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Aerospace Engineering Blog

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The science and engineering behind aeroplanes, rockets and everything aerospace.

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235

Image source: /wp-content/uploads/2012/08/f-_0001_AE-logo-c1-e1345058764349.png
Alternative text: Aerospace Engineering Blog
Image source: /wp-content/uploads/2017/07/Wing-spars.jpg
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Image source: /wp-content/uploads/2017/06/fokker-d-vii-1184x772-1024x668.jpg
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Image source: /wp-content/uploads/2017/06/4g_Spar_Stress-002-1024x531-1024x531.gif
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Image source: /wp-content/uploads/2017/06/fokker-d-vii-front-1024x680-1024x680.jpg
Alternative text: Not defined!
Image source: /latex.php
Alternative text: C_L
Image source: /latex.php
Alternative text: C_{L_\alpha} = 0.095/^\circ
Image source: /latex.php
Alternative text: -8^\circ
Image source: /wp-content/uploads/2017/06/1.-fokker-dvii-airfoil.png
Alternative text: Not defined!
Image source: /wp-content/uploads/2017/06/2.-c1-vs-aoa.png
Alternative text: Not defined!
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Alternative text: 1^\circ
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Alternative text: 0^\circ
Image source: /latex.php
Alternative text: C_{L,upper} = C_{L_\alpha} \left( \frac{AR}{AR+2} \right) \left( \alpha - \alpha_{0L} \right) = 0.095 \left( \frac{5.14}{5.14+2} \right) \left( 0-(-8)\right) = 0.55
Image source: /latex.php
Alternative text: C_{L,lower} = C_{L_\alpha} \left( \frac{AR}{AR+2} \right) \left( \alpha - \alpha_{0L} \right) = 0.095 \left( \frac{5.67}{5.67+2} \right) \left( 1-(-8)\right) = 0.63
Image source: /latex.php
Alternative text: L_{upper} = qS_{upper}C_{L,upper} = (0.277\ psi)(20,418.3\ in^2)(0.55) = 3,110.73\ lb
Image source: /latex.php
Alternative text: L_{lower} = qS_{lower}C_{L,lower} = (0.277\ psi)(12,630.72\ in^2)(0.63) = 2,204.19\ lb
Image source: /latex.php
Alternative text: S
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Alternative text: q = 1/2 \rho V^2
Image source: /latex.php
Alternative text: \rho
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Alternative text: V
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Alternative text: F_{tail}
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Alternative text: x
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Alternative text: F_{tail} = \frac{L_{lower} x_{lower} - L_{upper} x_{upper}}{x_{tail}} = \frac{3110.73 \times 11.60 - 2239.17 \times 10.41}{190.12} = 79.40\ lb
Image source: /latex.php
Alternative text: 3,110.73+2,204.19+79.40 = 5,394.32
Image source: /latex.php
Alternative text: L_{upper} = 2,894.41
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Alternative text: L_{lower} = 2,078.78
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Alternative text: F_{tail} = 62.81
Image source: /latex.php
Alternative text: \Delta C_{L,upper}
Image source: /latex.php
Alternative text: \Delta C_{L,lower}
Image source: /latex.php
Alternative text: \Delta C_{L}
Image source: /latex.php
Alternative text: C_{L}
Image source: /latex.php
Alternative text: \Delta C_{L,upper} = K_1 + K_2 C_L
Image source: /latex.php
Alternative text: K_1
Image source: /latex.php
Alternative text: K_2
Image source: /latex.php
Alternative text: \Delta C_{L,lower} = -\Delta C_{L,upper} \frac{S_{upper}}{S_{lower}}
Image source: /latex.php
Alternative text: K_1
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Alternative text: K_2
Image source: /latex.php
Alternative text: K_1 = -0.090
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Alternative text: K_2 = 0.195
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Alternative text: C_L = \frac{nW}{0.5 \rho V^2 S} = \frac{nW}{qS} = \frac{4 \times 1259}{0.277 \times 33049} = 0.55
Image source: /latex.php
Alternative text: K_1
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Alternative text: K_2
Image source: /latex.php
Alternative text: C_L
Image source: /latex.php
Alternative text: \Delta C_{L,upper}
Image source: /latex.php
Alternative text: \Delta C_{L,lower}
Image source: /latex.php
Alternative text: \Delta C_{L,upper} = 0.015
Image source: /latex.php
Alternative text: \Delta C_{L,lower} = -0.025
Image source: /latex.php
Alternative text: C_{L,upper} = C_L + \Delta C_{L,upper}
Image source: /latex.php
Alternative text: C_{L,lower} = C_L + \Delta C_{L,lower}
Image source: /latex.php
Alternative text: L_{upper} = 3,139.88
Image source: /latex.php
Alternative text: L_{lower} = 1,803.24
Image source: /latex.php
Alternative text: F_{tail} = 92.87
Image source: /wp-content/uploads/2017/06/04.-spanwise-lift-distribution.png
Alternative text: Not defined!
