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  • 1
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    Demonstration of an elastically coupled twist control concept for tilt rotor blade application (1994)
    In:  Other Sources
    Details
    Publication Date: 2011-08-24
    Description: The purpose of this Note is to present results from an analytic/experimental study that investigated the potential for passively changing blade twist through the use of extension-twist coupling. A set of composite model rotor blades was manufactured from existing blade molds for a low-twist metal helicopter rotor blade, with a view toward establishing a preliminary proof concept for extension-twist-coupled rotor blades. Data were obtained in hover for both a ballasted and unballasted blade configuration in sea-level atmospheric conditions. Test data were compared with results obtained from a geometrically nonlinear analysis of a detailed finite element model of the rotor blade developed in MSC/NASTRAN.
    Keywords: AERODYNAMICS
    Type: AIAA Journal (ISSN 0001-1452); 32; 7; p. 1549-1551
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Inverse boundary-layer technique for airfoil design (1979)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: A description is presented of a technique for the optimization of airfoil pressure distributions using an interactive inverse boundary-layer program. This program allows the user to determine quickly a near-optimum subsonic pressure distribution which meets his requirements for lift, drag, and pitching moment at the desired flow conditions. The method employs an inverse turbulent boundary-layer scheme for definition of the turbulent recovery portion of the pressure distribution. Two levels of pressure-distribution architecture are used - a simple roof top for preliminary studies and a more complex four-region architecture for a more refined design. A technique is employed to avoid the specification of pressure distributions which result in unrealistic airfoils, that is, those with negative thickness. The program allows rapid evaluation of a designed pressure distribution off-design in Reynolds number, transition location, and angle of attack, and will compute an airfoil contour for the designed pressure distribution using linear theory.
    Keywords: AERODYNAMICS
    Type: NASA. Langley Res. Center Advanced Technol. Airfoil Res., Vol. 1, Pt. 1; p 383-397
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Long fluid filled bags suspended by line forces (1975)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: A previous analysis of fluid filled storage bags is extended to the case of a long fluid filled cylindrical membrane supported by uniform line loads. Cross-sectional shape, stiffness of the support system and stress resultants in the membrane are determined. The application of the numerical results to problems arising in the design of nonrigid airships is discussed.
    Keywords: AERODYNAMICS
    Type: MIT Proc. of the Interagency Workshop on Lighter than Air Vehicles; p 199-208
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Some factors affecting the static longitudinal and directional stability characteristics of supersonic aircraft configurations (1957)
    In:  CASI
    Details
    Publication Date: 2019-05-23
    Description: Factors affecting static, longitudinal, and directional stability characteristics of supersonic aircraft configurations
    Keywords: AERODYNAMICS
    Type: NACA-RM-L57E24A
    Format: application/pdf
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  • 5
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    Stability and control characteristics at a mach number of 2.01 of a variable-wing-sweep configuration with outboard wing panels swept back 75 deg (1959)
    In:  CASI
    Details
    Publication Date: 2019-05-23
    Description: Stability and control of variable sweep wing configuration with outboard wing panels swept back 75 degrees at Mach 2.01
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-32
    Format: application/pdf
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  • 6
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    The role of tip clearance in high-speed fan stall (1991)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A numerical experiment has been carried out to define the near-stall casing endwall flowfield of a high-speed fan rotor. The experiment used a simulation code incorporating a simple clearance model, whose calibration is presented. The results of the simulation show that the interaction of the tip leakage vortex and the in-pasage shock plays a major role in determining the fan flow range. More specifically, the computations imply that it is the area increase of this vortex as it passes through the in-passage shock, which is the source of the blockage associated with stall. In addition, for fans of this type, it is the clearance over the forward portion of the fan blade which controls the flow processes leading to stall.
    Keywords: AERODYNAMICS
    Type: ASME PAPER 91-GT-83
    Format: text
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  • 7
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    Some effects of interference flow fields on supersonic configurations (1986)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A summary of selected results for various basic research models is presented in order to illustrate some effects of interference flow fields at supersonic speeds. Some general effects of wings and tails on typical cruciform missile configurations are shown. Several arrangements of cruise-type missile concepts are presented to show the effects of added body volume on the lift-drag ratio. In addition, the effects of several tail arrangements and some effects of body cross-section on the directional stability characteristics are included.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 86-2078
    Format: text
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  • 8
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    Static investigation of two STOL nozzle concepts with pitch thrust-vectoring capability (1986)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A static investigation of the internal performance of two short take-off and landing (STOL) nozzle concepts with pitch thrust-vectoring capability has been conducted. An axisymmetric nozzle concept and a nonaxisymmetric nozzle concept were tested at dry and afterburning power settings. The axisymmetric concept consisted of a circular approach duct with a convergent-divergent nozzle. Pitch thrust vectoring was accomplished by vectoring the approach duct without changing the nozzle geometry. The nonaxisymmetric concept consisted of a two dimensional convergent-divergent nozzle. Pitch thrust vectoring was implemented by blocking the nozzle exit and deflecting a door in the lower nozzle flap. The test nozzle pressure ratio was varied up to 10.0, depending on model geometry. Results indicate that both pitch vectoring concepts produced resultant pitch vector angles which were nearly equal to the geometric pitch deflection angles. The axisymmetric nozzle concept had only small thrust losses at the largest pitch deflection angle of 70 deg., but the two-dimensional convergent-divergent nozzle concept had large performance losses at both of the two pitch deflection angles tested, 60 deg. and 70 deg.
    Keywords: AERODYNAMICS
    Type: NASA-TP-2559 , L-165052 , NAS 1.60:2559
    Format: application/pdf
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  • 9
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    A model for closing the inviscid form of the average-passage equation system (1986)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A mathematical model is proposed for closing or mathematically completing the system of equations which describes the time average flow field through the blade passages of multistage turbomachinery. These equations referred to as the average passage equation system govern a conceptual model which has proven useful in turbomachinery aerodynamic design and analysis. The closure model is developed so as to insure a consistency between these equations and the axisymmetric through flow equations. The closure model was incorporated into a computer code for use in simulating the flow field about a high speed counter rotating propeller and a high speed fan stage. Results from these simulations are presented.
    Keywords: AERODYNAMICS
    Type: ASME PAPER 86-GT-227
    Format: text
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  • 10
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    Effects of some geometric variations on missile aerodynamic characteristics at supersonic speeds (1986)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A summary of some results from tests of a wing-body general research missile model is presented for a Mach number range up to 4.63. A basic ogive-cylinder body with a length-to-diameter ratio of 10 was used to which was attached a series of wing planforms. The planforms included a family of delta wings and a family of rectangular wings having a constant root chord but varying spans so that wings of constant exposed area could be compared. In addition, a cranked-tip planform was included and a rectangular planform with reduced chord. Some results are presented for wing-body-tail configurations - one utilizing a cranked wing planform and one with wings having a constant root chord and span, but tip chords that were 0, 20, and 40 percent of the root chord.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 86-0570
    Format: text
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