Aerodynamics for Engineers 5th Edition by Bertin; John J.; Cummings; Russell | 9780132355216 | 0132355213 | Holooly

Aerodynamics for Engineers

52 SOLVED PROBLEMS

Question: 12.3

We neglected the viscous forces and the base pressure in estimating the forces acting on the sharp cone of Example 12.2. Consider a sharp cone (θc =10°) exposed to the Mach 8 flow of Tunnel B at the Arnold Engineering Development Center (AEDC), as shown in Fig. 12.18. For this problem, the ...

Verified Answer:

Let us use Figs.

8.15 \mathrm{~b}

a...

Question: 10.3

For purposes of discussion, the flow field has been divided into numbered regions that correspond to each of the facets of the double-wedge airfoil, as shown in Fig. 10.5. As was true for the approximate theories, the flow properties in each region, such as the static pressure and the Mach number, ...

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Since the surface of region 1 is parallel to the f...

Question: 10.2

Let us calculate the pressure coefficient on each panel of the airfoil in Example 10.1 using Busemann’s theory. We will use equation (10.23). ...

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Since panel 1 is parallel to the free stream, [lat...

Question: 10.1

Let us use the linear theory to calculate the lift coefficient, the wave-drag coefficient, and the pitching-moment coefficient for the airfoil section whose geometry is illustrated in Fig 10.5. For purposes of discussion, the flow field has been divided into numbered regions, which correspond to ...

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Let us now evaluate the various geometric paramete...

Question: 8.6

Assume that you are given the task of determining the aerodynamic forces and moments acting on a slender missile which flies at a Mach number of 3.5 at an altitude of 27,432 m (90,000 ft). Aerodynamic coefficients for the missile, which is 20.0 cm (7.874 in) in diameter and 10 diameters long, are ...

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1. Flight conditions. Using the properties for a s...

Question: 8.3

Consider the infinitesimally thin airfoil which has the shape of a parabola: x² = -c²/zmax (z – zmax) where zmax = 0.10c, moving through the air at M∞ = 2.059. The leading edge of the airfoil is parallel to the free stream. The thin airfoil will be represented by five linear segments, as shown in ...

Verified Answer:

For the free-stream flow,

\nu_{\infty}=28.0...

Question: 5.7

The pilot of an F-16 wants to maintain steady, level (i.e., in a constant altitude, horizontal plane) unaccelerated flight. Recall from the discussion at the start of this chapter, for flight in a horizontal plane, where the angles are small, the lift must balance the weight and the thrust supplied ...

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The first step is to use straight lines to generat...

Question: 5.6

The pilot of an F-16 wants to maintain a constant altitude of 30,000 ft flying at idle power. Recall from the discussion at the start of the chapter, for flight in a horizontal plane (i.e., one of constant altitude), where the angles are small, the lift must balance the weight of the aircraft, ...

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Let us first calculate the lower limit for the spe...

Question: 5.4

Calculate the local skin friction at a point 0.5 m from the leading edge of a flat-plate airfoil flying at 60 mIs at a height of 6 km. ...

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Refer to Table 1.2 to obtain the static properties...

Question: 5.3

Consider tests of an unswept wing that spans the wind tunnel and whose airfoil section is NACA 23012. Since the wing model spans the test section, we will assume that the flow is two dimensional. The chord of the model is 1.3 m. The test section conditions simulate a density altitude of 3 km. The ...

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First, we need to calculate the section lift coeff...

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