Image source: /latex.php
Alternative text: L_{upper} = 3223.21
Image source: /latex.php
Alternative text: L_{lower} = 1,697.10
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Alternative text: F_{tail} = 122.75
Image source: /wp-content/uploads/2017/06/06.-table-2.png
Alternative text: Not defined!
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Image source: /wp-content/uploads/2017/06/results-image-3.png
Alternative text: Not defined!
Image source: /wp-content/uploads/2017/05/TakeoffClimbAfterburning-1024x685.png
Alternative text: Not defined!
Image source: /latex.php
Alternative text: \dot{m}
Image source: /latex.php
Alternative text: U_a
Image source: /latex.php
Alternative text: U_j
Image source: /latex.php
Alternative text: \text{Thrust} = F=\dot{m}(U_j-U_a)
Image source: /latex.php
Alternative text: U_a
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Alternative text: N_p
Image source: /latex.php
Alternative text: U_a
Image source: /latex.php
Alternative text: P=F U_a = \dot{m} U_a (U_j - U_a)
Image source: /latex.php
Alternative text: \Delta KE = 0.5 \dot{m} (U_j^2 - U_a^2)
Image source: /latex.php
Alternative text: N_p = \frac{\dot{m} U_a (U_j-U_a)}{0.5\dot{m} (U_j^2 - U_a^2)} = \frac{2Ua}{Ua + Uj}
Image source: /latex.php
Alternative text: U_a
Image source: /latex.php
Alternative text: U_j
Image source: /latex.php
Alternative text: U_j
Image source: /latex.php
Alternative text: \dot{m}
Image source: /wp-content/uploads/2013/01/Turbofan_operation.png
Alternative text: Not defined!
Image source: /wp-content/uploads/2017/05/Afterburning-1024x996.png
Alternative text: Not defined!
Image source: /wp-content/uploads/2017/05/TwoPositionNozzle-1024x601.png
Alternative text: Not defined!
Image source: /wp-content/uploads/2017/05/VariableAngleNozzle-1024x913.png
Alternative text: Not defined!
Image source: /latex.php
Alternative text: \frac{1773}{973} \times \frac{40\%}{2} = 36\%
Image source: /wp-content/uploads/2017/04/aeroelasticity-1024x549.png
Alternative text: Not defined!
Image source: /latex.php
Alternative text: \cos 45^\circ = 0.71
Image source: /latex.php
Alternative text: V \cos \psi
Image source: /latex.php
Alternative text: V
Image source: /main-qimg-b2ed0870141e48f2548239d477e2189f-c
Alternative text: Not defined!
