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Nonuniform deterministic routing on FChord(α
 In Proceedings of first International Workshop on Hot Topics in PeertoPeer Systems (HOTP2P ’04) (in conjunction with MASCOTS 2004) Volendam, The Nederlands
, 2004
"... Abstract—In this paper, we present a family of novel P2P routing schemes based on Chord [26] (and its variation FChord(α) [2]) that trades off uniformity with efficiency without using any additional overhead. We prove that HFChord(α)’s routing is more efficient than in FChord(α) in terms of its ..."
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Cited by 3 (2 self)
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average path length that is O(log n / log log n). We also show, by simulations, that HFChord(α) is more efficient than the corresponding FChord(α) by a percentage that goes from 15 % to 22 % even for small n. I.
FullScale WindTunnel Studies of F/A18 Tail Buffet
 Journal of Aircraft
, 1996
"... Tail buffet studies were conducted on a full.scale, production F/A18 fighter aircraft in the 80 by 120 ft Wind Tunnel at NASA Ames Research Center. The F/A18 was tested over an angleofattack range of 1850 deg, and at wind speeds of up to 168 ft/s, corresponding to a Reynolds number of 12.3 x 10 ..."
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Cited by 16 (0 self)
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Tail buffet studies were conducted on a full.scale, production F/A18 fighter aircraft in the 80 by 120 ft Wind Tunnel at NASA Ames Research Center. The F/A18 was tested over an angleofattack range of 1850 deg, and at wind speeds of up to 168 ft/s, corresponding to a Reynolds number of 12.3 x
and
"... We present experimental results to yield insight into the scalability and control effectiveness of singledielectricbarrierdischarge plasma actuators for leadingedge separation control on airfoils. The parameters investigated are chord Reynolds number, Mach number, leadingedge radius, actuator a ..."
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amplitude, and unsteady frequency. This includes chord Reynolds numbers up to 1:0 106 and a maximum freestream speed of 60 m=s corresponding to a Mach number of 0.176. The main objective of this work is to examine the voltage requirements for the plasma actuators to reattach the flow at the leading edge
THE CHORD CONSTRUCTION
, 2008
"... Abstract. Let F be a smooth plane curve of degree 3. Let β be an element in Pic(F)[2] − {0}. Let us define F ′: = {p(p + β)p ∈ F} ⊂ (P 2) ∗. In this note we show that F ′ is a smooth embedding of F/β. Moreover, let β ′ be the generator of Pic(F)/β, and let p ∈ F be a flex, then p(p + β) + β ′ is ..."
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associated to H. This notation will hold in the next definition and couple of lemmas. 2. Definition (The chord construction (c.c.)). Let us define i ′ : F/β → P 2∗ {p,p + β} ↦ → i(p)i(p + β) 3. Theorem. The c.c is an embedding. Proof. Let us identify F with its image i(F). The c.c. is 11: Let H be the line
FAILURES OF INSERVICE MPC PARALLELCHORD WOOD FLOOR TRUSS COMPONENTS REVEAL DEFICIENCIES IN ANSI/TPI STANDARDS
, 2000
"... ABSTRACT: The increased use of metalplateconnected (MPC) parallelchord wood floor trusses calls for a corresponding emphasis on the need for fully disclosed research and testing of web/chord joint behavior. Standardized industry procedures utilizing parallel and perpendiculartograin joint tests ..."
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ABSTRACT: The increased use of metalplateconnected (MPC) parallelchord wood floor trusses calls for a corresponding emphasis on the need for fully disclosed research and testing of web/chord joint behavior. Standardized industry procedures utilizing parallel and perpendiculartograin joint
and
, 2006
"... This paper presents an adjoint method for the optimal control of unsteady flows. The goal is to develop the continuous and discrete unsteady adjoint equations and their corresponding boundary conditions for the timeaccurate method. First, this paper presents the complete formulation of the timedepe ..."
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benefit of performing full unsteady optimization. Nomenclature A = flux Jacobian matrix B = boundary b = boundary velocity component c = chord length D = artificial dissipation flux E = internal energy F = Euler numerical flux vector f = Euler flux vector
J. Plasma Fusion Res. SERIES, Vol. 9 (2010) Development of Highly SpectralResolved Charge Exchange Recombination
, 2009
"... In this study, a high spectralresolved charge exchange recombination spectroscopy (CXRS) has been developed for the Heliotron J plasma aiming at improving the resolution of the rotation velocity, since it is expected that the rotation velocity would be small due to relatively high viscosity of the ..."
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of the Heliotron J configuration. A monochromator with Echelletype grating (f=200mm, F2.9) designed specially for the HeII (468.57nm) and CVI (529.05nm) CXR lines has dispersion of 0.163nm/mm for 468.57nm and 0.186nm/mm for 529.05nm, which corresponds to the resolution of the rotation velocity of 1.7 km
ABSTRACT A TEMPORAL MODEL FOR PITCH MULTIPLICITY AND TONAL CONSONANCE
"... One aspect of tonal consonance relevant to the pitch stability of chords and harmonic tension concerns the degree to which a collection of notes produces a unified, strong low pitch. We used a neurophysiologicallygrounded temporal model for pitch to test Stumpf's general hypothesis that conson ..."
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One aspect of tonal consonance relevant to the pitch stability of chords and harmonic tension concerns the degree to which a collection of notes produces a unified, strong low pitch. We used a neurophysiologicallygrounded temporal model for pitch to test Stumpf's general hypothesis
Effects of Noises on Fundamental Frequency Extraction Using Cepstral Analysis for Thai Dialects
"... Abstract: Problem statement: The fundamental frequency (F0) of the human speech corresponds to the vibration frequency of the human vocal chords. To extract the F0 from a speech utterance, one approach is based on the Cepstral analysis. In Thai, there are four main dialects spoken by Thai people res ..."
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Abstract: Problem statement: The fundamental frequency (F0) of the human speech corresponds to the vibration frequency of the human vocal chords. To extract the F0 from a speech utterance, one approach is based on the Cepstral analysis. In Thai, there are four main dialects spoken by Thai people
INVESTIGATION OF TEE LOWSPEED AERODYNAMIC CRARACTERISTICS OF A VARIABIXSWEEP AIRPLANE MODEL WITH
"... An investigation w a s conducted t o determine the lowspeed aerodynamic characterist ics of a variablesweep airplane model w i t h a twisted and at a Mach rider 1.10 and a lift coefficient of 0.25 a t Yo sweep. A comparison was made with the data. obtained on the same model w i t h an untwisted an ..."
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and uncanibered wing installed with the same incidence of the mean aerodynamic chord a t 500 sweep. The ef fec t of par t ia lspan spl i t f laps w a s also included i n the investigation. r cambered wing. The wing was designed t o have a uniform load istribution ti The t e s t s, .which were made a t a Reynolds
Results 1  10
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36