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  • 1
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    Buffeting tests in a cryogenic windtunnel (1995)
    In:  Other Sources
    Details
    Publication Date: 2011-08-24
    Description: Measurements of wing buffeting, using root strain gages, were made in the NASA Langley 0.3 m cryogenic wind tunnel to refine techniques which will be used in larger cryogenic facilities such as the United States National Transonic Facility (NTF) and the European Transonic Wind Tunnel (ETW). The questions addressed included the relative importance variations in frequency parameter and Reynolds number, the choice of model material (considering both stiffness and damping) and the effects of static aeroelastic distortion. The main series of tests was made on three half models of slender 65 deg delta wings with a sharp leading edge. The three delta wings had the same planform but widely differing bending stiffnesses and frequencies (obtained by varying both the material and the thickness of the wings). It was known that the steady flow on this configuration would be insensitive to variations in Reynolds number. On this wing at vortex breakdown the spectrum of the unsteady excitation is unusual, having a sharp peak at particular frequency parameter. Additional tests were made on one unswept half-wing of aspect ratio 1.5 with an NPL 9510 aerofoil section, known to be sensitive to variations in Reynolds number at transonic speeds. The test Mach numbers were M = 0.21 and 0.35 for the delta wings and to M = 0.30 for the unswept wing. On this wing the unsteady excitation spectrum is fairly flat (as on most wings). Hence correct representation of the frequency parameter is not particularly important.
    Keywords: AERODYNAMICS
    Type: Aeronautical Journal (ISSN 0001-9240); 99; 981; p. 1-14
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Further buffeting tests in a cryogenic wind tunnel (1992)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Further measurements of buffeting, using wing-root strain gauges, were made in the NASA Langley 0.3 m Cryogenic Wind Tunnel to refine techniques which will be used in larger cryogenic facilities such as the United States National Transonic Facility (NTF) and European Transonic Wind Tunnel (ETW). The questions addressed included the relative importance of variations in frequency parameter and Reynolds number, the choice of model material (considering both stiffness and damping) and the effects of static aeroelastic distortion. The main series of tests was made on half models of slender 65 deg delta wings with a sharp leading edge. The three delta wings had the same planform but widely different bending stiffness and frequencies (obtained by varying both the material and the thickness of the wings). It was known that the flow on this configuration would be insensitive to variations in Reynold number. Additional tests were made on one unswept half-wing of aspect ratio 1.5 with an NPL 9510 aerofoil section, known to be sensitive to variations in Reynolds number at transonic speeds. For brevity the test Mach numbers were restricted to M = 0.21 and 0.35 for the delta wings and to M = 0.30 for the unswept wing.
    Keywords: AERODYNAMICS
    Type: NASA-TM-107621 , NAS 1.15:107621 , RAE-TM-AERO-2231
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Status of wind tunnel magnetic suspension research (1985)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: This paper reports the status of the NASA Langley Research Center program aimed at the development of the technology required for large-scale Magnetic Suspension and Balance Systems. The use of magnetic suspension of the model in a wind tunnel is seen to be the only viable method to eliminate aerodynamic interference problems arising with mechanical model-supports. The two small-scale magnetic suspension systems in operation at Langley are the only ones now active in the U.S. The general features and capabilities of these two systems and all of the ongoing research in the use of magnetic suspension are described.
    Keywords: RESEARCH AND SUPPORT FACILITIES (AIR)
    Type: SAE PAPER 851898
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Dynamic Stability Instrumentation System (DSIS). Volume 1: Hardware description (1994)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This paper is a hardware description manual for the Dynamic Stability Instrumentation System that is used in specific NASA Langley wind tunnels. The instrumentation system performs either a synchronous demodulation or a fast Fourier transform on dynamic balance strain gage signals, and ultimately computes aerodynamic coefficients. The DSIS consists of a double rack of instruments, a remote motor-generator set, two special stings each with motor driven shafts, and specially designed balances. The major components in the instrumentation rack include a personal computer, digital signal processor microcomputers, computer-controlled signal conditioners, function generator, digital multimeter, and an optional fast Fourier transform analyzer.