Image source: /wikipedia/commons/thumb/2/21/Airflow_forward_and_backward_swept_aircraft.svg/256px-Airflow_forward_and_backward_swept_aircraft.svg.png
Alternative text: Airflow forward and backward swept aircraft
Image source: /wikipedia/commons/thumb/1/10/X-29_at_High_Angle_of_Attack_with_Smoke_Generators.jpg/512px-X-29_at_High_Angle_of_Attack_with_Smoke_Generators.jpg
Alternative text: X-29 at High Angle of Attack with Smoke Generators
Image source: /wp-content/uploads/2015/01/FRP.jpg
Alternative text: Not defined!
Image source: /latex.php
Alternative text: [+\theta,-\theta]
Image source: /latex.php
Alternative text: [-\theta,+\theta]
Image source: /latex.php
Alternative text: +\theta
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Alternative text: -\theta
Image source: /latex.php
Alternative text: +\theta
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Alternative text: -\theta
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Alternative text: +\theta
Image source: /wp-content/uploads/2017/04/GrummanX-29.png
Alternative text: Not defined!
Image source: /latex.php
Alternative text: \sigma
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Alternative text: \sigma = \frac{P}{A}
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Alternative text: P
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Alternative text: A = \pi d^2 / 4
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Alternative text: d
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Alternative text: \epsilon
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Alternative text: \epsilon = \frac{\Delta L}{L}
Image source: /latex.php
Alternative text: \Delta L
Image source: /latex.php
Alternative text: L
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Alternative text: E = \frac{\sigma}{\epsilon}
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Alternative text: E
Image source: /latex.php
Alternative text: \text{Strain Energy per unit volume} = \frac{1}{2} \sigma \times \epsilon
Image source: /latex.php
Alternative text: d
Image source: /latex.php
Alternative text: \sigma
Image source: /latex.php
Alternative text: \epsilon
Image source: /latex.php
Alternative text: \text{Strain Energy per unit area} = \frac{1}{2} \sigma \times \epsilon \times d
Image source: /latex.php
Alternative text: \epsilon = \frac{\sigma}{E}
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Alternative text: \epsilon
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Alternative text: \text{Strain Energy per unit area} = \frac{d\sigma^2}{2E}
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Alternative text: G
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Alternative text: 2G
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Alternative text: \frac{d\sigma^2}{2E} = 2G \Rightarrow \sigma = 2 \sqrt{\frac{G E}{d}}
Image source: /latex.php
Alternative text: \sigma = \sqrt{\frac{G E}{d}}
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Alternative text: E
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Alternative text: G
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Alternative text: G \approx \frac{Ed}{20}
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Alternative text: \sigma \approx \sqrt{\frac{E^2}{20}} \approx \frac{E}{5}
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Alternative text: \epsilon = \frac{\sigma}{E} \approx \frac{1}{5}
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Alternative text: E
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Alternative text: d = 3
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Alternative text: 1/100
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Alternative text: \mu
Image source: /wp-content/uploads/2016/07/Untitled.jpg
Alternative text: Variation of tensile strength with fibre diameter. From W.H. Otto (1955). Relationship of Tensile Strength of Glass Fibers to Diameter. Journal of the American Ceramic Society 38(3): 122-124. DOI: 10.1111/j.1151-2916.1955.tb14588.x.
Image source: /wp-content/uploads/2016/07/Untitled-1.jpg
Alternative text: Stress concentration at a notch
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Alternative text: a
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Alternative text: R
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Alternative text: 1 + 2 \sqrt{\frac{a}{R}}
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Alternative text: \mu
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Alternative text: 1 + 2 \sqrt{\frac{1 \times 10^{-6}}{1 \times 10^{-10}}} = 201
Image source: /wikipedia/commons/thumb/e/e5/Orville_Wright%26flyer1909.jpg/512px-Orville_Wright%26flyer1909.jpg
Alternative text: Orville Wright&flyer1909
Image source: /cayl6.jpg
Alternative text: Not defined!
