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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 181 records · Page 10

All sources NASA NTRS DOE OSTI

NASA NTRS1971

Space Shuttle: Stability and control effectiveness of the MDAC parametric delta canard booster at mach 0.38. Volume 4: Surface effectiveness, model buildup, and directional stability at high angles of attack

For abstract, see N72-10933.

Bradley, D.↗

NASA NTRS1971

Space Shuttle: Stability and control effectiveness of the MDAC parametric delta canard booster at Mach 0.38. Volume 3: Wing parametric variations: Incidence and dihedral

For abstract, see N72-10933.

Bradley, D.↗

NASA NTRS1971

Space shuttle: Stability and control effectiveness of the MDAC parametric delta canard booster at Mach 0.38. Volume 2: Wing parametric variations, size and location

For abstract, see N72-10933.

Bradley, D.↗

NASA NTRS1972

Space shuttle: Aerodynamic heating tests of the MDAC delta wing orbiter and canard booster

Design of an efficient thermal protection system for the space shuttle orbiter and booster is discussed, based on knowledge of the thermal environment to be experienced by the vehicles in all flight phases. The complex configurations of these vehicles limit the level of confidence which can be associated with purely analytical thermal environment predictions. Tests were conducted during April and May 1971 using an orbiter and booster model at a 96-in. hypersonic shock tunnel. Both models were tested separately as well as together. A sufficiently large range in Reynolds number was covered so that laminar, transitional, and turbulent data could be obtained.

Andresen, T. L.↗

NASA NTRS1973

Space shuttle: Pressure investigation of a space shuttle launch configuration consisting of a delta-wing orbiter and a swept-wing booster with canard and tip fins (M equals 0.6 to 1.3). Volume 1, part B: Booster data

For abstract, see .

Rampy, J. M.↗

NASA NTRS1973

Space shuttle: Pressure investigation of a space shuttle launch configuration consisting of a delta-wing orbiter and a swept-wing booster with canard and tip fins (M equals 0.6 to 1.3). Volume 2: Orbiter data

For abstract, see

Rampy, J. M.↗

NASA NTRS1978

Effect of twist and camber on the low-speed aerodynamic characteristics of a powered close-coupled wing-canard configuration

A series of wind-tunnel tests were conducted in a V/STOL tunnel to determine the low-speed longitudinal aerodynamic characteristics of a powered close-coupled wing/canard fighter configuration. The data was obtained for a high angle-of-attack maneuvering configuration and a takeoff and landing configuration. The data presented in tabulated form are intended for reference purposes.

Paulson, J. W., Jr.↗

NASA NTRS1983

Experimental wing and canard jet-flap aerodynamics

The effects of upper surface blowing on the aerodynamics of a 1/2-span wing/body/canard configuration are shown. The results expand a data base that is limited at high subsonic Mach numbers (M = 0.6-0.9), data that are needed if computational techniques are to be developed for the complex flowfields generated by jet blowing. At lift coefficients greater than about 1.0, the thrust removed drag coefficient was lower with jet blowing than without jet blowing. This favorable effect increased with increasing jet blowing coefficient, and, for a fixed coefficient, simultaneous wing/canard jet blowing was slightly more effective than blowing either surface alone.

Smeltzer, D. B.↗

NASA NTRS1984

Aerodynamic design optimization trim analysis of canard conventional configurations

Previously cited in issue 05, p. 594, Accession no. A83-16490

Keith, M. W.↗

NASA NTRS1986

Aerodynamic Prediction for Supersonic Canard-Tail Missiles

LRCDM2 computer program developed to calculate pressure distribution at points on surfaces of complete supersonic missile. Missile comprises up to two finned sections attached to axisymmetric body of circular cross section. Includes effects of vortex shedding due to forebody and forward fins, providing more accurate rolling moments. LRCDM2 written in FORTRAN IV.

Dillenius, M. F.↗

NASA NTRS1985

Aerodynamic characteristics of a propulsive wing-canard concept at STOL speeds

A full span model of a wing/canard concept representing a fighter configuration has been tested at STOL conditions in the NASA Langley 4 x 7 meter tunnel. The results of this test are presented, and comparisons are made to previous data of the same configuration tested as a semispan model. The potential of the propulsive wing/canard to develop very high lift coefficients was investigated with several nozzle spans (nozzle aspect ratios). Although longitudinal trim was not accomplished with the blowing distributions and configurations tested, the propulsive wing/canard appears to offer an approach to managing the large negative pitching moments associated with trailing edge flap blowing. Also presented are data showing the effects of large flap deflections and relative wing/canard positions. Presented in the appendix to the report are limited lateral-directional and ground effects data, as well as wing downwash measurements.

Stewart, V. R.↗

NASA NTRS1986