The present paper reports on the results of an experimental study on aerothermodynamic effects associated with the injection of a lateral jet into a hypersonic crossflow around a generic missile model. This study intends to close the gap of missing reliable information on measured combined surface pressure and heat flux distribution on a missile configuration with a lateral jet. The model, consisting of a cone, cylindrical main body, and a flare, includes a single side jet hole. The model is made of a material with low thermal conductivity to visualize the surface temperature distribution, that is, heat fluxes. The surface temperature development on the model has been measured by infrared thermography. Using these data, the heat flux rate has been determined, taking into account temperature-dependent material characteristics, assuming a semi-infinite wall and the exchange of radiative cooling to the environment. Flow topology was analyzed using oil flow and schlieren images and wall pressure distribution measurements. The experimental data show that the jet pressure ratio has a significant effect on the side jet flow topology and its interaction with the crossflow. The influence of the angle of attack and the yaw angle on the pressure and heat flux distribution has also been measured clearly. Finally, the effect of various side jet gas media on the flow interaction has been demonstrated with tests using argon and helium as a jet gas complementary to air. Nomenclature a = thermal diffusivity, m 2 s 1 a = speed of sound, m s 1 C p = pressure coefficient c p = specific heat capacity at constant pressure, J g 1 K 1 D = diameter of the cylindrical part of model, mm d J = diameter of jet nozzle, mm M J = Mach number of the jet flow M 1 = Mach number of the external flow p = local pressure, bar p t = total pressure, bar p 0J = pitot pressure at the jet exit, bar p 1 = static pressure of the external flow, bar q = dynamic pressure, bar q conv = convective flux q L = conductive heat flux q rad = radiative heat flux Re = Reynolds number based on m 1 St = Stanton number T J = static temperature of jet flow, K T t = total temperature of crossflow, K T 1 = static temperature of the external flow, K t = time, s U 1 = velocity of external flow, m s 1 x, y = Cartesian coordinates z = thickness of polyether ether ketone material, mm = angle of incidence, respectively, heat-transmission coefficient therm = coefficient of linear thermal expansion, K 1 = angle of yaw " = emission coefficient = isentropic coefficient = thermal conductivity, W m 1 K 1 = density, kg m 3 B = Stefan-Boltzmann constant, J K 1 ' = circumferential angle Subscripts i = index (position) J = jet j = index (time) ref = reference value U = ambiance W = wall 0 = stagnation condition 1 = freestream

Scramjet design is characterized by a multitude of design variables influencing a highly nonlinear and complex system. Methods such as mean line calculations, high fidelity computational fluid dynamics, and empirical studies are generally used to derive aircraft engine performance. Because of the high complexity and the incomplete knowledge of hypersonic flow regimes, the question of robust design arises in the given context and leads to the need of probabilistic methodology. In this paper a probabilistic approach to scramjet engine design assessing both inflow and model uncertainty is presented. The two different types of uncertainty are quantified with respect to their different nature by use of a two-step bootstrap methodology. A descriptive sampling Monte Carlo method is employed to propagate the quantified uncertainties through the engine model to exemplify the high sensitivity of net thrust vector to present uncertainties and to analyze the correlation between the parameters variations. Nomenclature A = area, m 2 E i = error vector of the ith component, i 2 0; 31; 4; 7 ;9 (see Fig. 1) F net;x , F net;y = net thrust in x and y directions, N G i = vector of geometrical parameters of the ith component, i 2 0; 31; 4; 7 ;9 (see Fig. 1) h = duct height, m L = segment length, m Ma = Mach number _ m = mass flow, kg s 1 n = surface normal vector p = static pressure, Pa px, px j y = probability of x; probability of x assuming y Re x = Reynolds number S fuel = vector of fuel parameters (see Fig. 1) T = static temperature, K v = velocity, m s 1 X i = vector of deterministic flow parameters of the ith component, i 2 0; 31; 4; 7 ;9 (see Fig. 1) X i = vector of probabilistic flow parameters of the ith component, i 2 0; 31; 4; 7 ;9 (see Fig. 1) = ramp angle, deg = boundary-layer displacement thickness, m = mean value x = spline describing the geometry of the nozzle expansion ramp = flow density, kg m 3

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