There are few papers for nonuniform in-plane motions of wings, practical applications of which may concern lead-lag motion of helicopter blades and motions of horizontal stabilizer in T-ail flutter. This paper presents a practical application for the basic formulation, which was developed by the present authors in reference 1. An airfoil having an arbitrary camber line is assumed to fly in a sinusoidally pulsating steam, which is inviscid and incompressible. Explicit formulae of lift distribution, lift and pitching moment are presented. The fact pointed out by ISAACS, the quasi-steady theory leads to a significant error, is confirmed in a more general way.
The pressure distributions on sphericallyblunted cones, which are installed in test section as axisymmetric condition, are measured in the hypersonic flows produced with contour and conical nozzles of the NAL gun tunnel. The experimental results of pressure coefficient are successfully correlated by the blast-wave-type parameters Cp/Cconep and (θcθc2/√CDn)/(xn/dn). The effect of nose bluntness on the pressure distribution of a blunted cone in inviscid hypersonic flow is clarified, by taking into account of viscous induced pressure included in the experimental results. It is also shown that the pressure distribution on models tested in conical nozzle is appreciable difference as compared With that tested in contour nozzle, but they are in good agreement with each other according to the source flow correction method proposed in the present paper. Detailed discussion about various effects, such as those of temperature and vibration, on pressure transducer is given for the measurement of low pressure.
The radial equilibrium of pseudo-axisymmetric flows in supersonic rotors which have no normal shock was considered and two examples were calculated with the following results.  The supersonic rotor blades which have flows with no turning and satisfying radial equilibrium conditions in the entire passages get thicker at the tip radius than at the hub.  If the deceleration combined with the appropriate turning through the supersonic rotor passage are taken into consideration, the constant absolute total pressure may be expected at the exit. The flow condition for which the radial equilibrium relations could be satisfied both before and behind the normal shock was described. An expression to establish the above was written by using three basic variables, which are the relative Mach number, the rotational Mach number of rotor (the ratio of rotational speed of rotor to sound velocity) and the relative flow angle, before the normal shock. In order to solve the equation, two variables or two equivalent conditions must be specified. The approach in this report seems to be useful in designing the rotor passage containing the normal shock.
The establishment of radial equilibrium of pseudo-axisymmetric flows was investigated in the entire passage of rotor containing a normal shock, and two examples, one with the known enthalpy addition from the rotor to the flow and the other with the known turning angle of flow, were calculated. The results showed the possibility of the apPlication of the approach stated in this report to the design of a shock-in-rotor type rotor.
An analysis on the CO2 Gasdynamic Laser cavity flow is reported. The analysis is based upon the solution for a simultaneous system of fluid dynamic equations and of photon-generating equation under the optimum conditions of the GDL nozzle flow. Numerical examples are performed on the three supersonic nozzles with different nozzle shapes.
The formation of mushroom-type longitudinal vortices with streamwise axces is noticed in the boundary layer both along flat walls and along curved ones of a two-dimensional convergent nozzle. The vortex formed on the flat wall is examined experimentally. Air flow in the boundary layer is visualized by using evaporated-gasoil smoke, which is supplied to the convergent nozzle through two-types of slit-nozzles set at two of the upstream walls. Owing to staticpressure gradient perpendicular to the nozzle axis, cross-flow in the boundary layer is generated, and the cross-flow is concentrated and gradually developed into a mushroom-type vortex.
A consideration of fiber anisotropy and temperature dependency of constituent material properties is included in a formulation of the problem. The method for solution used here is constructed by a slight modification of the method which was once developed and employed by the authors for calculating elastic moduli of unidirectional fiber-reinforced composites (UFC). Accuracy of numerical results is indicated by checking some relationships which should hold. It is shown that αz of UFC is approximately given by the modulus modified law of mixture, and that αx's based on the hexagonal and square array models are almost identical. Some relationships between α's of UFC and material properties of the constituents are graphically presented. Generally speaking, α's of UFC are linearly affected by those of the constituents.