The eccentricity \( e \) of an orbit can be related to the closest and farthest distances (periapsis \( R_p \) and apoapsis \( R_a \), respectively) using the formula:
\[ e = \frac{R_a - R_p}{R_a + R_p} \]
Given that \( R_p = 0.27 R_a \), we can express \( R_a \) in terms of \( R_p \):
\[ R_a = \frac{R_p}{0.27} \]
Now we can substitute \( R_a \) into the eccentricity formula:
- Substituting \( R_p = 0.27 R_a \):
\[ e = \frac{R_a - R_p}{R_a + R_p} \]
- Substitute \( R_p = 0.27 R_a \):
\[ e = \frac{R_a - 0.27 R_a}{R_a + 0.27 R_a} \]
- Simplifying this gives us:
\[ e = \frac{R_a (1 - 0.27)}{R_a (1 + 0.27)} = \frac{1 - 0.27}{1 + 0.27} = \frac{0.73}{1.27} \]
- Calculating this:
\[ e \approx 0.5748 \]
Thus, rounding gives us approximately \( 0.57 \).
Therefore, the correct response is:
0.57