robert f bales interaction process analysis

... or the FtF discussion was held first. However, more saggestions were offered on the arctic problem if it was discussed in CC as ~e first problem, but more in FTF discussion if the FTF was preceeded ... term for A, B, A x B S/ABC=error term for C/AB WG=Pooled error term Table Value for F 1 and 76 df=3.97 *Significant The nested design yields a significant difference be- tween the FTF and ... Conditions. The FTF conditions show a greater percent of their comments in category 3- Agrees. REFERENCES Bales, Robert 1950 Interaction Process Analysis; A Method for the Study of Small Groups....

Ngày tải lên: 24/03/2014, 01:21

Ngày tải lên: 04/07/2014, 19:27

Ngày tải lên: 04/07/2014, 19:26

... you find this information helpful in understanding how you can make these worksheets work for you. Form Number Form Type 1.# Top level of Business Reference Model : defines the “frame of reference” ... information. Form: Business Collaboration Form ID [Provide an ID for this form so other forms can reference it (Đ5.1.8)] Identifier [This is a unique identifier that follows the Business Process ... sequence of processes that are combined to form the “value chain” of the given business area. Form: Describe Process Area Form ID [Provide an ID for this form so other forms can reference it...

Ngày tải lên: 06/03/2014, 20:21

... amplify overlapping PCR fragments of rat VRL-1 (yellow to obtain fragment A with 534 bp, green for fragment B with 656 bp, orange for fragment C with 836 b and cyan for fragment D with 633 bp). Fig. ... 4. RT-PCR of fragment A. RT-PCR with rat VRL-1 specic primer for fragment A (34568 bp ẳ 534 bp) yielded not only a product from RNA of F- 11 (F1 1) and rat brain (rb) but also of the F- 11 parental ... were made with pcDNA3.1/ rVRL-1-CT-GFP transfected F- 11 cells. Anti-GFP (Fig. 8B) and anti-VRL-1 (Fig. 8C) Western blots of F- 11 cells show an analogous pattern of the rVRL-1 glycopro- tein, when...

Ngày tải lên: 31/03/2014, 07:20

... vehicles. !  Understanding of aircraft equations of motion, configuration aerodynamics, and methods for analysis of linear and nonlinear systems. !  Appreciation of the historical context within which past aircraft ... a sound footing for the development of future aircraft. More Learning Objectives" !  Detailed evaluation of the linear and nonlinear flight characteristics of a specific aircraft type." !  ... and references at http://blackboard.princeton.edu/" Syllabus, Second Half !  Analysis of Linear Systems !  Time Response !  Root Locus Analysis of Parameter Variations !  Transfer Functions...

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 ã Functions of ight ... = v x v y v z ⎡ ⎣ ⎢ ⎢ ⎢ ⎢ ⎤ ⎦ ⎥ ⎥ ⎥ ⎥ F I = f x f y f z ⎡ ⎣ ⎢ ⎢ ⎢ ⎢ ⎤ ⎦ ⎥ ⎥ ⎥ ⎥ I = F gravity + F aerodynamics + F thrust ⎡ ⎣ ⎤ ⎦ I Rate of change of position! Rate of change of velocity! Vector of combined forces! Equations ... " q Equations of Motion for a Point Mass Newtonian Frame of Reference" ã Newtonian (Inertial) Frame of Reference" –  Unaccelerated Cartesian frame whose origin is referenced to an...

Ngày tải lên: 04/07/2014, 19:20

... doubled (F4 F vs. F8 F)! ã Use of aps means high power at low speed, increasing relative signicance of thrust effects" ã Short-Takeoff-and-Landing (STOL) aircraft augment takeoff/landing lift ... compressibility effects on drag! ã Dramatic change in stability, control, and ying qualities! ã North American FJ-1 and FJ-4 Fury! ã Republic F- 84B Thunderbird and F- 8 4F Thunderstreak! ã Grumman F9 F-2 Panther ... F9 F-6 Cougar! Toward Supersonic Flight and Stealth Fighter Jets of the 1950s! ã Emphasis on supersonic speed! Republic F- 105! Lockheed F- 104! Convair F- 102! McDonnell F- 101!North American F- 100! Fighter...

Ngày tải lên: 04/07/2014, 19:21

... page)" Interference Effects Interference Effects Wing Aerodynamics Fuselage Aerodynamics Tail Aerodynamics Interference Effects ã NASA 30 x 60 Tunnel" Full-scale aircraft on balance" –  ... Airfoil section may vary from tip-to-tip" Chord length" Airfoil thickness" Airfoil prole" Airfoil twist" ã Lift of a 3-D wing is found by integrating 2-D lift coefficients ... D y ( ) c y ( ) q dy −b/2 b / 2 ∫ Effect of Aspect Ratio on Wing Lift Slope Coefcient (Incompressible Flow)" ã Airfoil section lift coefficients and lift slopes near wingtips are lower ...

