Practice Midterm 1
The slider-crank mechanism shown below consists of a circular crank which is driven by a motor. A link is
attached to the crank and used to translate a slider back and forth.
a) Derive the constraint equation for the slider-cr
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Flow Through a Venturi Meter
800 N State College Blvd
Fullerton, CA 92831
In this experiment, a Venturi
meter is set up and w
Consider the inverted-slider crank linkage with the following dimensions:
a) Calculate the values of s for = 165 , 175 , 185 , 195 .
b) Calculate the values of for the same inputs.
c) Draw the starting position an
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1Consider the data for the N ABA 2412 airfoil given in Figures 4.1 and 4.11. The chord length is 2
m and the freestream velocity is El] mfs at stande sea level conditions.
a] Calculate the lift1 drag? and moment about the quarter chord [per uni
The mean csmherline of an airfoil is farmed by 3 straight sections, given by
[1.25 (E) : Ill 5 E a: (1.2
E= [Lat : .2Ecfw_.5
0115 .1 [(3) :15] : 0.5 :1 E 5 1.0
Find the lift msicisnt a; at sngleufsttsck : = IE.
CDnsider two thin airfoils moving at oonstant 1welocities near sea level and at zero anglecfattaclt.
The rst airfoil has a chord of 1 In and is moving at 2D Infsec. The second airfoil has a chord of 0.5
in and is moving at 40 mfsec. Assume the boundary,r
Investigate the impact of taper ratio and aspect ratio on an untwisted and tapered wing that has
a symmetric airfoil.
Apprcnrirnate the circulation distribution with the rst two odd terms (is. a = 1 and n = 3) in the
Fourier series expansion
Consider a wing with a span of IE In, root chord of 3 n11. and a taper ratio ELIE. The wing is
composed of three cambered sirfoils with (15:9 = 2 at each section. The wing is linearly,r twisted
geometrically such that the effective angle-of-a
CDnsider a wing with a span nf ll l:n1 rent chnrd cf 3 mi, and a taper ratin ll. The wing is
mmpnsed cf three cambered airfnils with (11:. = 2 at each sectinn. The wing is linearly.r twisted
geometrically such that the effective angledattack changes linea
The circulation aerate; the span cf a wing fullcwa the parabolic law
Calculate the induced velocity u: at mid-span, and compare the value with that obtained 1when the
distributicn is elliptic.
Egme 433 Spring 2017
Homework No. 01, due on February 9, 2017
Consider an airfoil at a 12 angle-of-attack. The normal and axial force coefficients are 1.2 and
0.03, respectively. Calculate the lift and drag coefficients.
Egme 433 Spring 2017
Homework No. 02, due on February 23, 2017
Consider a vortex flow described by
x + y2
a) Show that this flow satisfies the incompressible continuity equation.
b) Obtain the equations of th