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  • 1
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    Tangential, semisubmerged, and internal store carriage and separation (1992)
    In:  Other Sources
    Details
    Publication Date: 2011-08-24
    Description: Accounts are presented of tangential, semisubmerged, and internal store carriage drag, as well as of the results to date of stores-separation investigations employing both computational and experimental methods. It is demonstrated that CFD can contribute to the data base needed for internal stores carriage design and trade studies. Attention is given to the case of an internally carried store separating from its bay at supersonic speeds, where various kinds of interference are encountered. A code is developed for the simulation of these unsteady flows through time-accurate computations; computation results are noted to closely reproduce experiment data.
    Keywords: AERODYNAMICS
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  • 2
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    Passive venting system for modifying cavity flowfields at supersonic speeds (1988)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Description: The drag of airfoils in transonic flow can be reduced through the use of a passive venting system that employs a porous plate for part of the airfoil upper surface with a vent chamber underneath the porous plate Attention is given to the results obtained with a wind tunnel model employing such a porous floor system. This passive venting system has been used to extend the length/height value before the onset of high drag-producing closed cavity flow at supersonic speeds.
    Keywords: AERODYNAMICS
    Type: AIAA Journal (ISSN 0001-1452); 26; 374-376
    Format: text
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  • 3
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    New test techniques to evaluate near field effects for supersonic store carriage and separation (1989)
    In:  CASI
    Details
    Publication Date: 2017-10-02
    Description: Store separation and store carriage drag studies were conducted. A primary purpose is to develop new experimental methods to evaluate near field effects of store separation and levels of store carriage drag associated with a variety of carriage techniques for different store shapes and arrangements. Flow field measurements consisting of surface pressure distributions and vapor screen photographs are used to analyze the variations of the store separation characteristics with cavity geometry. Store carriage drag measurements representative of tangent, semi-submerged, and internal carriage installations are presented and discussed. Results are included from both fully metric models and models with only metric segments (metric pallets) and the relative merits of the two are discussed. Carriage drag measurements for store installations on an aircraft parent body are compared both with prediction methods and with installations on a generic parent body.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AGARD, Stability and Control of Tactical Missile Systems; 9 p
    Format: text
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  • 4
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    Separation characteristics of generic stores from lee side of an inclined flat plate at Mach 6 (1995)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An experimental investigation was conducted to determine the aerodynamic characteristics of a store as it was separated from the lee side of a flat plate inclined at 15 deg to the free-stream flow at Mach 6. Two store models were tested: a cone cylinder and a roof delta. Force and moment data were obtained for both stores as they were moved in 0.5-in. increments away from the flat plate lee-side separated flow region into the free-stream flow while the store angle of attack was held constant at either 0 deg or 15 deg. The results indicate that both stores had adverse separation characteristics (i.e., negative normal force and pitching moment) at an angle of attack of 0 deg, and the cone cylinder had favorable separation characteristics (i.e., positive normal force and pitching moment) at an angle of attack of 15 deg. At an angle of attack of 15 deg, the separation characteristics of the roof delta are indeterminate at small separation distances and favorable at greater separation distances. These characteristics are the result of the local flow inclination relative to the stores as they traversed through the flat plate lee-side flow field. In addition to plotted data, force and moment data are tabulated and schlieren photographs of the stores and flat plate are presented.
    Keywords: AERODYNAMICS
    Type: NASA-TM-4652 , L-17384 , NAS 1.15:4652
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  • 5
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    Drag measurements of an axisymmetric nacelle mounted on a flat plate at supersonic speeds (1995)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An experimental investigation was conducted to determine the effect of diverter wedge half-angle and nacelle lip height on the drag characteristics of an assembly consisting of a nacelle fore cowl from a typical high-speed civil transport (HSCT) and a diverter mounted on a flat plate. Data were obtained for diverter wedge half-angles of 4.0 deg, 6.0 deg, and 8.0 deg and ratios of the nacelle lip height above a flat plate to the boundary-layer thickness (h(sub n)/delta) of approximately 0.87 to 2.45. Limited drag data were also obtained on a complete nacelle/diverter configuration that included fore and aft cowls. Although the nacelle/diverter drag data were not corrected for base pressures or internal flow drag, the data are useful for comparing the relative drag of the configuration tested. The tests were conducted in the Langley Unitary Plan Wind Tunnel at Mach numbers of 1.50, 1.80, 2.10, and 2.40 and Reynolds numbers ranging from 2.00 x 10(exp 6) to 5.00 x 10(exp 6) per foot. The results of this investigation showed that the nacelle/diverter drag essentially increased linearly with increasing h(sub n)/delta except near 1.0 where the data showed a nonlinear behavior. This nonlinear behavior was probably caused by the interaction of the shock waves from the nacelle/diverter configuration with the flat-plate boundary layer. At the lowest h(sub n)/delta tested, the diverter wedge half-angle had virtually no effect on the nacelle/diverter drag. However, as h(sub n)/delta increased, the nacelle/diverter drag increased as diverter wedge half-angle increased.