Ngày tải lên: 04/07/2014, 19:22

... Axes" f B = X B Y B Z B ! " # # # $ % & & & m B = L B M B N B ! " # # # $ % & & & Force Vector" Moment Vector" r ì 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 ... Dihedral effect" ã Vertical tail effect" Rolling Moment due to Sideslip Angle! ã Crossow effects depend on vertical location of the wing" Example of Configuration and Flap Effects! NACA ... S = C L C D Lift-Drag Polar for a Typical Bizjet" ã Lift-Drag Polar: Cross-plot of C L () vs. C D ()" Note different scaling for lift and drag! ã L/D equals slope of line drawn from the origin" – ...

Ngày tải lên: 04/07/2014, 19:22

... 0 ã Satisfy necessary condition for a maximum" ã Lift-to-drag ratio" ã Lift coefcient for maximum L/D and minimum thrust are the same" Airspeed, Drag Coefficient, and Lift-to-Drag ... V cruise C L C D ! " # $ % & 1 c T ! " # $ % & ln W i W f ! " # # $ % & & ! V cruise as fast as possible" !  ρ as small as possible" ! h as high as possible" C L MR = C D o 3 ε : Lift Coefficient for Maximum Range Maximum Range of a Jet Aircraft Flying at ... tubes on Fouga Magister" Cessna 172 pitot tube" X-15 Q Ball" Flight Testing Instrumentation" ã Air data measurement far from disturbing effects of the aircraft" z...

Ngày tải lên: 04/07/2014, 19:24

... Glide" Climbing Flight Gliding, Climbing, and Turning Flight Performance
 Robert Stengel, Aircraft Flight Dynamics, MAE 331, 2012 ! Copyright 2012 by Robert Stengel. All rights reserved. For educational ... stall" ã Flow-separation buffet" Angle of attack" –  Local shock waves" Piper Dakota Stall Buffet" http://www.youtube.com/watch?v=mCCjGAtbZ4g ! Boeing 787 Flight Envelope ... maneuver" The Flight Envelope Flight Envelope Determined by Available Thrust" ã Flight ceiling defined by available climb rate" –  Absolute: 0 ft/min" –  Service: 100 ft/min" Performance:...

Ngày tải lên: 04/07/2014, 19:25

... Measurement of Position in Alternative Frames - 1" ã Two reference frames of interest" –  I: Inertial frame (fixed to inertial space)" –  B: Body frame (xed to body)" ã Differences ... sequences of 3 rotations can be chosen; however, once sequence is chosen, it must be retained " Effects of Rotation on Vector Transformation from Inertial to Body Frame of Reference" Yaw ... 22.1ì10 6 slug-ft 2 I xz = 0.88 ì10 6 slug-ft 2 Angular Momentum of a Particle ! ã Moment of linear momentum of differential particles that make up the body" –  (Differential masses)...

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, 2012 " ã Rotating frames of reference" ã ... center of mass" Alternative Frames of Reference" ã Orthonormal transformations connect all reference frames" Next Time: Linearization and Modes of Motion   Reading Flight Dynamics, ... v B = 1 m F B + H I B g I B v B B = I B 1 M B B I B B ( ) ã Rate of change of Translational Position " ã Rate of change of Rotation Matrix " ã Rate of change of Translational...

Ngày tải lên: 04/07/2014, 19:25

... " # $ $ $ $ $ $ $ % & ' ' ' ' ' ' ' ã Four (6 x 6) blocks distinguish longitudinal and lateral-directional effects " F = F Lon F Lat−Dir Lon F Lon Lat−Dir F Lat−Dir " # $ $ % & ' ' Effects of longitudinal ... Numerically" First differences in f( x,u,w)" ã Analytically" Symbolic evaluation of analytical models of F, G, and L" F( t ) = ∂ f ∂ x x =x N (t ) u = u N (t ) w = w N (t ) G(t ) = ∂ f ∂ u x ... matrix" L(t) = f w x =x N (t ) u =u N (t ) w =w N (t ) = ∂ f 1 ∂ w 1 ∂ f 1 ∂ w 2 ∂ f 1 ∂ w s ∂ f 2 ∂ w 1 ∂ f 2 ∂ w 2 ∂ f 2 ∂ w s ∂ f n ∂ w 1 ∂ f n ∂ w 2 ∂ f n ∂ w s " # $ $ $ $ $ $ $ $ % & ' ' ' ' ' ' ' ' x...

