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  • 1
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    Measured and predicted heating distributions for biconics at Mach 10 (1986)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Description: Laminar heating distributions have been measured on a 1.9 percent scale model of a generic aeroassisted vehicle taking the shape of a spherically blunted, 13-deg/7-deg biconic whose forecone section is bent upward (by 7 deg) to furnish self-trim capability at a 20-deg angle-of-attack. The results thus obtained were compared with data gathered for a straight biconic. While no Reynolds number effect on heating was noted on the windward side of the forecone, the opposite was true of the leeward side, where a Reynolds number increase caused circumferential flow separation at lower angles of attack. Generally, windward heating was predicted to within 10 percent with a computer code solving the steady, three-dimensional parabolized Navier-Stokes equations.
    Keywords: AERODYNAMICS
    Type: Journal of Spacecraft and Rockets (ISSN 0022-4650); 23; 251-258
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Aerothermodynamics and transition in high-speed wind tunnels at NASA Langley (1990)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Description: The evolutionary development of subsonic, supersonic, and hypersonic wind tunnels for the study of aerodynamic, aerothermodynamic, and fluid-dynamic characteristics of the flow about models, including transition from laminar to turbulent boundary layers, is discussed. Currently, three supersonic and seven hypersonic wind tunnels are operational at Langley, and two additional tunnels are scheduled to become operational by 1990. In the present work, an effort is made to provide a 'tour'of selected supersonic and hypersonic wind tunnels at NASA-Langley used for aerodynamic and aerothermodynamic testing of models, and to present the evolution of quiet-tunnel technology at this facility over the last decade. It is noted that upgrades to the hypersonic facilities complex are underway in order to provide the high flow quality and improved data accuracy required to calibrate advanced computational fluid-dynamic computer codes. Also to be provided are increased productivity required for configuration development and improved reliability to support major hypersonic programs in an efficient and timely manner.
    Keywords: AERODYNAMICS
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    NASA TECHNICAL REPORTS
  • 3
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    Shock shapes of blunt bodies in hypersonic helium, air, and CO2 flows (1974)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: A primary factor governing hypersonic flowfield characteristics of blunt vehicles entering planetary atmospheres is the normal shock density ratio. Hence, a means of duplicating or simulating the high density ratios experienced during planetary entry is needed. One facility having the capability of generating a range of hypersonic-hypervelocity flow conditions in arbitrary test gases is the expansion tube. Preliminary shock shape results obtained in the Langley 6-in. expansion tube at hypersonic conditions are presented. Normal shock density ratios from approximately 4 to 19 were generated using helium, air, and CO2 test gases at freestream velocities from 5 to 7 km/sec. Test models were a flat-faced cylinder and the Viking aeroshell.
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 12; Mar. 197
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Refinement of an 'alternate' method for measuring heating rates in hypersonic wind tunnels (1985)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Description: Recently obtained hypersonic wind tunnel results are presented which resolve the principal uncertainty associated with the use of thin film gages on substrates of the glass ceramic substance designated MACOR.THe uncertainty is with respect to both MACOR's thermal properties and the variation of these properties with temperature. The relatively large influence of shock strength on stagnation point heating at low Reynolds numbers is illustrated.
    Keywords: RESEARCH AND SUPPORT FACILITIES (AIR)
    Type: AIAA Journal (ISSN 0001-1452); 23; 810-812
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    NASA TECHNICAL REPORTS
  • 5
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    Flow characteristics in an expansion tunnel as inferred from velocity measurements (1977)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: A photoionization technique was used to study flow characteristics in an expansion tunnel. Vertical surveys of the axial component of flow velocity just downstream from the nozzle exit were obtained, and estimates of freestream density were inferred from the velocity measurement technique. The pitot pressure was measured and compared to the average axial component of velocity as a function of time for the two cases when air and CO2 were used as test gases. Vertical velocity and static density profiles at the nozzle exit are presented for the case when CO2 was used as test gas. Experimental results were used to determine the diameter and uniformity of the test core at the nozzle exit and the duration of the quasi-steady flow period. These data are relevant to evaluation of the suitability of operating an expansion tube as an expansion tunnel. The expansion tunnel is an expansion tube with a conical nozzle positioned at the exit of the acceleration section, so that nozzle entrance flow conditions are hypersonic and characterized by hypervelocity.
