A two-stage sounding rocket operates in vacuum. Stage 1 has structural ratio $\epsilon_1 = 0.10$ and payload ratio $\lambda_1 = 0.20$ with exhaust velocity $c_1 = 2500\text{ m/s}$. The initial-to-burnout mass ratio of stage 1 is $\frac{m_{01}}{m_{f1}} = \frac{1 + \lambda_1}{\epsilon_1 + \lambda_1} = \frac{1.20}{0.30} = 4.0$. What is the burnout velocity increment $\Delta v_1$ (in m/s) contributed by Stage 1?