dc.rights.license CC BY-NC-ND. Users may download and share copies with attribution in accordance with a Creative Commons Attribution-Noncommercial-No Derivative Works 3.0 License. No commercial use or derivatives are permitted without the explicit approval of the author. dc.contributor Rusak, Zvi dc.contributor Hicken, Jason dc.contributor Sahani, Onkar dc.contributor Schwendeman, Donald W. dc.contributor.author Kraljic, Matthew dc.date.accessioned 2021-11-03T08:56:06Z dc.date.available 2021-11-03T08:56:06Z dc.date.created 2018-02-21T13:58:39Z dc.date.issued 2017-12 dc.identifier.uri https://hdl.handle.net/20.500.13015/2123 dc.description December 2017 dc.description School of Engineering dc.description.abstract The inception of leading-edge stall on stationary, smooth thin airfoils with various blunt nose shapes of the form $y=\pm k(ax)^{\frac{1}{a}}$ (where $a \geq 2$ and $k$ is a constant) at low to moderately high Reynolds numbers ($Re$) is studied. A reduced-order, multi-scale model problem is developed for relatively low $Re$ flows and is complimented by numerical computations using a Reynolds-Averaged Navier-Stokes (RANS) flow solver for moderately high $Re$. The asymptotic theory demonstrates that a flow about a thin airfoil may be described in terms of an outer region, around most of the airfoil's chord, and an inner region, around the nose, that asymptotically match each other. The flow in the outer region is dominated by the classical thin airfoil theory. Scaled (magnified) coordinates and a modified (smaller) Reynolds number ($Re_M$) are used to correctly account for the nonlinear behavior and acute velocity changes in the inner region, where both the near-stagnation and high-suction areas appear. The far-field of the inner region is described by a symmetric effect due to nose shape and an asymmetric effect with a lumped circulation parameter ($\tilde{A}$) due to angle of attack and camber. dc.description.abstract The inner flow problem is solved numerically using a transformation from the physical domain to a computational domain and a second-order finite-difference scheme for integrating the vorticity and stream function. The computed results demonstrate numerical convergence with mesh refinement. The inner region solutions reveal, for various values of $a$, the nature of the flow around the nose and the inception of global separation and stall as $\tilde{A}$ increases above a certain critical value, $\tilde{A}_s$, at fixed $a$ and $Re_M$. For $a \geq 2$, the value of $\tilde{A}_s$ decreases with $Re_M$ up to a limit value, $Re_{M,lim}$, above which unsteady effects increase $\tilde{A}_s$ and delay the onset of stall. For airfoils with the same thickness ratio and position of maximum thickness, global stall is delayed to higher angles of attack as $a$ is increased above 2. The results of the RANS computations for various $a$ show matching with the asymptotic results in a certain region of $Re_M$ values, as well as extend the stall predictions of $\tilde{A}_s$ to higher $Re_M$. Parametric studies provide data for the design of novel airfoils with blunt noses and higher stall angles of attack at various $Re$. dc.language.iso ENG dc.publisher Rensselaer Polytechnic Institute, Troy, NY dc.relation.ispartof Rensselaer Theses and Dissertations Online Collection dc.rights Attribution-NonCommercial-NoDerivs 3.0 United States * dc.rights.uri http://creativecommons.org/licenses/by-nc-nd/3.0/us/ * dc.subject Aeronautical engineering dc.title The leading-edge stall of airfoils with blunt noses at low to moderately high Reynolds numbers dc.type Electronic thesis dc.type Thesis dc.digitool.pid 178783 dc.digitool.pid 178784 dc.digitool.pid 178785 dc.rights.holder This electronic version is a licensed copy owned by Rensselaer Polytechnic Institute, Troy, NY. Copyright of original work retained by author. dc.description.degree PhD dc.relation.department Dept. of Mechanical, Aerospace, and Nuclear Engineering
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