Unformatted text preview: Massachusetts Institute of Technology
Department of Aeronautics and
Astronautics
Cambridge, MA 02139 16.03/16.04 Unified Engineering III, IV
Spring 2004 Problem Set 2 Time Spent
(min)
F3
F4
F5 Name: F6
Due Date: 2/17/04 M3
M4
M5
M6
Study
Time Announcements: Have a happy Valentine’s Day. Remember that Tuesday, 2/17 is a
Monday schedule. Spring 2004 Uniﬁed Engineering
Fluids Problems F3–F6 F3+F4. A symmetric airfoil has a trailing edge ﬂap, with the hinge at xh /c = 0.75, with the ﬂap set at some small downward deﬂection angle ∂ . a) Deﬁne and sketch the camberlineslope dZ/dx, both versus x and versus α . b) Use Thin Airfoil Theory to determine the airfoil’s c� and cm,c/4 , as functions of � and ∂ . c) Important quantities for an airplanecontrol designer are the ﬂap control derivatives �c�
�∂ , � cm,c/4
�∂ Determine these for the present ﬂapped airfoil. Note: You may wish to check your results with Xfoil. The GDES menu allows you to set a ﬂap deﬂection. F5. An experimentalist determines that the downwash velocity for a rectangular wing of span b approximately obeys the relation w= L
2π V�
b2 a) Assuming w is constant across the span, determine how CDi depends on CL for this wing.
b) Determine the wing’s CL (�) relation, and compare its dCL /d� to the 2D value of 2� .
Hint: Start with the relation CL = 2��eﬀ .
F6. Anderson Chapter 5, p 416. Problems 1. and 2. (closely related). Unified Engineering
Spring 2004
Problem M3
Draw loading, shear and bending moment diagrams for the following beam under the
loading shown. Label all key values (i.e. where changes in magnitude or slope occur).
Maintain the convention shown below for positive shear forces and bending moments: Problem M4
The spar in a wing is modeled as a 10 m long beam. The combination of lift and selfweight
is modeled as resulting in a load distribution varying linearly from 5kN/m at the root to zero
at the tip. The beam has a rectangular cross section, height, h, of 100 mm and breadth, b, of
50 mm. Calculate the maximum bending stress in the beam, stating its location(s) and
calculate the deflection of the tip of the beam Problem M5
A simply supported beam, length 3L, is loaded by a load P applied at a distance of L from the
left hand end. The beam has a flexural stiffness EI.
a) Calculate the deflection of the beam as a function of position along the beam. b) Calculate the maximum deflection of the beam and state its location. c) Calculate the location at which the bending moment is a maximum (is this the same as for (b)?) Problem M6
This question is a first step towards designing a beamlike structure – e.g. a wing. You
are asked to specify a material for a cantilever beam (i.e. a beam clamped at one end)
which is to be of a specified length, L, and to be of the lowest possible mass to support
a load, P, applied at its tip while minimizing the tip deflection, d , without failing.
a) Assuming that the beam is constrained to have a solid square crosssection, side, h,
express the mass of the beam, m, in terms of, L, the relevant material properties and
the stiffness of the beam (P/ d). ( Note: The key to achieving this is to eliminate the
crosssectional dimension, h, from the expression). What is the figure of merit
(combination of material properties) that must be minimized in order to achieve the
lightest weight beam for a given desired stiffness?
b) If instead of a requirement on minimizing deflection the beam is required to
support the same load, P, without exceeding the failure strength, sf? What should the
figure of merit for selecting a material now be in order to create a beam of minimum
2 mass?. Assume that failure will occur when the maximum bending stress equals the
strength of the material.
c) For the materials listed in the table below, identify the material(s) that you would
choose to meet the criteria of part (a) and part (b). What other factors should be
considered in selecting a material for this application?.
d) Square solid sections are structurally not very efficient – “I” beams or hollow “box”
beams are much more efficient – why is this? What other factors would need to be
considered in selecting a material if a “box” crosssection was to be considered in (c)?.
Material Density, r,
(Mg/m3) Modulus, E, CTE, a, Price , p, Tensile Strength, (GPa) x 10 6 K1 ($/Mg) sf , (MPa) Stainless Steel 177 PH 7.9 193 12 1500 1435 Aluminum alloy (2000 series) 2.8 71 24 1500 350 Titanium alloy Ti6Al4V 4.5 120 9.0 8000 850 Carbon fiber composite* 1.5 70 3.0 100000 700 Wood (e.g spruce)* 0.6 12 4.0 300 300 Silicon Carbide (SiC) 3.0 410 4.0 50000 300 * These materials are anisotropic. You can assume that the values given are available
in the requisite directions for this problem. 3 ...
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Full Document
 Fall '05
 MarkDrela
 Aeronautics, Astronautics, Airfoil, simply supported beam, Unified Engineering III, lightest weight beam

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