Aerodynamics of a Slender Cone with Asymmetric Nose Bluntness at Mach 14

T effect of nose shape asymmetries on the aerodynamics of a 10° cone (d= 5 in) was studied in ARL's 20-in.-hypersonic wind tunnel (M^ = 14.2, pt = 1500 psi, Tt = 2000°R, Re^d = 2.3 x 10, TJTt = 0.3, y = 1.4). Surface pressures were measured at various angles of attack and sideslip. Schlieren pictures were taken with a special nose model at several roll attitudes. Stability derivatives were measured by the free oscillation technique at the reduced frequency cod/IV^ « 0.003. The results are summarized and some conclusions relating to flight dynamics are drawn. Figure 1 shows a sketch of model A and the pressure distribution over the afterbody. The asymmetry of the nose tip is the result of a planar cut 40° off the x-z plane. The projected frontal area of the cut is approximately ^% of the base area. The schlieren picture on the left-hand side of Fig. 2 shows the shock contour in the x-y plane near the nose of model A. The plot below is a cross section of model and shock at the axial station l/L = 0.2. In the neighborhood of $ = 270°, the observed shock nearly coincides with the sharp cone shock, as given by the expression