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Radiative heat transfer in a concentric cylinder system with a participating medium is demonstrated to be inherently two-dimensional, even for the consideration of heat transfer to the total inner ...

Numerical solutions are presented for mixed convection in rotating concentric cylinders with a porous sleeve. The porous sleeve is press fitted to the inner surface of the outer cylinder. Whereas t...

Underwood, E. E., Gomez, A., and Ueng, C.E.S., "Design and -'abrication of New Core Configurations for Sandwich Panels," Proceedings, IVth Inter-American Conference on Materials Technology, Caracas, Venezuela, June-July 1975, p. 531. Ueng, C.E.S. and Liu, T. L., "Optimization of a New Lightweight Sandwich Core," Proceedings, International Conference on Lightweight Shell and Space Structures for Normal and Seismic Zones, Alma-Ata, USSR, Vol. 2, Sept. 1977, pp. 375-383. Ueng, C.E.S., "Superplastically Formed New Sandwich Cores," Transportation Engineering Journal, ASCE, July 1978, pp. 437-447. Ueng, C.E.S., Underwood, E. E., and Liu, T. L., "Shear Modulus of Superplastically Formed Sandwich Cores," Proceedings of Symposium on Future Trends in Computerized Structural Analysis and Synthesis, Pergamon Press, edited by A. K. Noor and H. G. McComb, Jr., eds., Oct.-Nov. 1978, Washington, D.C., pp. 393-397; also International Journal of Computers and Structures, Vol. 10, Nos. 1 and 2,1979, pp. 393-397. Ueng, C.E.S. and Liu, T. L., "Least-Weight of Superplastically Formed Cores," Proceedings, Second ASCE Engineering Mechanics Specialty Conference, North Carolina State University, Raleigh, N.C., May 1977, pp. 440-443. Ueng, C.E.S. and Liu, T. L., "Least-Weight Analysis of a New Sandwich Core," Proceedings, 14th Annual Meeting of the Society of Engineering Science, Nov. 1977, Lehigh University, Bethlehem, Pa., pp. 273-283. Plantema, F. J., Sandwich Construction, John Wiley and Sons, New York, 1966. 8 Alien, H. G., Analysis and Design of Structural Sandwich Panels, Pergamon Press, New York, 1969. Kelsey, S., Gellately, R. A., and Clark, B. W., "The Shear Modulus of Foil Honeycomb Core," Aircraft Engineering, Vol. 30, Oct. 1958, pp. 294-302. Argyris, J. H., "Energy Theorems and Structural Analysis," Aircraft Engineering, Vol. 26, Oct.-Nov. 1954; Vol. 27, Feb., March, April, and May 1955; see also J. H. Argyris, Energy Theorems and Structural Analysis, Butterworth Scientific Publications, London, 1960.

Concentric tube resistojet life tested on hydrogen and ammonia propellants for use with biowaste propellants

Modele numerique pour les mouvements du fluide et le transfert de chaleur, le cylindre interieur etant chauffe et tournant

I commenting on a technical note by W. Zinman, Prof. Weymann referred to our work and incorrectly estimated our diaphragm-probe distance as 100 cm. As a consequence of this estimate, he concluded the following: " . . . that the two probes will measure a stationary state at x = 50 cm ahead of the shock front if the distance of the first probe from the diaphragm is larger than zc == 96 cm . . . It is, therefore, quite curious that Lederman and Wilson find stationary profiles in their shock tube." The over-all length of the driven section is 10 ft, or 305 cm, as stated in Ref. 3. The correct diaphragm-probe distance is 210 cm. Therefore, even according to Professor Weymann's own analysis, it is not at all "curious" that we found stationary profiles in our experiments.

R ECENTLY Leibovich has derived a stability criterion of density-stratified spiral flows between two concentric cylinders for axisymmetric disturbances. Here we have extended his discussion to nonaxisymmetric disturbances. Let (ur, UQ, uz) be the components of the velocity vector in a cylindrical (r, 9, z) coordinate system. The flowfield is described by ur = u(r, 0, z, f) ue = V(r) + v(r, 0, z, t) uz = W(r) + w(r, 0, z,t) p = P(r) + O(r, 0, z, t) ,0,z,i) (1) where p and p are density and pressure respectively. Here (O, V, W, P, p) describe the undisturbed flow and are arbitrary, and Q = (u, v, w, II, p J represents a small perturbation to which the basic flow is subjected. The perturbations Q are governed by the linear set of equations Lu-2(V/r)v = -(l/p)dn/dr + (V/r)Pl/p Lv + (D*V)u = -(\/pr)dn/d9 Lw + (D W}u = ( 1/p) dU/dz dz = 0 (2)