Table 3. Inertial parameters measured during each flight configuration.

	Steady flight		Parabolic flight		Unit
	Mean	Range	Mean	Range
h	6.332	0.025	8.642	0.228	km
s	163	8	82	13	m s−1
ax	−0.196	0.314	0.078	0.069	m s−2
ay	0.078	0.039	0.039	0.039	m s−2
az	9.816	0.382	0.098	0.226	m s−2
θx	−1.2	2.5	−1.9	2.4	°
θy	0.01	0.35	−6.0	50.8	°
Ωx	−0.07	0.24	−0.19	0.90	° s−1
Ωy	0.00	0.15	4.1	1.1	° s−1
Ωz	−0.04	0.12	0.00	0.16	° s−1
〈a〉	9.789	0.002	9.782	0.002	m s−2
〈cosθ〉	0.999	0.002	0.875	0.100
aeff	9.779	0.020	8.56	0.98	m s−2

h, altitude; s, air speed; a_x, a_y, a_z, accelerations along x, y, z axes of the vehicle; θ_x, roll angle; θ_y, slope angle; Ω_x, Ω_y, Ω_z, rotation rates about the x, y, z axes.

Values in the ‘Mean' columns indicate the average of data recorded over five consecutive parabolas (∼800 s of flight time), and the ‘Range' column gives the interquartile range of the same data—indicating the typical variation for each parameter. The aircraft's altitude, air speed, roll and slope angles are courtesy of Novespace. The last three rows give the mean gravitational acceleration 〈a〉, the mean projection factor 〈cosθ〉 and the effective gravitational acceleration a^eff (equation (12)) used to measure the Eötvös parameter shown in Table 2. In these rows, the value in the Range column corresponds to the 1σ uncertainty. Estimates of 〈a〉 were obtained from the Earth gravity model EGM2008 over the flight region defined by opposite-corner coordinates 6° 44′ W, 45° 23′ N and 2° 43′ W, 48° 37′ N at the indicated mean altitude h. The projection factor is based on the variation in the aircraft's roll and slope angles during the measurements.