Parametric investigation of the effects of active flow control on the normal force of a delta wing

Yair Guy, Julie A. Morrow, Thomas E. Mclaughlin, Israel J Wygnanski

Research output: Chapter in Book/Report/Conference proceedingConference contribution

3 Citations (Scopus)

Abstract

The efficacy of active flow control in delaying vortex breakdown and enhancing the lift characteristics of a 70°-sweep delta wing is experimentally investigated in a low-speed wind tunnel at the USAF Academy. Periodic blowing and suction with zero net mass flux is applied at the leading edge of the wing. The pressure distribution over the upper surface of the wing is measured at a freestream velocity of 4.3 m/s, corresponding to a chord Reynolds number of 2.1×105. A parametric study is conducted, aimed at investigating the effect of periodic flow excitation on the pressure distribution on the upper surface of the wing. In particular, the normal force is computed and optimum values of key control parameters are established. The momentum coefficient of the flow excitation is varied from 0 to 0.004 and the nondimensional frequency is varied from 0 to 3.5. Pressure distribution on the upper surface of the wing is measured at angles of attack of 20° to 40° and the pressure is integrated to yield the normal force coefficient. It is found that the periodic flow excitation delays wing stall and greatly increases the normal force at angles of attack where stall would have occurred otherwise. At a constant momentum coefficient, the effect of the flow excitation is maximized at a nondimensional frequency of 1.38. At a constant frequency, an almost asymptotic increase of the normal force is observed as the momentum coefficient increases. The effect of the periodic flow excitation reaches its maximum at a momentum coefficient of 0.004 approximately. These results are consistent with results that were obtained in previous investigations. A maximum increase of 38% in the normal force is obtained at an angle of attack of 40o at the test conditions, relative to the unforced case. A 10o delay of the stall angle is achieved.

Original languageEnglish (US)
Title of host publication38th Aerospace Sciences Meeting and Exhibit
PublisherAmerican Institute of Aeronautics and Astronautics Inc.
StatePublished - 2000
Event38th Aerospace Sciences Meeting and Exhibit 2000 - Reno, NV, United States
Duration: Jan 10 2000Jan 13 2000

Other

Other38th Aerospace Sciences Meeting and Exhibit 2000
CountryUnited States
CityReno, NV
Period1/10/001/13/00

Fingerprint

delta wings
flow control
Flow control
wings
angle of attack
momentum
Momentum
Angle of attack
pressure distribution
Pressure distribution
coefficients
excitation
swept wings
low speed wind tunnels
vortex breakdown
blowing
suction
leading edges
Blow molding
wind tunnel

ASJC Scopus subject areas

  • Space and Planetary Science
  • Aerospace Engineering

Cite this

Guy, Y., Morrow, J. A., Mclaughlin, T. E., & Wygnanski, I. J. (2000). Parametric investigation of the effects of active flow control on the normal force of a delta wing. In 38th Aerospace Sciences Meeting and Exhibit American Institute of Aeronautics and Astronautics Inc..

Parametric investigation of the effects of active flow control on the normal force of a delta wing. / Guy, Yair; Morrow, Julie A.; Mclaughlin, Thomas E.; Wygnanski, Israel J.

38th Aerospace Sciences Meeting and Exhibit. American Institute of Aeronautics and Astronautics Inc., 2000.

Research output: Chapter in Book/Report/Conference proceedingConference contribution

Guy, Y, Morrow, JA, Mclaughlin, TE & Wygnanski, IJ 2000, Parametric investigation of the effects of active flow control on the normal force of a delta wing. in 38th Aerospace Sciences Meeting and Exhibit. American Institute of Aeronautics and Astronautics Inc., 38th Aerospace Sciences Meeting and Exhibit 2000, Reno, NV, United States, 1/10/00.
Guy Y, Morrow JA, Mclaughlin TE, Wygnanski IJ. Parametric investigation of the effects of active flow control on the normal force of a delta wing. In 38th Aerospace Sciences Meeting and Exhibit. American Institute of Aeronautics and Astronautics Inc. 2000
Guy, Yair ; Morrow, Julie A. ; Mclaughlin, Thomas E. ; Wygnanski, Israel J. / Parametric investigation of the effects of active flow control on the normal force of a delta wing. 38th Aerospace Sciences Meeting and Exhibit. American Institute of Aeronautics and Astronautics Inc., 2000.
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AB - The efficacy of active flow control in delaying vortex breakdown and enhancing the lift characteristics of a 70°-sweep delta wing is experimentally investigated in a low-speed wind tunnel at the USAF Academy. Periodic blowing and suction with zero net mass flux is applied at the leading edge of the wing. The pressure distribution over the upper surface of the wing is measured at a freestream velocity of 4.3 m/s, corresponding to a chord Reynolds number of 2.1×105. A parametric study is conducted, aimed at investigating the effect of periodic flow excitation on the pressure distribution on the upper surface of the wing. In particular, the normal force is computed and optimum values of key control parameters are established. The momentum coefficient of the flow excitation is varied from 0 to 0.004 and the nondimensional frequency is varied from 0 to 3.5. Pressure distribution on the upper surface of the wing is measured at angles of attack of 20° to 40° and the pressure is integrated to yield the normal force coefficient. It is found that the periodic flow excitation delays wing stall and greatly increases the normal force at angles of attack where stall would have occurred otherwise. At a constant momentum coefficient, the effect of the flow excitation is maximized at a nondimensional frequency of 1.38. At a constant frequency, an almost asymptotic increase of the normal force is observed as the momentum coefficient increases. The effect of the periodic flow excitation reaches its maximum at a momentum coefficient of 0.004 approximately. These results are consistent with results that were obtained in previous investigations. A maximum increase of 38% in the normal force is obtained at an angle of attack of 40o at the test conditions, relative to the unforced case. A 10o delay of the stall angle is achieved.

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