DAN MICHAEL SOMERS
Pilots at Rose Dr, Port Matilda, PA
License number
Pennsylvania A1791313
Category
Airmen
Type
Authorized Aircraft Instructor
Address
Address
122 Rose Dr, Port Matilda, PA 16870
Personal information
See more information about DAN MICHAEL SOMERS at radaris.comName
Address
Phone
122 Rose Dr, Port Matilda, PA 16870
122 Reese Rd, Bellefonte, PA 16823
122 Rose Dr, Patton, PA 16668
122 Rose Dr, Port Matilda, PA 16870
601 Cricklewood Dr, State College, PA 16803
Professional information
Wing Airfoil
US Patent:
6607164, Aug 19, 2003
Filed:
Oct 22, 2001
Appl. No.:
09/982972
Inventors:
Dan M. Somers - Port Matilda PA
Assignee:
Toyota Motor Sales, U.S.A., Inc. - Torrance CA
International Classification:
B64C 314
US Classification:
244 35R
Abstract:
An airfoil having particular use in a general aviation aircraft operating at generally low speeds. The airfoil has a shape designed to produce high lift coefficients at low speeds, with low drag and lower lift coefficients at higher speeds. The airfoils lift characteristics are not sensitive to surface roughness on the leading edge caused by the accumulation of foreign matter on the airfoil due to the transition to turbulent flow occurring near the leading edge at high lift coefficients.
Quiet Airfoils For Small And Large Wind Turbines
US Patent:
8197218, Jun 12, 2012
Filed:
Nov 8, 2007
Appl. No.:
11/937183
Inventors:
James L. Tangler - Boulder CO, US
Dan L. Somers - Port Matilda PA, US
Dan L. Somers - Port Matilda PA, US
Assignee:
Alliance for Sustainable Energy, LLC - Golden CO
International Classification:
F03D 1/06
US Classification:
416238, 416243, 416DIG 2
Abstract:
Thick airfoil families with desirable aerodynamic performance with minimal airfoil induced noise. The airfoil families are suitable for a variety of wind turbine designs and are particularly well-suited for use with horizontal axis wind turbines (HAWTs) with constant or variable speed using pitch and/or stall control. In exemplary embodiments, a first family of three thick airfoils is provided for use with small wind turbines and second family of three thick airfoils is provided for use with very large machines, e. g. , an airfoil defined for each of three blade radial stations or blade portions defined along the length of a blade. Each of the families is designed to provide a high maximum lift coefficient or high lift, to exhibit docile stalls, to be relatively insensitive to roughness, and to achieve a low profile drag.
Cooling-Tower Fan Airfoils
US Patent:
6899524, May 31, 2005
Filed:
Jan 21, 2000
Appl. No.:
09/936802
Inventors:
James L. Tangler - Boulder CO, US
Dan M. Somers - Port Matilda PA, US
Dan M. Somers - Port Matilda PA, US
Assignee:
Midwest Research Institute - Kansas City MO
International Classification:
F03B003/12
US Classification:
416223R, 416DIG 2, 416DIG 5
Abstract:
A family of airfoils for a blade of a cooling-tower fan, is provided wherein the blade has a root region and a tip region, the family of airfoils comprises an airfoil () in the root region of the blade having a Reynolds number of 500,000, and an airfoil () in the tip region of the blade having a Reynolds number of 1,000,000, and wherein each airfoil is characterized by a maximum lift coefficient that is largely insensitive to roughness effects.
Laminar-Flow Airfoil
US Patent:
6905092, Jun 14, 2005
Filed:
Nov 20, 2002
Appl. No.:
10/299660
Inventors:
Dan M. Somers - Port Matilda PA, US
Assignee:
Airfoils, Incorporated - Port Matilda PA
International Classification:
B64C009/14, B64C009/16
US Classification:
244 3, 244 35 R, 244216, 244211
Abstract:
An airfoil having a fore airfoil element, an aft airfoil element, and a slot region in between them. These elements induce laminar flow over substantially all of the fore airfoil element and also provide for laminar flow in at least a portion of the slot region. The method of the invention is one for inducing natural laminar flow over an airfoil. In the method, a fore airfoil element, having a leading and trailing edge, and an aft airfoil element define a slot region. Natural laminar flow is induced over substantially all of the fore airfoil element, by inducing the pressures on both surfaces of the fore airfoil element to decrease to a location proximate the trailing edge of the fore airfoil element using pressures created by the aft airfoil element.