
VIFF vectoring in forward flight,
Vs1 stall velocity in 1g flight
VTOL vertical take-off and landing,
v increment in velocity,
W weight of aircraft,
W/b span loading,
W/S wing loading
x distance from leading edge measured along chord line,
x/c fraction of chord length,
Y sideforce,
y distance measured normal from surface in boundary layer,
α angle of attack,
α0 angle of attack for zero lift,
Cn circulation ... and ETC.