Image source: /wikipedia/commons/thumb/3/31/Ray_Flying_Legends_2005-1.jpg/512px-Ray_Flying_Legends_2005-1.jpg
Alternative text: Ray Flying Legends 2005-1
Image source: /wikipedia/commons/thumb/5/50/Bell_X-1_46-062_%28in_flight%29.jpg/512px-Bell_X-1_46-062_%28in_flight%29.jpg
Alternative text: Bell X-1 46-062 (in flight)
Image source: /wikipedia/commons/thumb/2/26/North_American_X-15.jpg/512px-North_American_X-15.jpg
Alternative text: North American X-15
Image source: /wikipedia/commons/thumb/a/a1/Shuttle_profiles.jpg/512px-Shuttle_profiles.jpg
Alternative text: Shuttle profiles
Image source: /aircraft/Blaue-Maus-Glider/IMAGES/Schwatze-Duvel-glider.jpg
Alternative text: Not defined!
Image source: /aircraft/Blaue-Maus-Glider/IMAGES/Blaue-Maus-Infligh1.jpg
Alternative text: Not defined!
Image source: /wikipedia/commons/thumb/7/78/Aircraft_Glider_Vampyr.jpg/512px-Aircraft_Glider_Vampyr.jpg
Alternative text: Aircraft Glider Vampyr
Image source: /wikipedia/commons/thumb/4/45/Von_Karman_and_JATO_Team_-_GPN-2000-001652_%28cropped%29.jpg/512px-Von_Karman_and_JATO_Team_-_GPN-2000-001652_%28cropped%29.jpg
Alternative text: Von Karman and JATO Team - GPN-2000-001652 (cropped)
Image source: /wp-content/uploads/2016/06/Untitled-1024x679.png
Alternative text: Boundary layer separation over cylinder
Image source: /latex.php
Alternative text: Re = \frac{\rho V d}{\mu}
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Alternative text: \rho
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Alternative text: V
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Alternative text: d
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Alternative text: \mu
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Alternative text: \rho V d
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Alternative text: \mu
Image source: /wp-content/uploads/2016/07/Untitled.png
Alternative text: Flow around a cylinder for different Reynolds numbers
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Alternative text: V
Image source: /wikipedia/commons/b/b4/Vortex-street-animation.gif
Alternative text: Vortex-street-animation
Image source: /wp-content/uploads/2016/06/untitled.jpg
Alternative text: Velocity profile of laminar versus turbulent boundary layer
Image source: /latex.php
Alternative text: \tau_w = \mu \frac{\mathrm{d}u}{\mathrm{d}y}_w
Image source: /latex.php
Alternative text: \mathrm{d}u/\mathrm{d}y
Image source: /wp-content/uploads/2016/06/Untitled-1024x679.png
Alternative text: Boundary layer separation over cylinder
Image source: /latex.php
Alternative text: C_D
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Alternative text: C_D = \frac{D}{1/2 \rho U_0^2A}
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Alternative text: D
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Alternative text: \rho
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Alternative text: U_0
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Alternative text: A
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Alternative text: A
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Alternative text: A
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Alternative text: A
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Alternative text: 1/2 \rho U_0^2
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Alternative text: A
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Alternative text: C_D
Image source: /training/flight_training/aero/images/30.jpg
Alternative text: Not defined!
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Alternative text: R = \frac{\rho U_0 d}{\mu}
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Alternative text: U_0
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Alternative text: d
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Alternative text: R = 10^5
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Alternative text: R = 10^7
Image source: /latex.php
Alternative text: R = 10^5
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Alternative text: R = 10^7
Image source: /latex.php
Alternative text: C_D U_0^2
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Alternative text: U_0
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Alternative text: d
Image source: /shutterstock/videos/1878445/thumb/1.jpg
Alternative text: Not defined!
Image source: /dept/chem-eng/WWW/faculty/plawsky/Comsol%20Modules/CylinderTransient/CylinderImage.jpg
Alternative text: Not defined!
