Dynamics cheat sheet

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$my Latex and Tex4ht cheat sheet$

http://www.youtube.com/watch?v=8uT55aei1NI http://www.youtube.com/user/DAMSQAZ?feature=watch A=area of wing D=density of air V=wind speed relative to wing 116
zero-lift angle The angle of attack at which an airfoil does not produce any lift. Its value is generally less than zero unless the airfoil is symmetrical. This from Foundations of aerodynamics, 5 th ed. By Chow and Kuethe http://www.answers.com/topic/zero-lift-angle These are from text :foundation of aerodynamics by Kuethe and Chow 1. the center of pressure is at ¼ chord for all values of lift coeff. 2. center of pressure (c.p.) of a force is defined as the point about which the moment vanishes. 3. The geometric angle of attack is defined as the angle between the flight path and the chord line of the airfoil. When the geometric angle of attack is zero, the lift coeff. Is zero. 4. The point about which the moment coeff. Is independent of the angle of attack is called the aerodynamic center of the section. (a.c.) 5. a.c. is at the ¼ chord line point. 6. The value of the angle of attack that makes the lift coeff. Zero is called the angle of zero lift (Z.L.L.) There are from Foundations of aerodynamics, 5 th ed. By Chow and Kuethe 19.5 Some strange shaped airplanes Image http://edition.cnn.com/2014/01/16/travel/inside-airbus-beluga/index.html?hpt=ibu_c2 117
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Dynamics cheat sheet Nasser M. Abba
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18.7.2 Bi-Elliptic transfer orbit .
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are the natural frequencies of the
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Similarly, µ 2 is found ⎧ ⎫T
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Or in full form and ⎧ ⎫ ⎡ ⎨
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Hence The first eigen vector is Sim
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The transformation from modal coord
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Where F n = 2 T F 0 = 2 T ∫ T 0
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Let z = Re { Ze iωt} , z ′ = Re
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Now, u = Re { Ue iωt} , u ′ = Re
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Hence at t = 0 the phase of the res
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The following table gives the solut
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5.3 no loading (free) mu ′′ + c
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5.5 Impulse sin function Input is g
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Solution to single degree of freedo
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7 Some common formulas These defini
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8 Derivation of the solutions of th
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8.2.2 under-damped ζ < 1 The gener
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When ϖ ≈ ω but less than ω, le
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Hence the full solution is u p = p
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8.4 Response to impulsive loading 8
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where A = B = F 0 m 2ω √ ξ 2
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where ∆ is very small positive qu
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at t = t 1 ˙u (t 1 ) = −ξωe
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8.5 references 1. Vibration analysi
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11 Formulas sin 2 x 1cos2x 2 cos 2
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12 Velocity and acceleration diagra
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12.3 spring pendulum with block mov
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13 Velocity and acceleration of rig
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14.2 3D Not Using vehicle dynamics
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14.2.2 Derivation for τ = Iω in 3
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15 Wheel spinning precession x Mg
Page 65 and 66: 18 Astrodynamics 18.1 Ellipse main
Page 67 and 68: magnitude of ⃗r period T mean sat
Page 69 and 70: 18.3 Flight path angle for ellipse
Page 71 and 72: This diagram below from Orbital mec
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Page 75 and 76: 18.7.3 semi-tangential elliptical t
Page 77 and 78: 18.8.1 Rocket equation with plane c
Page 79 and 80: 18.10 interplanetary transfer orbit
Page 81 and 82: 2. Find speed of second planet V 2
Page 83 and 84: 1 mu = 324859; 2 alt = 1475.776; 3
Page 85 and 86: 18.11.3 Two satellite, separate orb
Page 87 and 88: 1 TOF:=hohmann_rendezvous_2(theta=0
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Page 91 and 92: 18.14 Orbit changing by low contiuo
Page 93 and 94: C r below is the core chord of the
Page 95 and 96: 1 C L = ∂C L ∂α α = C Lα α
Page 97 and 98: 1 2 3 C Lwb = ∂C L wb ∂α wb α
Page 99 and 100: 2. stall from http://en.wikipedia.o
Page 101 and 102: http://en.wikipedia.org/wiki/Flight
Page 103 and 104: http://www.grc.nasa.gov/WWW/k-12/UE
Page 105 and 106: http://en.wikipedia.org/wiki/Lift_c
Page 107 and 108: http://adamone.rchomepage.com/cg_ca
Page 109 and 110: From http://www.solar-city.net/2010
Page 111 and 112: Page 184, flight dynamics principle
Page 113 and 114: Image from http://www.americanflyer
Page 115: From FAA pilot’s handbook I do no
Page 119: Image from http://www.aerospaceweb.
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Dynamics cheat sheet

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