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Instrumentation, techniques and data reduction associated with airfoil testing programs at Wichita State University (1978)

Wentz, W. H., Jr. ; Seetharam, H. C. ; Rodgers, E. J.

In: CASI

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Publication Date: 2006-02-22

Description: Two dimensional airfoil testing was conducted at the Wichita State University Beech Wind Tunnel for a number of years. The instrumentation developed and adapted during this period of testing for determination of flow fields along with traversing mechanisms for these probes are discussed. In addition, some of the techniques used to account for interference effects associated with the apparatus used for this two dimensional testing are presented. The application of a minicomputer to the data reduction and presentation is discussed.

Keywords: INSTRUMENTATION AND PHOTOGRAPHY

Type: NASA. Langley Res. Center Advanced Technol. Airfoil Res., Vol. 1, Pt. 2; p 539-558

Format: text

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2

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Experimental Studies of Flow Separation of the NACA 2412 Airfoil at Low Speeds (1997)

Rodgers, E. J. ; Seetharam, H. C. ; Wentz, W. H., Jr.

In: CASI

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Publication Date: 2019-06-28

Description: Wind tunnel tests have been conducted on an NACA 2412 airfoil section at Reynolds number of 2.2 x 10(exp 6) and Mach number of 0.13. Detailed measurements of flow fields associated with turbulent boundary layers have been obtained at angles of attack of 12.4 degrees, 14.4 degrees, and 16.4 degrees. Pre- and post-separated velocity and pressure survey results over the airfoil and in the associated wake are presented. Extensive force, pressure, tuft survey, hot-film survey, local skin friction, and boundary layer data are also included. Pressure distributions and separation point locations show good agreement with theory for the two layer angles of attack. Boundary layer displacement thickness, momentum thickness, and shape factor agree well with theory up to the point of separation. There is considerable disparity between extent of flow reversal in the wake as measured by pressure and hot-film probes. The difference is attributed to the intermittent nature of the flow reversal.

Keywords: AERODYNAMICS

Type: NASA-CR-197497 , NAS 1.26:197497 , AR77-3

Format: application/pdf

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3

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Experimental studies of flow separation of the GA(W)-2 airfoil at low speeds (1977)

Rodgers, E. J. ; Seetharam, H. C. ; Wentz, W. H., Jr.

In: Other Sources

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Publication Date: 2019-06-28

Description: Wind tunnel tests have been conducted on a NASA GA(W)-2 airfoil section at Reynolds number of 2.2 x 10(exp 6) and Mach number of 0.13. Detailed measurements of flow fields associated with turbulent boundary layers have been obtained at angles of attack of 10.3, 14.4, and 18.3 deg. Pre- and post-separated velocity and pressure survey results over the airfoil and in the associated wake are presented. Extensive force, pressure, tuft survey, hot-film survey, local skin friction, and boundary layer data are also included. Pressure distributions and separation point locations show good agreement with theory for the two lower angles of attack. Boundary layer displacement thickness, momentum thickness, and shape factor agree well with theory up to the point of separation. There is considerable disparity between extent of flow reversal in the wake as measured by pressure and hot-film probes. The difference is attributed to the intermittent nature of the flow reversal.

Keywords: AERODYNAMICS

Type: NASA-CR-197254 , NAS 1.26:197254 , AR77-4

Format: text

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4

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Experimental studies of flow separation of three airfoils at low speeds (1982)

Wentz, W. H., Jr. ; Seetharam, H. C. ; Rodgers, E. J.

In: CASI

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Publication Date: 2019-06-28

Description: Wind tunnel tests were conducted on the NASA LS(1)-0421 Mod, NACA 2412 and NASA GA(W)-2 airfoil sections at a Reynolds number of 2.2 x 10(6) and a Mach number of 0.13. Detailed measurements of flow fields associated with turbulent boundary layers of these airfoils were obtained at pre-stall, near-stall, and post-stall angles of attack. Velocity and pressure survey results over the airfoil and in the associated wake, are presented for fully attached flow conditions through the stalled flow condition. Extensive force, pressure, tuft survey, hot-film survey, local skin friction and boundary layer data are also included.

Keywords: AERODYNAMICS

Type: NASA-CR-3530 , NAS 1.26:3530 , AR-79-2

Format: application/pdf

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