    Keywords: AERODYNAMICS
    Type: NASA-TM-4660 , L-17416 , NAS 1.15:4660
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  • 6
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    Measurements of forces, moments, and pressures on a generic store separating from a box cavity at supersonic speeds (1991)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An experimental investigation was conducted to measure the forces, moments, and pressure distributions on the generic store separating from a rectangular box cavity contained in a flat plate surface at supersonic speeds. Pressure distributions inside the cavity and oil flow and vapor-screen photographs of the cavity flow field were also obtained. The measurements were obtained for the store separating from a flat plate surface, from two shallow cavities having length to depth ratios (L/h) of 16.778 and 12.073, and from a deep cavity having L/h = 6.730. Measurements for the shallow cavities were obtained both with and without rectangular doors attached to sides of the cavities. The tests were conducted at free stream Mach numbers of 1.69, 2.00 and 2.65 for a free stream Reynolds number per foot of 2 x 10(exp 6). Presented here are a discussion of the results, a complete tabulation of the pressure data, figures of both the pressure and force and moment data, and representative oil flow and vapor screen photographs.
    Keywords: AERODYNAMICS
    Type: NASA-TP-3110 , L-16866 , NAS 1.60:3110
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  • 7
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    Experimental cavity pressure distributions at supersonic speeds (1987)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An investigation was conducted to define pressure distributions for rectangular cavities over a range of free-stream Mach numbers and cavity dimensions. These pressure distributions together with schlieren photographs are used to define the critical values of cavity length-to-depth ratio that separate open type cavity flows from closed type cavity flows. For closed type cavity flow, the shear layer expands over the cavity leading edge and impinges on the cavity floor, whereas for open type cavity flow, the shear layer bridges the cavity. The tests were conducted by using a flat-plate model permitting the cavity length to be remotely varied from 0.5 to 12 in. Cavity depths and widths were varied from 0.5 to 2.5 in. The flat-plate boundary layer approaching the cavity was turbulent and had a thickness of approximately 0.2 in. at the cavity front face for the range of test Mach numbers from 1.5 to 2.86. Presented are a discussion of the results and a complete tabulation of the experimental data.
    Keywords: AERODYNAMICS
    Type: NASA-TP-2683 , L-16215 , NAS 1.60:2683
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  • 8
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    Drag measurements of blunt stores tangentially mounted on a flat plate at supersonic speeds (1987)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An investigation has been conducted in the Langley Unitary Plan Wind Tunnel to measure the drag of blunt stores (hemispherical noses and afterbodies) tangentially mounted in various arrays on a flat plate at nominal Mach numbers of 1.60, 1.90, 2.16,and 2.86 and at a nominal Reynolds number of 2X10 to the 6th power per foot. The arrays consisted of two and three stores mounted in lateral, tandem, or staggered arrangements. The relative position of the stores in the arrays was varied while the drag of only one store was measured to determine the effect of spacing on the store drag. Store-on-store interference was determined by comparing the drag of a single store with the drag of the store in an array. The results indicate virtually all arrangements and spacings which were tested had favorable store-on-store interference (drag reduction) across the Mach number range. Tabulated data, schlieren photographs, and shadowgraphs are included.
    Keywords: AERODYNAMICS
    Type: NASA-TP-2742 , L-16284 , NAS 1.60:2742
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  • 9
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    Tangential, semisubmerged, and internal store carriage and separation at supersonic speeds (1991)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: This paper presents a general overview of experimental research conducted in the area of tangential, semisubmerged, and internal store carriage and separation at supersonic speeds. Some of the advantages and disadvantages of tangential and semisubmerged carriage are presented along with a discussion of the interference effects between stores mounted in various arrays. Also included is a review of cavity flow fields that exist at supersonic speeds and a discussion of the effect of cavity size and cavity doors on the separation characteristics of stores. Finally, three passive venting systems are described which can modify the flow field of certain cavities and thus improve the separation characteristics of stores from those cavities.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 91-0198
    Format: text
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  • 10
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    Experimental Investigation of Porous-floor Effects on Cavity Flow Fields at Supersonic Speeds (1990)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An experimental investigation was conducted to determine the effectiveness of a passive-venting system to modify the flow field characteristics of a rectangular-box cavity at supersonic speeds. The passive-venting system consists of a porous floor with a vent chamber beneath the floor. For certain cavity length-to-height ratios, this configuration allowed high-pressure air at the rear of the cavity to vent to the forward part of the cavity, thereby modifying the cavity flow field. The wind-tunnel model consisted of a flat plate that housed a cavity mounted on a balance such that only the cavity drag was measured. The cavity height remained constant, and the length varied with rectangular-block inserts. Both solid-and porous-floor cavities were tested for comparison at Mach numbers of 1.60, 1.90, 2.16, and 2.86. These results showed that the passive-venting system did modify the cavity flow field. In order to determine the type flow field which existed for the porous-floor configuration, pressures were measured inside the cavity at the same conditions and for the same configurations as those used in the drag tests. Pressure data were also obtained with stores mounted in the cavity. These results, along with Schlieren photographs and the tabulated data, are presented to document the porous-floor cavity flow field.
    Keywords: AERODYNAMICS
    Type: NASA-TP-3032 , L-16711 , NAS 1.60:3032
    Format: application/pdf
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