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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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At least 145 records · Page 8
All sourcesNASA NTRSDOE OSTI
NASA NTRS1972

Aerodynamic static stability characteristics, fin effectiveness, and fin location of the MSFC 33-foot pressure fed booster at high angles of attack

Experimental aerodynamic investigations were conducted in the NASA/MSFC 14 x 14 inch trisonic wind tunnel during early February 1972 on a 0.00280 scale model of the MSFC 33-foot diameter space shuttle pressure fed booster configuration. The basic configuration tested was a 40 deg cone/cylinder/7 deg frustrum designated the MSFC 33 foot pressure fed booster. Six component aerodynamic force and moment data were recorded over a Mach number range from 0.9 to 5.0 at angles of attack from +20 to +90 at 0 deg sideslip and over a sideslip range from -10 to +10 deg at 30, 50, 60 and 80 deg angles of attack. Primary configuration variables were fin deflection angle and vertical position on the frustrum.

Hamilton, T.↗
NASA NTRS1972

Some effects of external stores on the static stability of fighter airplanes

Fighter airplanes may have a seemingly limitless number of external store arrangements. Some practical considerations and some aerodynamic considerations must be taken into account in the arrangements of the external stores. The nature of the problems concerning the type of store arrangement involved and the type of airplane on which the stores are installed are reported.

Spearman, M. L.↗
NASA NTRS1972

Aerodynamic static stability characteristics of the MSFC 33-foot pump fed booster at high angles of attack

Experimental aerodynamic investigations were conducted in the 14-inch trisonic wind tunnel during early February 1972 on a 0.00340 scale model of the 33-foot diameter space shuttle pump fed booster configuration. The basic configuration tested was a 40-deg cone/cylinder. Six component aerodynamic force and moment data were recorded over a Mach number range from 0.6 to 5.0, angles-of-attack from 50 to 90 deg at 0 deg sideslip and over a sideslip range from -10 to +10 deg at 60 and 80 deg angles-of-attack. Primary configuration variables were fin area and body cutout size.

Hamilton, T.↗
NASA NTRS1972

Aerodynamic static stability and control effectiveness of a parametric shuttle launch configuration

Experimental aerodynamic investigations were conducted in the NASA/MSFC 14-inch Trisonic Wind Tunnel on a 0.004-scale model of the NR ATP baseline Shuttle launch configuration. The test model consisted of the NR ATP baseline orbiter, external tank, and SRB's with nozzles. Six component aerodynamic force and moment data were recorded over an angle of attack range from minus 10 deg to 10 deg at zero degrees sideslip and angle of sideslip range of minus 10 deg to 10 deg at zero angle of attack for a Mach range of 0.6 to 4.96. Rudder flare was constant at 10 deg during the entire test. The purpose of the test was to define the performance, stability, and control characteristics of the launch configuration as well as to investigate the buildup effect of two geometrical parameters.

Ramsey, P. E.↗
NASA NTRS1974

Static stability characteristics of the space shuttle external tank (MSFC model 458) during reentry in the MSFC 14-inch TWT (TA1F)

Data obtained in a wind tunnel test of a 0.003-scale modified MCR 0200 space shuttle external tank (ET) model tested at reentry conditions in the MSFC 14-inch trisonic wind tunnel are presented. This test is a continuation of a series of tests conducted to evaluate the aerodynamic characteristics of the ET during reentry. Three Mach numbers were investigated: 1.96, 3.48, and 4.96. The angle-of-attack range was -10 deg to 190 deg. Eight roll positions of the model from 0 deg to 315 deg were tested. The run schedule consisted of 162 runs. No. 120 grit was applied randomly over the model throughout the test.

Ramsey, P. E.↗
NASA NTRS1975

Reentry static stability characteristics of a (Model 471) .005479-scale 146-inch solid rocket booster tested in the NASA/MSFC 14 by 14 inch TWT (SA8F)

A force test of a scale model of the Space Shuttle Solid Rocket Booster was conducted in a trisonic wind tunnel. The model was tested with such protuberances as a camera capsule, electrical tunnel, attach rings, aft separation rockets, ET attachment structure, and hold-down struts. The model was also tested with the nozzle at gimbal angles of 0, 2.5, and 5 degrees. The influence of a unique heat shield configuration was also determined. Some photographs of model installations in the tunnel were taken and are included. Schlieren photography was utilized for several angles of attack.

Johnson, J. D.↗
NASA NTRS1977

Subsonic longitudinal and lateral directional static stability characteristics of a variable sweep fighter configuration employing various control surface deflections at angles of attack of 0 deg to 50 deg and large sideslip angles

A variable sweep fighter configuration with the wing in the 22 deg sweep position having leading edge slats and trailing edge flaps on the outboard panels was tested at a Mach number of 0.15 in the Langley 7- by 10-foot high speed tunnel. The angle of attack range was 0 deg to 50 deg and the sideslip angle range was -20 deg to 20 deg. Pitch, roll, and yaw control effectiveness were studied as well as the effects of spoilers. The data are presented without analysis.

Jarrett K Huffman↗
NASA NTRS1980

Baroclinic instability with variable static stability - A design study for a spherical atmospheric model experiment

The effect of a radially-variable, dielectric body force, analogous to gravity on baroclinic instability for the design of a spherical, synoptic-scale, atmospheric model experiment in a Spacelab flight is investigated. Exact solutions are examined for quasi-geostrophic baroclinic instability in which the rotational Froude number is a linear function of the height. Flow in a rotating rectilinear channel with a vertically variable body force without horizontal shear of the basic state is also discussed.

Giere, A. C.↗
NASA NTRS1984

L-1011 testing with relaxed static stability

Wind tunnel and flight tests indicate that fuel savings of 2 percent can be achieved by center of gravity (C.G.) management for an L-1011 with the current wing configuration. The normal c.b. location is at 25 percent mean aerodynamic center (MAC). The maximum fuel saving occurs for a C.G. location of 35 percent MAC. However, flight at 35 percent requires that the C.G. range be extended aft of the 35-percent point. Flight at C.G. locations aft or 35 percent requires a pitch active control system (PACS) so that handling qualities are not significantly degraded. The development of this PACS is discussed.

Rising, J. J.↗
NASA NTRS1985

A simple model for the interaction between vertical eddy heat fluxes and static stability

A numerical model for studying the interaction of vertical eddy heat fluxes and vertical temperature structure in midlatitude regions is described. The temperature profile for the model was derived from calculations of the equilibrium among heating rates in simplified representations of large-scale vertical eddy heat flux, moist convection and radiation. An eddy flux profile is calculated based on the quasi-geostrophic, liner baroclinic instability of a single wave. Model equilibrium states for summer and winter conditions are compared with observations, and the results are discussed in detail.

Gutowski, W. J., Jr.↗