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  • 1
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    Supersonic loads due to shuttle-orbiter/external-tank attachment structures (1983)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: A large variety of tests were conducted during development of the Space Shuttle to determine the strength, fatigue, and thermal characteristics of the thermal-protection system of the orbiter. The research and analysis carried out to accurately define and simulate the flow characteristics immediately ahead of the external tank attachment structures are described. The highest known acoustic pressure loads occur in these regions and tests to insure the ability of the titles to withstand these acoustic loads, plus those due to pressure gradient, were thought necessary. First flight-critical wind tunnel tests were therefore conducted in the Langley 8-Foot Transonic Pressure Tunnel (8-Ft. TPT), which simulated the time histories of Shuttle ascent loads on tile arrays bonded to structures which accurately duplicated those of the Shuttle. The time-varying free stream conditions were provided by controlling the deflection angle history of diffuser spoiler flaps in an automated way. Time histories of the critical load parameters imposed on the tile arrays in the tunnel are compared with those expected in flight.
    Keywords: SPACE TRANSPORTATION
    Type: Shuttle Performance: Lessons Learned, Part 1; p 95-138
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Surface step induced gap heating in the Shuttle Thermal Protection System (1984)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: Previously cited in issue 5, p. 606, Accession no. A83-16533
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Journal of Spacecraft and Rockets (ISSN 0022-4560); 21; 156-161
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Comparative aerodynamic study of two hypersonic cruise aircraft configurations derived from trade-off studies (1967)
    In:  Other Sources
    Details
    Publication Date: 2016-06-07
    Keywords: GENERAL
    Type: Conf. on Hypersonic Aircraft Technol.; p 45-62
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Optimum transonic wind tunnel (1986)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The optimum facility to complement existing high Reynolds number transonic wind tunnels is discussed. It is proposed that the facility be cryogenic, have a total pressure of five atmospheres or less, and have a test section on the order of 4- to 5-meters square. The large size is to accommodate complicated models such as those used in propulsion testing. It is suggested that magnetic suspension and wall interference minimization and correction procedures be used. Simplicity of initial design is stressed as a means of providing for future growth opportunities.
    Keywords: RESEARCH AND SUPPORT FACILITIES (AIR)
    Type: AIAA PAPER 86-0755
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    Filler bar heating due to stepped tiles in the shuttle orbiter thermal protection system (1983)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: An analytical study was performed to investigate the excessive heating in the tile to tile gaps of the Shuttle Orbiter Thermal Protection System due to stepped tiles. The excessive heating was evidence by visible discoloration and charring of the filler bar and strain isolation pad that is used in the attachment of tiles to the aluminum substrate. Two tile locations on the Shuttle orbiter were considered, one on the lower surface of the fuselage and one on the lower surface of the wing. The gap heating analysis involved the calculation of external and internal gas pressures and temperatures, internal mass flow rates, and the transient thermal response of the thermal protection system. The results of the analysis are presented for the fuselage and wing location for several step heights. The results of a study to determine the effectiveness of a half height ceramic fiber gap filler in preventing hot gas flow in the tile gaps are also presented.
    Keywords: SPACE TRANSPORTATION
    Type: Shuttle Performance: Lessons Learned, Pt. 2; p 891-912
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Analysis of gap heating due to stepped tiles in the shuttle thermal protection system (1983)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Analytical methods used to investigate entry gap heating in the Shuttle orbiter thermal protection system are described. Analytical results are given for a fuselage lower-surface location and a wing lower-surface location. These are locations where excessive gap heating occurred on the first flight of the Shuttle. The results of a study to determine the effectiveness of a half-height ceramic fiber gap filler in preventing hot-gas flow in the tile gaps are also given.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TP-2209 , L-15636 , NAS 1.60:2209
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    GEMPAK: An arbitrary aircraft geometry generator (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A computer program, GEMPAK, has been developed to aid in the generation of detailed configuration geometry. The program was written to allow the user as much flexibility as possible in his choices of configurations and the detail of description desired and at the same time keep input requirements and program turnaround and cost to a minimum. The program consists of routines that generate fuselage and planar-surface (winglike) geometry and a routine that will determine the true intersection of all components with the fuselage. This paper describes the methods by which the various geometries are generated and provides input description with sample input and output. Also included are descriptions of the primary program variables and functions performed by the various routines. The FORTRAN program GEMPAK has been used extensively in conjunction with interfaces to several aerodynamic and plotting computer programs and has proven to be an effective aid in the preliminary design phase of aircraft configurations.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TP-1022 , L-11666
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    Low-density, leading-edge bluntness, and ablation effects on wedge-induced laminar boundary layer separation at moderate enthalpies in hypersonic flow (1968)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Low density, leading edge bluntness, and ablation effects on wedge induced laminar boundary layer separation at moderate enthalpies in hypersonic flow
    Keywords: FLUID MECHANICS
    Type: NASA-TN-D-4829
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    Predictions of entry heating for lower surface of shuttle orbiter (1983)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A broad base of thermocouple and phase change paint data was assembled and correlated to the nominal design 14414.1 and proposed STS-1 (first flight of the space transportation system) entry trajectories. Averaged data from phase change paint tests compared favorably with thermocouple data for predicting heating rates. Laminar and turbulent radiation equilibrium heating rates were computed on the lower surface of the Shuttle orbiter for both trajectories, and the lower surface center line results were compared both with aerodynamic heating design data and with flight values from the STS-1 and STS-2 trajectories. The peak laminar heating values from the aerodynamic heating design data book were generally 40 to 60 percent higher than the laminar estimates of this study, except at the 55 percent location of maximum span where the design data book values were less than 10 percent higher. Estimates of both laminar and turbulent heating rates compared favorably with flight data.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-TM-84624 , L-15556 , NAS 1.15:84624
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    Arbitrary aircraft-geometry generator (1979)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Computer program helps designers to generate detailed configuration geometry with much flexibility in choices of configurations and details of description. Input requirements, program turnaround time, and costs are kept low. It consists of routines that generate fuselage and planar-surface (winglike) geometries and routine that determines true intersection of all components with fuselage.
    Keywords: MECHANICS
    Type: LAR-12515 , NASA Tech Briefs (ISSN 0145-319X); 4; 2; P. 267
    Format: text
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    NASA TECHNICAL REPORTS
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