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

Table 7

The aerodynamic derivatives about the drag in different Mach numbers.

Ma
0.6 Ma	0.093318	−0.005678	0.558185
0.7 Ma	0.092991	−0.005468	0.536770
0.9 Ma	0.001978	−0.006535	0.591776
1.2 Ma	0.000626	−0.005586	0.554623
1.5 Ma	−0.000931	−0.003766	0.409749
1.8 Ma	−0.001214	−0.003171	0.362277
2.2 Ma	−0.001622	−0.002469	0.302371
2.5 Ma	−0.002239	−0.002041	0.267316
2.8 Ma	−0.002979	−0.001763	0.243614
3.2 Ma	−0.002786	−0.001496	0.221210