International Journal of Aerospace Engineering / 2015 / Article / Fig 6

Research Article

A Numerical Method for Blast Shock Wave Analysis of Missile Launch from Aircraft

Figure 6

Exemplary contour plot of strain distribution in helicopter tail boom during shock wave loading from missile launch (a) and comparison with test data for strain gauge SG1 in front of horizontal stabiliser (b) and SG2 behind horizontal stabiliser (c).
(a)
(b)
(c)