    Keywords: COMPUTER PROGRAMMING AND SOFTWARE
    Type: NASA-TM-109160-VOL-1 , NAS 1.15:109160-VOL-1
    Format: application/pdf
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  • 5
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    Aerodynamic force measurements with a strain-gage balance in a cryogenic wind tunnel (1983)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Aerodynamic force measurements on a generalized 75 deg delta wing model with sharp leading edges were made with a three component internal strain gage balance in a cryogenic wind tunnel at stagnation temperatures of 300 K, 200 K, and 110 K. The feasibility of using a strain gage balance without thermal control in a cryogenic environment as well as the use of electrical resistance heaters, an insulator between the model and the balance, and a convection shield on the balance was investigated. Force and moment data on the delta wing model as measured by the balance are compared at the different temperatures while holding constant either the Reynolds number or the tunnel stagnation pressure. Tests were made at Mach numbers of 0.3 and 0.5 and at angles of attack up to 29 deg. The results indicate that it is feasible to acquire accurate force and moment data while operating at steady state thermal conditions in a cryogenic wind tunnel, either with or without electrical heaters on the balance. Within the limits of the balance accuracy, there were no apparent Reynolds number effects on the aerodynamic results for the delta wind model.
    Keywords: AERODYNAMICS
    Type: NASA-TP-2251 , L-15685 , NAS 1.60:2251
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Preliminary results of buffet tests in a cryogenic wind tunnel (1981)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Buffet tests of two wings with different leading-edge sweep show that it is feasible to use the standards wing root bending moment technique in a cryogenic wing tunnel. The results for the 65 deg sweep delta wing indicate the importance of matching the reduced frequency parameter in model tests for planforms which are sensitive to reduced frequency parameter if quantitative buffet measurements are required. The unique ability of a pressurized cryogenic wind tunnel to separate the effects of Reynolds number and of aeroelastic distortion by variations in the tunnel stagnation temperature and pressure was demonstrated.
    Keywords: AERODYNAMICS
    Type: NASA-TM-81923
    Format: application/pdf
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  • 7
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    Transonic static and dynamic stability characteristics of a finned projectile configuration (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Static and dynamic stability tests were made of a finned projectile configuration with the aft-mounted fins arranged in a cruciform pattern. The tests were made at free stream Mach numbers of 0.7, 0.9, 1.1, and 1.2 in the Langley 8-foot transonic pressure tunnel. Some of the parameters measured during the tests were lift, drag, pitching moment, pitch damping, and roll damping. Configurations tested included the body with undeflected fins, the body with various fin deflections for control, and the body with fins removed. Theoretical estimates of the stability derivatives were made for the fins on configuration.
    Keywords: AERODYNAMICS
    Type: NASA-TM-74058 , L-11966
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    Supersonic dynamic-stability derivatives of the space shuttle launch vehicle (1976)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An investigation was made to determine the dynamic stability characteristics of a 0.015-scale model of the space shuttle launch vehicle at supersonic speeds. These tests were made at angles of attack from -10 deg to 10 deg at Mach numbers of 2.00, 2.86, 3.96, and 4.63. The complete launch vehicle, consisting of the orbiter, external tank, and solid rocket boosters, has positive damping in pitch, roll, and yaw over the angle-of-attack and Mach number range. The orbiter external tank configuration has a region of negative angles pitch damping for small negative of attack at a Mach number of 2.00. At all other test conditions, the orbiter external tank configuration has positive damping about all three axes.
    Keywords: LAUNCH VEHICLES AND SPACE VEHICLES
    Type: NASA-TM-X-3315 , L-10494
    Format: application/pdf
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  • 9
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    Subsonic and transonic dynamic stability characteristics of a space shuttle orbiter (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Subsonic and transonic forced oscillation tests of a 0.0165-scale model of a modified 089B space shuttle orbiter were made in the Langley 8-foot transonic pressure tunnel. The period and damping of the basic unaugmented vehicle were calculated along the entry trajectory utilizing these measured dynamic data. Some parameter analyses were made with the measured dynamic derivatives.
    Keywords: LAUNCH VEHICLES AND SPACE VEHICLES
    Type: NASA-TN-D-8042 , L-10304
    Format: application/pdf
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  • 10
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    Supersonic dynamic stability characteristics of a space shuttle orbiter (1976)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Supersonic forced-oscillation tests of a 0.0165-scale model of a modified 089B Rockwell International shuttle orbiter were conducted in a wind tunnel for several configurations over a Mach range from 1.6 to 4.63. The tests covered angles of attack up to 30 deg. The period and damping of the basic unaugmented vehicle were calculated along the entry trajectory using the measured damping results. Some parameter analysis was made with the measured dynamic derivatives. Photographs of the test configurations and test equipment are shown.
    Keywords: AERODYNAMICS
    Type: NASA-TN-D-8043 , L-10063
    Format: application/pdf
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