Roll Effects on Carryover for Hypersonic Delta Fin Missiles

Abstract

An Euler code is used to predict hypersonic missile ow elds and to determine the carryover factors for the effect of the body on wing lift K W ( (B) ) and for the effect of the wing on body lift K B( (W ) ). Results are presented for Mach 4, 6, 8, and 10 at an angle of attack of 2 deg. The missile has a conical nose, a cylindrical fuselage with a 1-deg are angle, and delta ns. Both £ and + n con gurationsare considered. Results are given for 20-and 30-deg semivertex angles as a function of nspan to body radius (at n leading edge), S/R LE . The wing-body carryover for £ ns is smaller for the top set of ns than it is for the bottom set of ns. The value of K W ( (B) ) for the missile with £ ns is slightly larger than it is for + ns at Mach 8 and 10. At Mach 4 and 6, K W ( (B) ) is independent of n con guration. K B( (W ) ) is larger for £ ns than it is for + ns, and it increases as semivertex angle decreases from 30 to 20 deg. K B( (W ) ) generally decreases as both Mach number and nspan increase. Equations and tables are presented for the carryover factors. Nomenclature A F = planform area of one n (A W =2), m 2 A R = aspect ratio of wing formed by joining two ns at their root chord A W = wing-planform area formed by two ns joined at their root chord, m 2 C L = lift coef cient referenced to A W C L B = lift coef cient, body alone C L B;® = lift curve slope, body alone C L M = lift coef cient, entire missile C L W = lift coef cient, wing alone C L W ;® = lift curve slope, wing alone F N ;i = normal force on i th n, N K B.W / = body-n carryover K F .B/;i = n-body carryover on i th n K W .B/ = wing-body carryover K B W .B/ = wing-body carryover ( ns 3 plus 4) K T W .B/ = wing-body carryover ( ns 1 plus 2) L B = lift, body alone, N L B.W / = body lift in presence of ns, N L F.B/;i = lift of i th n in presence of body, N L M = lift, entire missile, N L W = wing-alone lift (2 D 0), N M 1 = freestream Mach number P = pressure/(freestream pressure) q 1 = freestream dynamic pressure, N/m 2 R = body radius at end of nosecone, m R LE = body radius at root chord leading edge (1.419R), m S = nspan, from body centerline, m Z = missile axial distance, from nose, m Z LE = root-chord leading edge position, m ® eq = equivalent angle of attack, deg ® F = n angle of attack, deg ® 1 = missile angle of attack, deg ² = n semivertex angle (20, 30 deg) 2 = n angular position (0, 45 deg) µ f = body are angle (1 deg) Á = body angular position, deg (0 at top)