## Textbooks & Solution Manuals

Find the Source, Textbook, Solution Manual that you are looking for in 1 click.

## WriteWise AI Model by Holooly Genius

Your Ultimate AI Essay Writer & Assistant.

## Holooly Arabia

For Arabic Users, find a teacher/tutor in your City or country in the Middle East.

## Holooly Help Desk

Need Help? We got you covered.

Products

## Textbooks & Solution Manuals

Find the Source, Textbook, Solution Manual that you are looking for in 1 click.

## WriteWise AI Model by Holooly Genius

Your Ultimate AI Essay Writer & Assistant.

## Holooly Arabia

For Arabic Users, find a teacher/tutor in your City or country in the Middle East.

## Holooly Help Desk

Need Help? We got you covered.

## Q. 14.2

A box-shaped truck body 2.5 m wide, 3 m high, and 7 m long (Figure 14.9) is traveling at 20 m/s in 20°C air. Calculate the contributions to the total drag of the truck from the sides and top of the truck body. Assume that a sheet metal seam near the leading edge of each panel causes the boundary layer to be turbulent for the full length of the panel. Also ﬁnd the wall shear stress and boundary layer thickness along the top panel, and the maximum value of the wall shear stress and boundary layer thickness on this panel.

## Verified Solution

We will ﬁrst use Eq. 14.16a to calculate the maximum Reynolds number at the down-stream edge x = L of each panel. With viscosity data from Appendix A, we obtain

$Re_L=\frac{UL}{\nu}=\frac{(20 \ m/s)(7\ m )}{1.51×10^{−5}\ m^2/s}=9.3\times 10^6$

This is just within the applicable range of Eqs. 14.16a–14.16h. The drag force on each panel is calculated by using Eq. 14.16g. For the top we obtain

$Re_x=\frac{Ux}{\nu}$                           (14.16a)

$\frac{\delta (x)}{x}=0.370(Re_x)^{-1/5}$                            (14.16b)

$\frac{\delta ^*(x)}{x}=0.0463(Re_x)^{-1/5}$                            (14.16c)

$\frac{\Theta (x)}{x}=0.0360(Re_x)^{-1/5}$                            (14.16d)

$\tau_W$(x) = 0.0288ρU2(Rex)−1/5                               (14.16e)

Cf(x) = 0.0577(Rex)−1/5                                            (14.16f)

CD = 0.072(ReL)−1/5                                           (14.16h)

$F_{D_{top}}$ = 0.036ρU2wL(ReL)−1/5

$=\frac{0.036(1.204\ kg/m^3)(20\ m/s)^2(2.5\ m)(7\ m)}{(9.3×10^6)^{1/5}}$
= 12.3 N
The drag on each side panel is found using the same formula with w = 3 m instead of w = 2.5 m. Thus we can write $F_{D_{side}}$ = (3/2.5)$F_{D_{top}}$ = 14.8 N. The drag of all three panels is now calculated as $F_{D}$ = 2$F_{D_{side}}$ + $F_{D_{top}}$ = 2(14.8 N ) + 12.3 N = 41.9 N. To ﬁnd the boundary layer thickness and wall shear stress on the top panel, we use Eqs. 14.16b and 14.16e, respectively. Writing these explicitly in terms of x we have

$\delta (x)=0.370x\left(\frac{Ux}{\nu} \right)^{-1/5}=0.370\left(\frac{20\ m/s}{1.51\times 10^{-5}\ m^2/s} \right)^{-1/5} x^{4/5}=0.022x^{4/5}\ m^{1/5}$

$τ_W(x) =0.0288ρU^2\left(\frac{Ux}{\nu} \right)^{-1/5}$

= 0.0288(1.204 kg/m3)(20 m/s)2 $\left(\frac{20\ m/s}{1.51\times 10^{-5}\ m^2/s} \right)^{-1/5} x^{-1/5}$

= 0.83 x−1/5 (N/m2)(m1/5)

Note that these results for δ(x) and $\tau_W$(x) also apply to the side panels. The maximum value of the shear stress and boundary layer thickness on each panel will occur at x = L. Inserting the data we ﬁnd:

δ(L) = 0.022L4/5m1/5 = 0.022(7 m )4/5m1/5 = 0.104 m = 10.4 cm

$\tau_W$(L) = 0.83L−1/5(N/m2)(m1/5) = (0.83)(7 m )−1/5(N/m2)(m1/5) = 0.56 N/m2