Acoustic Surveys of a Scaled-Model CESTOL Transport Aircraft in Static and Forward Speed Conditions

Burnside, Nathan; Horne, Clifton

doi:10.2514/6.2012-2231

Cited by 2 publications

(1 citation statement)

References 8 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…The result is a rather cursory overview of the overall system capabilities and the reader is encouraged to refer to van Aken [19] for more general information on the NFAC DAS. Acoustic measurements are acquired on a separate data system, and the reader can refer to Burnside [20] for details. …”

Section: Data Acquisitionmentioning

confidence: 99%

An Experimental Investigation of the STOL Performance of Cal Poly's AMELIA in the NFAC

Lichtwardt¹

View full text Add to dashboard Cite

show abstract

Section: Data Acquisitionmentioning

confidence: 99%

An Experimental Investigation of the STOL Performance of Cal Poly's AMELIA in the NFAC

Lichtwardt¹

View full text Add to dashboard Cite

show abstract

AMELIA CESTOL Test: Acoustic Characteristics of Circulation Control Wing with Leading- and Trailing-Edge Slot Blowing

Horne

Burnside

2013

51st AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

Self Cite

View full text Add to dashboard Cite

Aeroacoustic measurements of the 11 % scale full-span AMELIA CESTOL model with leading-and trailing-edge slot blowing circulation control (CCW) wing were obtained during a recent test in the Arnold Engineering Development Centel' 40-by SO-Ft. Wind Tunnel at NASA Ames Research Center, Sound levels and spectra were acquired with seven in-flow microphones and a 4S-element phased microphone array for a variety of vehicle configurations, CCW slot flow rates, and forward speeds, COITections to the meaSUI'emel1ts and processin g al'e in progress, however the data from selected configurations presented in this report conlil'm good measurement quality al1d dynamic range over the test conditions, Array beamform maps at 40 kts tunnel speed show that the trailing edge flap so urce is dominant for most frequencies at flap angles of O· and 60°, The overall sound level for the 60° flap was similar to tbe 0° flap for most slot blowing rates forward of 90° incidence, but was louder by up to 6 dB fOI' downstream angles, At 100 kts, the in-flow microphone levels were louder than the sensor self-noise fOI' the highel' blowing rates, while passive and active background noise suppression methods for the microphone array revealed source levels as much as 20 dB lowel' than observed with the in-flow microphones, NomenclatureLift coeffic ient, L / (q*S) CCW slow momentum coefficient, (m*V j ) / (q*S) Circul ati on contro l wing Cross-spectra l matrix Lift, Ib r Slot mass fl ow rate, Ibm / s Overa ll sound pressure level, dB re 20,6 Pa Freestream dynamic pressure, Ib r / ft2 Radi a l di stance fi'o m model aco ustic center to sensor, inches Wing planfo rm reference area, ft 2 CCW s lot j et veloc ity, ft / s E mi ssion ang le relati ve to model aco ustic center, 0 = 0° for upstream emission

show abstract

Acoustic Surveys of a Scaled-Model CESTOL Transport Aircraft in Static and Forward Speed Conditions

Cited by 2 publications

References 8 publications

An Experimental Investigation of the STOL Performance of Cal Poly's AMELIA in the NFAC

An Experimental Investigation of the STOL Performance of Cal Poly's AMELIA in the NFAC

AMELIA CESTOL Test: Acoustic Characteristics of Circulation Control Wing with Leading- and Trailing-Edge Slot Blowing

Contact Info

Product

Resources

About