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 15; Sept
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    NASA TECHNICAL REPORTS
  • 6
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    Flow-establishment times for blunt bodies in an expansion tube (1975)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Flow establishment results are presented as obtained from shock standoff distance, pressure, and heat transfer measurements in the Langley expansion tube. The models tested were flat-faced cylinders with varying radius and a sphere with a constant radius, and they were positioned at the acceleration section exit and tested in the open jet at zero angle of attack. The experimental results were obtained as spinoff from various studies using helium, air, and CO2 test gases at freestream velocities in the range 5-7 km/sec. Time histories of shock detachment distance illustrate that the shock formation about the smaller-radii flat-faced cylinders and the sphere is symmetrical, whereas a complex, asymmetric formation is observed for the larger-radii cylinders. Flow is shown to establish more readily about the sphere than a flat-faced cylinder of the same diameter. A quasi-steady flow exists about relatively large blunt models during two-thirds of the approximate 250-microsec expansion tube test period.
    Keywords: RESEARCH AND SUPPORT FACILITIES (AIR)
    Type: AIAA Journal; 13; Dec. 197
    Format: text
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    NASA TECHNICAL REPORTS
  • 7
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    Heating distributions for a 0.006-scale Shuttle Orbiter over a range of hypersonic flow conditions (1984)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: Previously cited in issue 15, p. 2342, Accession no. A82-31855
    Keywords: AERODYNAMICS
    Type: Journal of Spacecraft and Rockets (ISSN 0022-4650); 21; 120-122
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    NASA TECHNICAL REPORTS
  • 8
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    Pressure distributions and shock shapes for a bent-nose biconic at incidence (1982)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: Initial results of a NASA study of the lift-drag characteristics of a 12.84/7 deg biconic model intended for airbraking during atmospheric entry of probes to Mars, Venus, Saturn, and Titan are reported. Pressure distributions and shock shapes were measured in the Langley 20 in. Mach 6 tunnel with the spherically blunted bent-nose model set at angles from 0-25 deg. Pressure distributions and shock shapes where computed using the STEIN flowfield code, which features a MacCormack scheme to integrate the three-dimensional Euler equations, the Rankine-Hugoniot jump conditions to model shock waves as discontinuities, and requires a supersonic condition at every step. A comparison was made between measured and predicted values. The leeward shock angle was found to be predictable to within 3% for all angles of attack, while parabolized Navier-Stokes equations are regarded as offering more accurate results than the STEIN code for surface pressure distributions.
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 20; Aug. 198
    Format: text
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    NASA TECHNICAL REPORTS
  • 9
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    Expansion tunnel performance with and without an electromagnetically opened tertiary diaphragm (1977)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: A study was conducted to examine the effect of synchronization of an electromagnetically opened tertiary diaphragm with flow arrival at the diaphragm on the pitot pressure measured at the test section of an expansion tunnel. The effect of tertiary diaphragm pressure ratio (ratio of initial nozzle pressure to quiescent acceleration section pressure) on the pitot pressure time history is also determined. The inadequacy of a pressure transducer protection arrangement used in previous expansion tube and expansion tunnel tests was revealed.
    Keywords: RESEARCH AND SUPPORT FACILITIES (AIR)
    Type: AIAA Journal; 15; July 197
    Format: text
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    NASA TECHNICAL REPORTS
  • 10
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    Hypersonic aerodynamic/aerothermodynamic testing capabilities at Langley Research Center (1992)
    In:  Other Sources
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    Publication Date: 2019-06-28
    Description: Capabilities of the Langley Hypersonic Facilities Complex that consists of nine blowdown-to-vacuum wind tunnels are reviewed. These tunnels complement one another to provide ranges of Mach number from 6 to 20, unit Reynolds number from 0.03 to 40 million per ft, and normal shock density ratio from 2 to 12. Topics under consideration include the basic components of each facility, status, and upgrades recently performed; instrumentation and testing techniques routinely used to measure forces and moments, surface pressures, surface temperature-time histories, flow properties within the shock layer about the model via survey probes, and flow visualization; and data acquisition systems and upgrades performed via a NASA revitalization program.
    Keywords: RESEARCH AND SUPPORT FACILITIES (AIR)
    Type: AIAA PAPER 92-3937
    Format: text
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