Global ETD Search

Search theses and dissertations gathered from participating repositories worldwide. Every result links back to the library that holds it. No account is needed.

Results

Showing 1 to 5 of 5 for “"Semispan"”.

  1. An Experimental Study of the Flowfield on a Semispan Rectangular Wing With a Simulated Glaze Ice Accretion

    … glaze ice accretion on the flowfield of a semispan, reflection-plane, rectangular wing at Re = 1.5 million and M = 0.12 was investigated. A laser Doppler velocimeter was used to map the flowfield on the upper surface of the model in both the clean and iced configurations at $\alpha$ = 0, 4, …

    uiuc Repository record for An Experimental Study of the Flowfield on a Semispan Rectangular Wing With a Simulated Glaze Ice Accretion (opens in a new tab)

  2. Identification of Transient Nonlinear Aeroelastic Phenomena

    … to a set of experiments involving a flexible semispan model (FSM) of a High Speed Civil Transport (HSCT) wing configuration conducted by Silva et al. (Experimental Steady and Unsteady Aerodynamic and Flutter Results for HSCT Semispan Models; AIAA/ASME/ASCE/AHS/ASC 41st Structures, Structural …

    vt Repository record for Identification of Transient Nonlinear Aeroelastic Phenomena (opens in a new tab)

  3. Analysis of pressure data obtained at transonic speeds on a thin low-aspect-ratio cambered delta wing-body combination

    … cambered over the outboard 15 percent of each semispan. The wing had an aspect ratio of 2.31, 60° sweepback of the leading edge, and had NACA 65A003 airfoil sections parallel to the model plane of symmetry over the uncambered portion. The results of this investigation indicate that a …

    vt Repository record for Analysis of pressure data obtained at transonic speeds on a thin low-aspect-ratio cambered delta wing-body combination (opens in a new tab)

  4. The effects of aero-propulsive coupling on aircraft with distributed propulsion systems

    … consisted of low-speed wind-tunnel testing of a semispan model of the modified SR22 geometry at Re = 3.5x10^5; 4.5x10^5 and 5.5x10^5. Data were again acquired as a function of angle of attack and fan speed. Measurements of the forces and moments experienced by the model were acquired with a …

    uiuc Repository record for The effects of aero-propulsive coupling on aircraft with distributed propulsion systems (opens in a new tab)

  5. Experimental Investigation of Active Wingtip Vortex Control Using Synthetic Jet Actuators

    … jet actuation (SJA) on the drag of a NACA 0015 semispan wing. The wing, which was designed and manufactured for this experiment, has an aspect ratio of 4.20, a span of 0.427 m (16.813”), and is built around an internal array of piezoelectric actuators, which work in series to create a synthetic …

    calpoly Repository record for Experimental Investigation of Active Wingtip Vortex Control Using Synthetic Jet Actuators (opens in a new tab)