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Results for “SLENDER BODY”

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 127 records · Page 7
All sourcesNASA NTRSDOE OSTI
NASA NTRS1946

Flow over a slender body of revolution at supersonic velocities

The theory of small disturbances is applied to the calculation of the pressure distribution and drag of a closed body of revolution traveling at supersonic speeds. It is shown that toward the rear of the body the shape of the pressure distribution is similar to that for subsonic flow. For fineness ratios between 10 and 15 the theoretical wave drag is of the same order as probable values of the frictional drag.

FLOW VELOCITY, HIGH-SUPERSONIC↗
NASA NTRS1954

Aerodynamics of Slender Bodies at Mach Number of 3.12 and Reynolds Numbers from 2 x 10(exp 6) to 15 x 10(exp 6) IV : Aerodynamic Characteristics of Series of Four Bodies Having Near-parabolic Noses and Cylindrical Afterbodies

Pressure distributions and forces for a series of four bodies of revolution having nose-fineness ratios varying from 4 to 10 have been obtained and compared with theory for a Mach number of 3.12, a Reynolds number range of 2x10(sup)6 to 14x10(sup)6, and angles of attack from zero to 9 degrees. In general, a comparison of the experimental data with a second-order theory showed good agreement for the range of variables investigated.

BODIES - FITNESS RATIO↗
NASA NTRS1954

Aerodynamics of Slender Bodies at Mach Number of 3.12 and Reynolds Numbers from 2 x 10(exp 6) to 15 x 10(exp 6) V : Aerodynamic Load Distributions for a Series of Four Boattailed Bodies

Pressure distributions for a series of four boattailed bodies of revolution were obtained and compared with theory for a Mach number of 3.12, a Reynolds number range of 2 x 10 to 6th power to 14 x 10 to the 6th power, and angles of attack from zero to 9 degrees. Second-order theory adequately predicted the pressure distribution for regions free of the effects of cross-flow separation.

Moskowitz, Barry↗
NASA NTRS2018

Performance of Supersonic Parachutes behind Slender Bodies

NASA's ASPIRE (Advanced Supersonic Parachute Inflation ResearchExperiments) project is investigating the supersonic deployment, inflation andaerodynamics of full-scale disk-gap-band (DGB) parachutes. The first two flight tests werecarried out in October 2017 and March 2018, while a third test is planned for the fall of 2018. Inthese tests, Mars-relevant conditions are achieved by deploying the parachutes at high altitudesover Earth using a sounding rocket test platform. As a result, the parachute is deployed behind aslender body (roughly 1/6-th the diameter of the capsule that will use this parachute for descentat Mars). Because there is limited flight and experimental data for supersonic DGBs behindslender bodies, the development of the parachute aerodynamic models was informed by CFDsimulations of both the leading body wake and the parachute canopy. This presentation willdescribe the development of the pre-flight parachute aerodynamic models and compare preflightpredictions with the reconstructed performance of the parachute during the flight tests.Specific attention will be paid to the differences in parachute performance behind blunt andslender bodies.

Muppidi, Suman↗