Hybrid Trajectory Optimization Method and Tracking Guidance for Variable-Sweep Missiles

Table 6

The aerodynamic derivatives about the lift in different Mach numbers.

Ma
0.6 Ma	−3.9e−05	0.005258	−0.000222	0.187119	0.001143
0.7 Ma	−3.7e−05	0.004970	−0.000214	0.190234	0.001116
0.9 Ma	−9.3e−05	0.008979	−0.002487	0.641453	5.4e−05
1.2 Ma	−9.5e−05	0.009604	−0.005051	1.432001	2.8e−05
1.5 Ma	−6.4e−05	0.007119	−0.003462	1.331806	−5.9e−05
1.8 Ma	−5.5e−05	0.006341	−0.002875	1.182695	−9.4e−05
2.2 Ma	−4.3e−05	0.005274	−0.002523	1.067554	−0.00013
2.5 Ma	−3.6e−05	0.004722	−0.002362	1.025435	−0.000163
2.8 Ma	−3.1e−05	0.004311	−0.002229	0.983656	−0.000202
3.2 Ma	−2.6e−05	0.004004	−0.002097	0.947885	−0.000212