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  • 1
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    Comparisons of boundary-layer transition measurement techniques at supersonic Mach numbers (1991)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: AIAA Journal (ISSN 0001-1452); 29; 865-871
    Format: text
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  • 2
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    An overview of the fundamental aerodynamics branch's research activities in wing leading-edge vortex flows at supersonic speeds (1986)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: For the past 3 years, a research program pertaining to the study of wing leading edge vortices at supersonic speeds has been conducted in the Fundamental Aerodynamics Branch of the High-Speed Aerodynamics Division at the Langley Research Center. The purpose of the research is to provide an understanding of the factors governing the formation and the control of wing leading-edge vortices and to evaluate the use of these vortices for improving supersonic aerodynamic performance. The studies include both experimental and theoretical investigations and focus primarily on planform, thickness and camber effects for delta wings. An overview of this research activity is presented.
    Keywords: AERODYNAMICS
    Type: Vortex Flow Aerodynamics, Vol. 1; p 349-377
    Format: application/pdf
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  • 3
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    An evaluation of the relative merits of wing-canard, wing-tail, and tailless arrangements for advanced fighter applications (1984)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: Two sets of wind tunnel tests were performed to examine the relative merits of wing-canard, wing-tail and tailless configurations for advanced fighters. Both sessions focused on variable camber using automated, prescheduled leading and trailing edge flap positioning. The trials considered a modified F-16 tail and canard configuration at subsonic, transonic and supersonic speeds, a 60 deg delta wing sweep, a 44 deg leading edge trapezoidal wing at subsonic and supersonic speeds, vortex flow effects, and flow interactions in the canard-wing-tail-tailless variations. The results showed that large negative stabilities would need to be tolerated in wing-canard arrangements to make them competitive with wing-tail arrangements. Subsonic polar shapes for canard and tailless designs were more sensitive to static design margins than were wing-tail arrangements. Canards provided better stability at supersonic speeds. The static margin limits were a critical factor in control surface selection. Finally, a tailless delta wing configuration exhibited the lowest projected gross take-off weight and drag values.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Format: text
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  • 4
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    An evaluation of leading-edge flap performance on delta and double-delta wings at supersonic speeds (1986)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The aerodynamic performance of leading-edge flaps on three delta double-delta wing planforms having aspect ratios of 1.75, 2.11, and 2.50, have been investigated experimentally. The wings were mounted on a generic fuselage without an inlet canopy, or a vertical tail. The Mach numbers of the flow over the wings were 1.60, 1.90 and 2.16. A primary set of full-span leading-edge flaps with similar root and tip chords were tested on each wing, and several alternate flap planforms were tested on the aspect ratio 1.75 wings. It is found that all leading edge geometries were effective in reducing drag lifting over the range of wing aspect ratios and Mach numbers tested. Greater flap performance was obtained when primary flaps were applied to the delta planform. In general, the primary flap geometry yielded better performance than the alternative geometries tested. Flow visualization techniques were found to be useful for identifying the beneficial effects of leading-edge flap deflection on flow separation as well as fuselage interference effects. Black and white photographs of the delta and double-delta planforms are provided.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 86-0315
    Format: text
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  • 5
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    Experimental and theoretical study of the longitudinal aerodynamic characteristics of delta and double-delta wings at Mach numbers of 1.60, 1.90, and 2.16 (1985)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An experimental and theoretical study was conducted to investigate the supersonic aerodynamic characteristics of delta and double-delta wings. Testing was conducted in the Langley Unitary Plan Wind Tunnel at Mach numbers of 1.60, 1.90, and 2.16. The double-delta wings exhibited lower zero-lift drag values than the delta wings having the same aspect ratio, whereas delta wings provided the lower drag due to lift. Deflections of the trailing-edge flaps for pitch control revealed that the induced aerodynamic forces were only a function of the flap planform and were independent of wing planform. The supporting theoretical analysis showed that the supersonic design and analysis system (SDAS) did not consistently predict all the longitudinal aerodynamic characteristics of the low-sweep, low-fineness-ratio wing-body configurations under investigation.
    Keywords: AERODYNAMICS
    Type: NASA-TP-2433 , L-15899 , NAS 1.60:2433
    Format: application/pdf
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  • 6
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    Supersonic aerodynamic characteristics of canard, tailless, and aft-tail configurations for 2 wing planforms (1985)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Aerodynamic characteristics of canard, tailless, and aft tail configurations were compared in tests on a general research model (generic fuselage without canopy, inlets, or vertical tails) at Mach 1.60 and 2.00 in the Langley Unitary Plan Wind Tunnel. Two uncambered wing planforms (trapezoidal with 44 deg leading edge sweep and delta with 60 deg leading edge sweep) were tested for each configuration. The relative merits of the configurations were also determined theoretically, to evaluate the capabilities of a linear theory code for such analyses. The canard and aft tail configurations have similar measured values for lift curve slope, maximum lift drag ratio, and zero lift drag. The stability decrease as Mach number increases is greatest for the tailless configuration and least for the canard configuration. Because of very limited accuracy in predicting the aerodynamic parameter increments between configurations, the linear theory code is not adequate for determining the relative merits of canard, tailless, and aft tail configurations.
