An Euler code is used to predict the e owe eld over a hypersonic missile and to determine the carryover factors KW(B), e n liftinthepresenceofthebody,and KB(W),liftproducedby thebody in thepresenceofthee ns. Themissile is assumed to have cruciform, delta e ns in the + orientation and an aspect ratio of 1.529. Results are presented as a function of e n span at Mach 6, 8, and 10, for a 2-deg angle of attack. Two ratios of specie c heats, 1.4 and 1.3, are considered to partially account for vibrational excitation effects. Both carryover factors have approximately the same variation with e n size as their slender body predictions. The values of KW(B) and KB(W) are 2 for a missile without e ns. Thevalue of KW(B) decreases toward 1 and KB(W) decreases toward 0.20 as thee n span becomeslarge. At a e xed e n size, KW(B) decreases and KB(W) increases as Mach number increases. At a e xed value of e n size and Mach number, both KW(B) and KB(W) increase slightly due to vibrational excitation effects. Nomenclature AF = wing-planform area formed by two e ns joined at their root chord, m 2 AR = aspect ratio of wing formed by joining two e ns at their rootchord CN = normal force coefe cient referenced to AF CNC = normal force coefe cient of entire missile CNF = normal force coefe cient of e n alone CNF;® = normal force curve slope, e n alone CNFB = forebody-alone normal force coefe cient CNFB;® = normal force curve slope, forebody alone KB.W/ = body‐e n interference factor KW.B/ = en‐body interference factor L B.W/ = body lift in presence of e n, N LC = entire missile cone guration lift, N L F = e n-alone lift, N LFB = forebody-alone lift, N LW.B/ = e n lift in presence of body, N M = freestream Mach number P = local pressure/(freestream pressure ) q = freestream dynamic pressure, N/m 2