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Alternative text: F_B
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Alternative text: F_B = \frac{\pi}{6} d^3 \left( \rho_l-\rho_g \right)g
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Alternative text: d
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Alternative text: \rho_g
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Alternative text: \rho_l
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Alternative text: g
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Alternative text: 9.81 m/s^2
Image source: /latex.php
Alternative text: \frac{\pi}{6} d^3
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Alternative text: D
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Alternative text: D = 1/2 C_D \rho_l U_T^2 \left( \frac{\pi}{4} d^2\right)
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Alternative text: U_T
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Alternative text: A
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Alternative text: \frac{\pi}{4} d^2
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Alternative text: D
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Alternative text: F_B
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Alternative text: \frac{\pi}{6} d^3 \left( \rho_l-\rho_g \right)g = 1/2 C_D \rho_l U_T^2 \left( \frac{\pi}{4} d^2\right)
Image source: /latex.php
Alternative text: U_T^2 = \frac{4d\left(\rho_l-\rho_g\right)g}{3C_D\rho_l}
Image source: /latex.php
Alternative text: 10^3-10^5
Image source: /wikipedia/commons/thumb/4/4c/Drag_coefficient_of_a_sphere_as_a_function_of_Reynolds_number.png/512px-Drag_coefficient_of_a_sphere_as_a_function_of_Reynolds_number.png
Alternative text: Drag coefficient of a sphere as a function of Reynolds number
Image source: /latex.php
Alternative text: 1.2 kg/m^3
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Alternative text: 989 kg/m^3
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Alternative text: U_T^2 = \frac{4 \times 0.003 \times \left(989-1.2\right) \times 9.81}{3 \times 0.5 \times 989} = 0.0790 \ m^s/s^2
Image source: /latex.php
Alternative text: U_T = 0.281 \ m/s = 28.1 \ cm/s \left( 11 \ inches/s \right)
Image source: /latex.php
Alternative text: \mu = 0.001 Ns/m^2
Image source: /latex.php
Alternative text: R = \frac{\rho_l U_T d}{\mu} = \frac{989 \times 0.281 \times 0.003}{0.001} = 833
Image source: /latex.php
Alternative text: 10^3-10^5
Image source: /wikipedia/commons/thumb/d/db/Junkers_J_1_at_D%C3%B6beritz_1915.jpg/512px-Junkers_J_1_at_D%C3%B6beritz_1915.jpg
Alternative text: Not defined!
Image source: /wp-content/uploads/2016/06/untitled.jpg
Alternative text: Velocity profile of laminar versus turbulent boundary layer
Image source: /wp-content/uploads/2016/06/Untitled-1024x679.png
Alternative text: Boundary layer separation over cylinder
Image source: /wp-content/uploads/2016/06/boundarylayeraerofoil.jpg
Alternative text: Boundary layer separation over the top surface of a wing
Image source: /images/i/000/047/934/original/golf-ball-dimples-1004-02.jpg
Alternative text: Not defined!
Image source: /latex.php
Alternative text: L = \frac{1}{2}C_L \rho V^2 S
Image source: /latex.php
Alternative text: \rho
Image source: /latex.php
Alternative text: V
Image source: /latex.php
Alternative text: S
Image source: /latex.php
Alternative text: C_L
Image source: /latex.php
Alternative text: C_{Lmax}
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Alternative text: 16^\circ
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Alternative text: \approx 2^\circ
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Alternative text: V
Image source: /latex.php
Alternative text: \approx 15^\circ
Image source: /wikipedia/commons/archive/2/2b/20071215180040%21Wing.slat.600pix.jpg
Alternative text: Not defined!
Image source: /wp-content/themes/platform/images/pagelines.png
Alternative text: Platform by PageLines
Image source: /wp-content/plugins/jetpack/modules/sharedaddy/images/loading.gif
Alternative text: loading

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http://web.mit.edu/drela/Public/web/xfoil/
https://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/19930094469.pdf
https://www.amazon.com/Jet-Engine-Rolls-Royce/dp/1119065992/ref=sr_1_1?ie=UTF8&qid=1495004962&sr=8-1&keywords=the+jet+engine
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