# 7.2: Air Resistance Proportional to the Speed

- Page ID
- 6968

As in the previous section, I shall write the \( x\)-component of the equation of motion, and of the first and second time integrals, in the left hand column, and the \( y\)-component in the right-hand column. The \( x\)-component of the air resistance per unit mass is \( \gamma\dot{x}\) and the \( y\)-component is \( \gamma\dot{y}\). Here \( \gamma\) is the damping constant, defined in Section 6.3. The \(x\)- and \(y\)-components of the initial velocity are, respectively, \( V_{0} \cos \alpha\) and \( V_{0} \sin \alpha\). It should be readily seen that the equations of motion and their time integrals are as follows:

Horizontal | Vertical | |
---|---|---|

\( \ddot{x} = -\gamma\dot{x}\) | \( \ddot{y} = -g-\gamma\dot{y}\) | \( 7.2.1a,b\) |

\( \dot{x} = u = V_{0}\cos\alpha.e^{-\gamma t} \) | \( \dot{y}= v= V_0 \sin \alpha e^{-\gamma t} -\hat{v}(1-e^{\gamma t} ) \\ \text{where} \, \hat{v} = g/\gamma\) | \( 7.2.2a,b\) |

\( x=x_\infty\left(1 - e^{-\gamma t}\right)\\ \text{where}\space x_{\infty} = \frac{V_0 \cos \alpha}{\gamma} \) | \( y = \dfrac{1}{\gamma}(V_{0}\sin \alpha + \hat{v})(1-e^{-\gamma t})- \hat{v}t \) | \( 7.2.3a,b\) |

(In case it is not "readily seen", for the horizontal motion refer to Chapter 6, Section 3, especially Equations 6.3.2, 6.3.3 and 6.3.5, and for the vertical motion refer to Chapter 6, Section 3b, especially Equations 6.3.24, 6.3.25 and 6.3.27.) It will be seen that, as \( t\rightarrow\infty\), \( u\rightarrow0\), \( v\rightarrow -\hat{v}\), \( x\rightarrow x_{\infty}\). The \( xy\)*-equation** to the trajectory* is the \( t\)-eliminant of Equations \( 6.2.3a\) and \( 6.2.3b\). After a small amount of algebra this is found to be:

\[ y=\dfrac{x(V_{0}\sin\alpha+\hat{v})}{V_{0}\cos\alpha} + \dfrac{\hat{v}}{\gamma}\ln \left(1-\dfrac{x}{x_{\infty}}\right). \tag{7.2.4}\label{eq:7.2.4} \]

The *range on a horizontal plane* is found by setting \( y\) = 0, to obtain either

\[ x = -Aln(1-\frac{x}{x_{\infty}}) \tag{7.2.5}\label{eq:7.2.5} \]

or

\[ x = {x_{\infty}}(1-e^{-\frac{x}{A}}), \tag{7.2.6}\label{eq:7.2.6} \]

where

\[ A=\frac{\hat{v}V_{0}cos\alpha}{\gamma(V_{0}sin\alpha+\hat{v})},x_{\infty}=\frac{V_{0}cos\alpha}{\gamma}\]

and

\[ \hat{v}=\frac{g}{\gamma}.\]

Example \(\PageIndex{1}\)

Suppose

- \( V_{0}\) = 20 ms
^{-1} - \( \alpha\) = 50\( ^{\circ}\)
- \( g\) =9.8 ms
^{-2} - \(\gamma\) =1.96s
^{-1}(\( \therefore\hat{v}\)=5 ms^{−1})

Then \( A\) =1.613 870 65 m

and \( x_{\infty}\) = 6.55905724 m.

Try to find the range on the horizontal plane, using either Equation \(\ref{eq:7.2.5}\) or \(\ref{eq:7.2.6}\), to nine significant figures. Which equation works best? Newton-Raphson may fail with a stupid first guess - but it should not be difficult to make a fairly intelligent first guess. I should not tell you, but figure VII.2 was calculated using the data of this example.

I make the answer 6.437 584 2 m.

Here’s a more difficult problem.

Example \(\PageIndex{2}\)

It is well known that, in the absence of air resistance, the maximum range on the horizontal plane is effected by choosing the initial launch elevation to be \( \alpha\) = 45\( ^{\circ}\). What if there is air resistance, with damping constant \( \gamma\)? What, then, should be the angle of launch to achieve the greatest range on the horizontal plane? Given Equation \(\ref{eq:7.2.6}\), \( x=x_{\infty}(1-e^{\frac{-x}{A}})\), for what value of \( \alpha\) is \( x\) greatest?

**Solution**

Equation \( \ref{eq:7.2.6}\), written in full, is

\[ x=\frac{V_{0}cos\alpha}{\gamma}\left[1-exp\left(\frac{-\gamma(V_{0}\sin\alpha+\hat{v})x}{\hat{v}V_{0}\cos\alpha}\right)\right]. \tag{7.2.7}\label{eq:7.2.7}\]

This can be written

\[ x=acos\alpha\left[1-exp\left(-\frac{(b \sin\alpha + 1)x}{a \cos\alpha}\right)\right], \tag{7.2.8}\label{eq:7.2.8}\]

where \( a=\frac{V_{0}}{\gamma}\) and \( b=\frac{V_{0}}{\hat{v}}=\frac{\gamma V_{0}}{g}\). We have to find for what value of \( \alpha\) is \( x\) greatest. It seems a simple enough problem, but at the moment I can’t find a good way of solving it. If anyone has a clue, let me know (jtatum@uvic.ca). In the meantime, the best I can offer is, for our particular numerical example, to calculate the range, \( x\), for several values of \( \alpha\) and see where it goes through a maximum. For our particular numerical example, \( a\) = 10.204 081 63 m and \( b\) = 4. Here is a graph of range versus launch angle, for an initial speed of 20 ms^{−1}. A launch angle of about 23\( ^{\circ}\) 59′ gives a range of about 8.4635 m. For a given \( \gamma\) and \( g\), the optimum launch angle depends on the launch speed \( V_{0}\). Is this intuitively obvious?