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Blackstock, T. A.

Publications and source records attributed to Blackstock, T. A..

8 records
All sourcesNASA NTRSDOE OSTI
NASA NTRS1984

Fine-cut bluntness effects on the hypersonic static stability of a 10 degree cone

A systematic wind-tunnel investigation has been performed on a series of spherically blunted 10-degree cones to determine Mach number and angle-of-attack effects on the hypersonic static stability. The cones, which range in nose-to-base radius ratios from 0 to 0.5, have been tested from -4 to 20 degrees angle of attack at Mach numbers of 6 and 10 in air and 20 in helium. Relatively large excursions in the center-of-pressure location were observed for small changes in cone nose bluntness. The movement of the center of pressure was also noted to become more pronounced as Mach number increased; increases in angle of attack tended to lessen the magnitude of these excursions. Computational predictions of basic aerodynamic coefficients as well as the center-of-pressure locations using both viscous and inviscid theory compare very well with the experimental data.

Bryan, M. D.↗
NASA NTRS1983

Space Shuttle third flight /STS-3/ entry RCS analysis

Flight data obtained from three Space Transportation System orbiter entries (STS-1, 2, and 3) are processed and analyzed to determine the roll interactions caused by the firing of the entry reaction control system (RCS). Comparisons between the flight-derived parameters and the predicted derivatives without interaction effects are made. The flight-derived RCS Plume flow-field interaction effects are independently deduced by direct integration of the incremental changes in the wing upper surface pressures induced by RCS side thruster firings. The separately obtained interaction effects are compared to the predicted values and the differences are discussed.

Scallion, W. I.↗
NASA NTRS1983

An experimental investigation of control surface effectiveness and real-gas simulation for biconics

Aerodynamic coefficients, pressure distributions, and oil-flow patterns measured on spherically blunted, 13 degrees/7 degrees on-axis and bent biconics at Mach 6 and 10 in air are compared. Angle of attack, referenced to the axis of the aft cone, was varied from zero to 40 degrees. The effect of deflection of base-mounted flaps on aerodynamic characteristics was examined at Mach 10. Real-gas effects on aerodynamic coefficients, pressure distributions and shock detachment distance were simulated by testing the biconic models in Mach 6 air and Mach 6 CF4 flows. (Density ratio equal to 5.3 for air and 12 for CF4.) The on-axis biconic is stable but cannot be trimmed at angles of attack above zero with the assumed center of gravity and flap configuration. Flaps on the bent biconic produced a stable and trim configuration for angles of attack from zero to 23 degrees. A significant effect of density ratio on aerodynamic coefficients, pressure distribution, and shock detachment distance was observed.

Miller, C. G.↗
NASA NTRS1977

Experimental verification of the technique for measurement of ablation on the GASJET nose tip

The GASJET nose tip is proposed to reduce the erosion at the apex of a missile nose flying at hypersonic speeds through a rain storm as it reenters the atmosphere. A forward facing sonic jet is directed through the tip introducing a secondary counter-flow which displaces the bow shock and blankets the tip with a protective layer of relatively cool gas. Wind tunnel experiments are described which proved the validity of measuring nose recession in flight by recording the pressure in the blast tube supplying the GASJET.

Donohoe, J. C.↗
NASA NTRS1973

Hypersonic performance, stability and control characteristics of a .0075 scale model Rockwell International 089B-139B orbiter configuration

An investigation was made in the Langley Continuous Flow Hypersonic Tunnel at a Mach number of 10.3 to study the hypersonic aerodynamic characteristics of a Rockwell International shuttle orbiter configuration. Tests were made at a Reynolds number of 790,000 x 106 based on body length with an angle-of-attack range of 10 to 35 deg and sideslip variations of +1 to -9 deg. The effects of elevon and body flap deflection were investigated.

Powell, R. W.↗