Taking the first terms in -me and -md, one can also obtain the stiffness derivative -c mQ and the damping derivative -Cmj. Numerical results show 8 that in both -me and -me, terms proportional to k 2 , & 3 , . . . , etc. are negligible even if k is of order unity.As seen from Fig. 2, the second set of waves tends to destabilize the body and it becomes dominant for thick wedges. It is due to this set of waves that negative damping appears under certain conditions.For hypersonic flow past a slender wedge the shock angle 0 is small, and if terms of order /3 2 are neglected we havewhere K = M m fi is the hypersonic similarity parameter. Therefore the second set of waves disappears and we have from which we obtaina n~3 (m n + 1) sinojn} where oi n = k(m n -1)[2 Equation (14) and a special case of (15) when h = 0 are identical to those obtained in Ref.6. An example is given in Fig. 2 showing the difference between the results of the general analysis [Eq. (11)] and that of Mclntosh [Eq. (15)]. A detailed comparison can be found in Ref. 8. Nomenclature M = Mach number Pb = base pressure POO = freestream pressure base pressure ratio dome radius base radius freestream Reynolds number based on length nose radius bluntness ratio A0 = flow separation angle T = temperature h = enthalpy
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