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Results for “SLENDER CONE”

Search indexed NASA NTRS and DOE OSTI research on propulsion, heat transfer, battery materials and energy systems. Follow report and document links to the original sources.

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At least 19 records
All sourcesNASA NTRSDOE OSTI
NASA NTRS1972

Experimental damping-in-pitch of two slender cones at Mach 2 and incidences up to 30 deg

Oscillatory experiments were performed on two slender cones at Mach 2 and incidences up to 30 deg, using three different experimental arrangements. The damping-in-pitch was found to remain constant at incidences of up to a value approximately corresponding to the cone semi-angle, after which an almost linear increase with incidence was noted. The results obtained with the different techniques were in very good agreement up to an incidence of 15 deg and in some cases up to 25 deg.

Iyenger, S.↗
NASA NTRS1973

Unsteady aerodynamic loads on slender cones at free-stream Mach numbers from 0 to 22.

Results of an experimental study to determine the flow-induced unsteady aerodynamic loads on slender cones at very high Mach numbers. Experiments on 8-deg half-angle-cone/flat-base configurations were conducted at free-stream Mach numbers of 6 and 15 and Reynolds numbers corresponding to shuttle reentry conditions. The flow facilities used were the H-3 Hypersonic Facility (Mach 6) and the Longshot Free Piston Tunnel (Mach 15) of the Von Karman Institute for Fluid Dynamics in Rhode-St.-Genese, Belgium. With these test results and pertinent results from other research efforts, data were available at free-stream Mach numbers of 0.67, 2.5, 3, 4, 6, 15, and 22, so that empirical expressions could be developed for the Mach number dependence (1) of the overall fluctuating pressure under an attached turbulence boundary layer and (2) of the overall fluctuating base pressure.

Heller, H. H.↗
NASA NTRS1972

Hypersonic rarefied flow over sharp slender cones

Drag, heat transfer, and number flux were measured on sharp cones in the near free, molecule flow regime, and the results were compared with available Monte Carlo calculations. In general, the calculations predicted the magnitude of the data; however, the heat transfer and drag increased with increasing Knudsen number at a faster rate than predicted. Also the drag coefficients measured for the slender cones at high Knudsen number were higher than predicted for free molecule flow. These disagreements between theory and experiment could possibly be attributed to the simplicity of the surface interaction laws assumed in the theory. Reynolds analogy factors obtained from the experimental measurements agreed with free-molecule values and also with that obtained by the Monte Carlo technique.

Kussoy, M. I.↗
NASA NTRS1972

Calculation of linearized supersonic flow over slender cones of arbitrary cross section

Supersonic linearized conical-flow theory is used to determine the flow over slender pointed cones having horizontal and vertical planes of symmetry. The geometry of the cone cross sections and surface velocities are expanded in Fourier series. The symmetry condition permits the uncoupling of lifting and nonlifting solutions. The present method reduces to Ward's theory for flow over a cone of elliptic cross section. Results are also presented for other shapes. Results by this method diverge for cross-sectional shapes where the maximum thickness is large compared with the minimum thickness. However, even for these slender-body shapes, lower order solutions are good approximations to the complete solution.

Mascitti, V. R.↗