ensemble averaging; a Blackman-Harris window is used to prevent spectral leakage. The frequency dependent gain is then obtained as $$G(f)=10\mathrm{Log}_{10} \frac{S_{SCM}}{S_{MAG}}.$$ Figure \[gain\_error\] shows the measured distribution of $G(f)$ for each vector component as well as the mean at each frequency, and the median gain error computed between 3 and 10 Hz. Systematic gain differences are measured in the $x$, $y$, and $z$ directions of -2.67, -2.50, and -2.58 dB. These values indicate that the typical SCM amplitude is approximately $75\%$ of the measured MAG signal.

Due to the relatively stable gain discrepancy in frequency and time, the SCM may be gain-matched to the MAG through multiplication of scaling factors (1.36,1.33, and 1.34) for the respective $x$, $y$,and $z$ axes. This correction is required in-order to remove artifacts associated with merging signals with un-equal amplitudes. The difference between on-ground and in-flight gain measurements are likely due to differences in the SCM operating temperature and small discrepancies caused by the matching between SCM and DFB, which unfortunately were not quantified due to lack of end-to-end calibration. Continued efforts to quantify and monitor variations in the gain-matching coefficients will be performed throughout the mission. Additionally, both gain-matched and nominal calibrations will be 