Ngày tải lên: 04/07/2014, 19:25

... ) + L Lon Δw Lon (t ) F = ∂ f 1 ∂ V ∂ f 1 ∂γ ∂ f 1 ∂ q ∂ f 1 ∂α ∂ f 2 ∂ V ∂ f 2 ∂γ ∂ f 2 ∂ q ∂ f 2 ∂α ∂ f 3 ∂ V ∂ f 3 ∂γ ∂ f 3 ∂ q ∂ f 3 ∂α ∂ f 4 ∂ V ∂ f 4 ∂γ ∂ f 4 ∂ q ∂ f 4 ∂α $ % & & & & & & & & & & & ' ( ) ) ) ) ) ) ) ) ) ) ) G ... = ∂ f 1 ∂ V ∂ f 1 ∂γ ∂ f 1 ∂ q ∂ f 1 ∂α ∂ f 2 ∂ V ∂ f 2 ∂γ ∂ f 2 ∂ q ∂ f 2 ∂α ∂ f 3 ∂ V ∂ f 3 ∂γ ∂ f 3 ∂ q ∂ f 3 ∂α ∂ f 4 ∂ V ∂ f 4 ∂γ ∂ f 4 ∂ q ∂ f 4 ∂α $ % & & & & & & & & & & & ' ( ) ) ) ) ) ) ) ) ) ) ) G = ∂ f 1 ∂δ E ∂ f 1 ∂δ T ∂ f 1 ∂δ F ∂ f 2 ∂δ E ∂ f 2 ∂δ T ∂ f 2 ∂δ F ∂ f 3 ∂δ E ∂ f 3 ∂δ T ∂ f 3 ∂δ F ∂ f 4 ∂δ E ∂ f 4 ∂δ T ∂ f 4 ∂δ F # $ % % % % % % % % % % & ' ( ( ( ( ( ( ( ( ( ( L ... Dynamics" ∂ f 3 ∂δ E = 1 I yy C m δ E ρ V N 2 2 Sc $ % & ' ( ) ∂ f 3 ∂δ T = 1 I yy C m δ T ρ V N 2 2 Sc $ % & ' ( ) ∂ f 3 ∂δ F = 1 I yy C m δ F ρ V N 2 2 Sc $ % & ' ( ) ∂ f 3 ∂ V wind = − ∂ f 3 ∂ V ∂ f 3 ∂α wind = − ∂ f 3 ∂α ∂ f 4 ∂δ E = − ∂ f 2 ∂δ E ∂ f 4 ∂δ T = − ∂ f 2 ∂δ T ∂ f 4 ∂δ F = − ∂ f 2 ∂δ F ∂ f 4 ∂ V wind = ∂ f 2 ∂ V ∂ f 3 ∂α wind = ∂ f 2 ∂α ...

Ngày tải lên: 04/07/2014, 19:26

... Stability-and-Control Derivatives" ∂ f 1 ∂ v ∂ f 1 ∂ p ∂ f 1 ∂ r ∂ f 1 ∂φ ∂ f 2 ∂ v ∂ f 2 ∂ p ∂ f 2 ∂ r ∂ f 2 ∂φ ∂ f 3 ∂ v ∂ f 3 ∂ p ∂ f 3 ∂ r ∂ f 3 ∂φ ∂ f 4 ∂ v ∂ f 4 ∂ p ∂ f 4 ∂ r ∂ f 4 ∂φ # $ % % % % % & ' ( ( ( ( ( Stability ... top! Dutch Roll, front! Why Modify the Equations?" F LD = F DR F RS DR F DR RS F RS ! " # # $ % & & = F DR small small F RS ! " # # $ % & & ≈ F DR 0 0 F RS ! " # # $ % & & Effects ... Δ  v(t) Δ  p(t) Δ  r(t) Δ  φ (t) # $ % % % % % & ' ( ( ( ( ( = ∂ f 1 ∂ v ∂ f 1 ∂ p ∂ f 1 ∂ r ∂ f 1 ∂φ ∂ f 2 ∂ v ∂ f 2 ∂ p ∂ f 2 ∂ r ∂ f 2 ∂φ ∂ f 3 ∂ v ∂ f 3 ∂ p ∂ f 3 ∂ r ∂ f 3 ∂φ ∂ f 4 ∂ v ∂ f 4 ∂ p ∂ f 4 ∂ r ∂ f 4 ∂φ # $ % % % % % % % % % % % & ' ( ( ( ( ( ( ( ( ( ( ( Δv(t) Δp(t) Δr(t) Δ φ (t) # $ % % % % % & ' ( ( ( ( ( +...

Ngày tải lên: 04/07/2014, 19:26

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Ngày tải lên: 04/07/2014, 19:28

Ngày tải lên: 04/07/2014, 19:28