    Keywords: AERODYNAMICS
    Type: NASA-TP-2434 , L-15927 , NAS 1.60:2434
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  • 7
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    Effects of axisymmetric and normal air jet plumes and solid plume on cylindrical afterbody pressure distributions at Mach numbers from 1.65 to 2.50 (1982)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A wind tunnel investigation of the interference effects of axisymmetric nozzle air plumes, a solid plume, and normal air jet plumes on the afterbody pressure distributions and base pressures of a cylindrical afterbody model was conducted at Mach numbers from 1.65 to 2.50. The axisymmetric nozzles, which varied in exit lip Mach number from 1.7 to 2.7, and the normal air jet nozzle were tested at jet pressure ratios from 1 (jet off) to 615. The tests were conducted at an angle of attack of 0 deg and a Reynolds number per meter of 6.56 million. The results of the investigation show that the solid plume induces greater interference effects than those induced by the axisymmetric nozzle plumes at the selected underexpanded design conditions. A thrust coefficient parameter based on nozzle lip conditons was found to correlate the afterbody disturbance distance and the base pressure between the different axisymmetric nozzles. The normal air jet plume and the solid plume induce afterbody disturbance distances similar to those induced by the axisymmetric air plumes when base pressure is held constant.
    Keywords: AERODYNAMICS
    Type: NASA-TP-2005 , L-14883 , NAS 1.60:2005
    Format: application/pdf
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  • 8
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    Interference effects of aft reaction-control yaw jets on the aerodynamic characteristics of a space shuttle orbiter model at supersonic speeds (1983)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A wind tunnel investigation of the interference effects of aft reaction control system yaw jet plumes on a 0.0125 scale Space Shuttle orbiter model was conducted at Mach numbers from 2.50 to 4.50. Test variables included model angle of attack, model angle of sideslip, jet to free stream mass flow ratio, and number and position of operating jets. The aft reaction control jet plume creates a blockage above and behind the wing on the side in which the jet exhausts and results in flow separation on the wing upper surface and fuselage side. Positive pitching moment and side force increments and negative yawing moment and rolling moment increments due to the flow separations are incurred for left side firing jets, primarily at angles of attack above 10 deg. The yawing moment interference increments are favorable and result in a small jet thrust amplification. As a result of this investigation, the aft reaction control system was certified for operation at supersonic Mach numbers prior to the first flight of the space transportation system (STS-1).
    Keywords: AERODYNAMICS
    Type: NASA-TM-84645 , L-15576 , NAS 1.15:84645
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  • 9
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    Development of a metric half-span model for interference free testing (1980)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: A metric half-span model has been developed which allows measurement of aerodynamic forces and moments without support interference or model distortion. This is accomplished by combining the best features of the conventional sting/balance and half-span splitter plate supports, For example, forces and moments are measured on one-half of a symmetrical model which is mechanically supported by a sting on the nonmetric half. Tests were performed in the Langley Unitary Plan wind tunnel over a Mach range of 1.60 to 2.70 and an angle-of-attack range of 04 deg to 20 deg. Preliminary results on concept evaluation, and effect of fuselage modification to house a conventional balance and sting are presented.
    Keywords: RESEARCH AND SUPPORT FACILITIES (AIR)
    Type: AIAA PAPER 80-0460 , Aerodynamics Testing Conference; Mar 18, 1980 - Mar 20, 1980; Colorado Springs, CO
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  • 10
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    Aerodynamic characteristics of a series of bodies with variations in nose camber (1983)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The aerodynamic characteristics of a series of cambered forebody models having a systematic variation in nose droop angle were determined from tests in the Langley 8-Foot Transonic Pressure Tunnel at Mach numbers from 0.60 to 1.20 and in the Langley Unitary Plan Wind Tunnel at Mach numbers of 1.47, 1.80, and 2.16. The models were tested through an angle-of-attack range of about 0 deg to 12 deg in the 8-Foot Transonic Pressure Tunnel and -2 deg to 20 deg in the Unitary Plan Wind Tunnel. Static longitudinal aerodynamic characteristics of the models were determined for all Mach numbers, and lateral-directional characteristics were determined for Mach numbers of 1.47 to 2.16. The investigation indicated that the principal effect of varying nose droop was on pitching moment, with some secondary effects on lift and drag. The experimental data were also compared with theoretical estimates.
    Keywords: AERODYNAMICS
    Type: NASA-TP-2206 , L-15647 , NAS 1.60:2206
    Format: application/pdf
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