Aircraft Flight Dynamics Robert F Stengel Lecture5 Configuration Aerodynamics 2

... Axes" f B = X B Y B Z B ! " # # # $ % & & & m B = L B M B N B ! " # # # $ % & & & Force Vector" Moment Vector" r × f = i j k x y z f x f y f z = yf z − zf y ( ) i + zf x − xf z ( ) j + xf y − yf x ( ) k m = yf z − zf y ( ) zf x − xf z ( ) xf y − yf x ( ) # $ % % % % & ' ( ( ( ( =  rf ... = Surface ∫ L B M B N B " # $...

Ngày tải lên: 04/07/2014, 19:22

... page)" Interference Effects Interference Effects Wing Aerodynamics Fuselage Aerodynamics Tail Aerodynamics Interference Effects •  NASA 30 x 60 Tunnel" –  Full-scale aircraft on balance" –  ... Configuration Aerodynamics - 1 
 Robert Stengel, Aircraft Flight Dynamics, MAE 331, 20 12 ! •  Configuration Variables" •  Lift" –  Effects of shape, angle...

Ngày tải lên: 04/07/2014, 19:22

... C m α ,C m q ,C m  α ,C l o ,C n o ,C n β ,C n r ,C n  β Configuration and Power Effects on Flight Stability 
 Robert Stengel, Aircraft Flight Dynamics, MAE 331, 20 12& quot; •  Wing design" •  Empennage design" •  Aerodynamic coefficient estimation ... Power Effects" Copyright 20 12 by Robert Stengel. All rights reserved. For educational use only.! http://ww...

Ngày tải lên: 04/07/2014, 19:31

... = x 1 ∫ dt x 2 ∫ dt x 3 ∫ dt ⎡ ⎣ ⎢ ⎢ ⎢ ⎢ ⎢ ⎤ ⎦ ⎥ ⎥ ⎥ ⎥ ⎥ Aircraft Flight Dynamics Robert Stengel, Princeton University, 20 12& quot; Copyright 20 12 by Robert Stengel. All rights reserved. For educational ... only.! http://www.princeton.edu/ ~stengel/ MAE331.html! !  Dynamics & Control of Atmospheric Flight !  Configuration Aerodynamics !  Aircraft Performance ! ...

Ngày tải lên: 04/07/2014, 19:19

... Frame" C X C Y C Z ⎡ ⎣ ⎢ ⎢ ⎢ ⎤ ⎦ ⎥ ⎥ ⎥ B = axial force coefficient side force coefficient normal force coefficient ⎡ ⎣ ⎢ ⎢ ⎢ ⎤ ⎦ ⎥ ⎥ ⎥ C D C Y C L ⎡ ⎣ ⎢ ⎢ ⎢ ⎤ ⎦ ⎥ ⎥ ⎥ = drag coefficient side force coefficient lift coefficient ⎡ ⎣ ⎢ ⎢ ⎢ ⎤ ⎦ ⎥ ⎥ ⎥ •  ... = v x v y v z ⎡ ⎣ ⎢ ⎢ ⎢ ⎢ ⎤ ⎦ ⎥ ⎥ ⎥ ⎥ F I = f x f y f z ⎡ ⎣ ⎢ ⎢ ⎢ ⎢ ⎤ ⎦ ⎥ ⎥ ⎥ ⎥ I = F gravity + F aerodynamics + F thrust...

Ngày tải lên: 04/07/2014, 19:20

... metres (3,8 92 sq!ft) 3,501!sq!ft ( 325 m 2 ) Tail height 42 ft 5 in ( 12. 93 m) 16.85!metres (55!ft!3!in) 55!ft!6!in (16.9 m) Fuselage width 12! ft 4 in (3.76 m) 5.64!metres (18!ft!6!in) 18!ft!11!in ... to 1990
 Robert Stengel, Aircraft Flight Dynamics, MAE 331, 20 12& quot; Copyright 20 12 by Robert Stengel. All rights reserved. For educational use only.! http://www.princ...

Ngày tải lên: 04/07/2014, 19:21

... Cruising Flight Performance
 Robert Stengel, Aircraft Flight Dynamics, MAE 331, 20 12! Copyright 20 12 by Robert Stengel. All rights reserved. For educational use only.! http://www.princeton.edu/ ~stengel/ MAE331.html! http://www.princeton.edu/ ~stengel/ FlightDynamics.html! •  ... C L MT L D = C L C D = C L C D o + ε C L 2 ∂ C L C D ( ) ∂ C L = 1 C D o + ε C L 2 − 2 ε...

Ngày tải lên: 04/07/2014, 19:24

... Performance
 Robert Stengel, Aircraft Flight Dynamics, MAE 331, 20 12 ! Copyright 20 12 by Robert Stengel. All rights reserved. For educational use only.! http://www.princeton.edu/ ~stengel/ MAE331.html ! http://www.princeton.edu/ ~stengel/ FlightDynamics.html ! •  ... #5, 20 08)" Best Cruise Region" Gliding Flight D = C D 1 2 ρ V 2 S = −W sin γ C L 1 2...

Ngày tải lên: 04/07/2014, 19:25

... XB-70! Nominal Configuration Tips folded, 50% fuel, W = 38, 524 lb x cm @0 .21 8 c I xx = 1.8 ×10 6 slug-ft 2 I yy = 19.9 ×10 6 slug-ft 2 I xx = 22 .1×10 6 slug-ft 2 I xz = −0.88 ×10 6 slug-ft 2 Angular ... a set of principal axes" Ellipsoid of Inertia! € I xx x 2 + I yy y 2 + I zz z 2 = 1 Inertia Matrix of an Aircraft with Mirror Symmetry" I = (y 2 + z...

Ngày tải lên: 04/07/2014, 19:25

... sin γ ! " # # # $ % & & & Relationship of Inertial Axes to Velocity Axes" Aircraft Equations of Motion - 2 Robert Stengel, Aircraft Flight Dynamics, MAE 331, 20 12 " •  Rotating frames of reference" •  ... of Reference" •  Orthonormal transformations connect all reference frames" Next Time: Linearization and Modes of Motion   Reading...

Ngày tải lên: 04/07/2014, 19:25