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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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Wind tunnel tests to determine subsonic stability and control effectiveness of straight and delta wing configurations on space shuttle booster
Fabrication and testing of one-third scale boron/epoxy tubular booster thrust structure
Space Shuttle abort stage separation wind tunnel tests of orbiter and booster vehicles - orbiter proximity data, Mach number 5
Space shuttle abort stage separation wind tunnel tests of orbiter and booster vehicles - orbiter proximity data, Mach number 3
Space shuttle abort stage separation wind tunnel tests of orbiter and booster vehicles - orbiter proximity data, Mach number 2
Wind tunnel stability tests of space shuttle model booster with G3-A orbiter
Aerodynamic force and moment coefficients for scale model of expendable second stage modified S-2 alone and mounted piggyback on space shuttle booster from Mach 0.6 to 4.96
Low speed wind tunnel tests of takeoff, landing, and cruise aerodynamic characteristics of space shuttle booster with exhaust effect simulation
Aerodynamic characteristics of scale model of space shuttle booster at cruise and landing speed of Mach 0.2
Static longitudinal, directional, and lateral characteristics and control surface effectiveness of scale model of space shuttle canard booster at Mach 0.26
Solid propellants based on low cost hydroxyl terminated polybutadiene binders meeting burning rate, mechanical properties and processing requirements for large booster motors
Frozen bipropellants as self supporting structural member for booster weight reduction, considering mechanical and thermal properties and melting rate requirement
A 0.015 scale model of a modified version of the MDAC space shuttle booster was tested in the Naval Ship Research and Development Center 7 x 10 foot transonic wind tunnel, to obtain force, static stability, and control effectiveness data. Data were obtained for a cruise Mach Number of 0.38, altitude of 10,000 ft, and Reynolds Number per foot of approximately 2 x one million. The model was tested through an angle of attack range of -4 deg to 15 deg at zero degree angle of sideslip, and at an angle of sideslip range of -6 deg to 6 deg at fixed angles of attack of 0 deg, 6 deg, and 15 deg. Other test variables were elevon deflections, canard deflections, aileron deflections, rudder deflections, wing dihedral angle, canard incidence angle, wing incidence angle, canard position, wing position, wing and canard control flap size and dorsal fin size.
Force tests on a 0.0035-scale model of the General Dynamics/Convair aerospace space shuttle B-15B-1 booster were conducted in the MSFC trisonic wind tunnel. The configuration has a low delta wing, all-movable delta-planform canard controls, and a single vertical tail. The test was devoted to investigating the effects of various configuration variables upon lateral-directional characteristics. These variables included wing dihedral, rudder flare, and body flap deflection. Yaw runs were made at angles of attack of 6, 10, 15, 25, 30, and 35 degrees. The Mach number range for this test was 1.20 to 4.96.
The results of the booster verification wind tunnel test are presented. These tests were conducted in a 14 x 14-inch trisonic wind tunnel utilizing a .0035 scale model. The nominal Mach numbers tested were 0.6, 0.9, 0.95, 1.0, 1.05, 1.20, 1.50, 2.0, 2.74, 3.00, 4.50 and 5.0. The angle of attack range was +5 to 40 deg. The yaw data was obtained over a range of -10 to +10 deg at fixed angles of attack of 0, 6, 15, 25, and 30 deg. The Reynolds number range was 4.2 to 6.9 million per foot. Results include elevon and canard effectiveness in pitch, and rudder, aileron, body flap, and tail effectiveness in yaw.
Experimental aerodynamic investigations were made in the Grumman 36-inch hypersonic wind tunnel on a .00435 scale model of the H-32 reusable space shuttle booster. The objectives of the test were to determine the static stability characteristics and control surface effectiveness at hypersonic speeds. Data were taken at M = 8.12 over a range of angles of attack between -5 and 85 deg at beta = 0 deg and over a range of side slip angles between -10 and 10 deg at alpha = 0 and 70 deg. Six component balance data and base-cavity pressure data were recorded.
Experimental aerodynamic investigations were conducted on a .003366-scale model of the Grumman space shuttle configuration mounted to a three (3) segmented solid propellant booster. These tests were conducted in the MSFC 14-inch trisonic wind tunnel over a Mach number range of 0.6 to 4.96. The purpose of the test was to determine the aerodynamic characteristics of this configuration. Aerodynamic data was taken over a nominal angle of attack and angle of sideslip of -10 degrees to 10 degrees at zero degrees beta and alpha respectively. In addition, data was obtained for the H-33 orbiter alone to supplement data from TWT 502 and TWT 503.
The .00429 scale model Titan 3 booster was mated with the DTO-7 space shuttle orbiter with drop tanks and tested for aerodynamic performance in a 14 x 14 inch trisonic wind tunnel. Six component aerodynamic force and moment data were measured on several variations of the above component in a launch configuration over a Mach number range from 0.6 to 3.48. Angle of attack ranged from -12 deg to 12 deg at 0 deg and -6 deg sideslip angle and sideslip angle ranged from -12 deg to 12 deg at 0 deg angle of attack. Date are presented in plotted form in both the stability and body axis system.