Evaluation of a statistical method for determining peak inlet flow distortion using F-15 and F-18 data

Stevens, Claire H.; Oliphant, R.; Spong, E. D.

doi:10.2514/6.1980-1109

Cited by 10 publications

(5 citation statements)

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“…If the dynamic total pressure is defined in terms of pressure recovery, then, for each probe, dyn The basic method is similar to that described by Stevens et al 5 and consists of two fundamental elements: the generation of the compressor face dynamic total pressures and the determination of the maximum distortion level and pressure contour map. Rms turbulence and random numbers are combined to form the fluctuating pressure components which are added to the steady-state pressures to form the dynamic total pressures.…”

Section: Statistical Model Developmentmentioning

confidence: 99%

“…The method developed by Stevens et al 5 is very similar to that of Motycka, with two differences. First, the pressure data are processed at a cutoff filter frequency consistent with expected engine sensitivity in determining the probe rms turbulence levels.…”

Section: Introductionmentioning

confidence: 97%

“…4 ' 6 Due to the potential of these methods, a model similar to that described in Ref. 5 was used in comparisons with several inlet distortion data sets. The initial results appeared to validate the model, particularly in terms of the predicted peak distortion level/As cases, with increasing average inlet turbulence were investigated and as fewer rootmean-square (rms) turbulence measurements were used in the analysis, the quality of the predicted maps deteriorated.…”

Section: Introductionmentioning

confidence: 99%

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Statistical analysis method for prediction of maximum inlet distortion

Sedlock

1985

Journal of Propulsion and Power

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" '. MAY 10 W 95 FLIGHT DYNAMICS LABORATORY AIR FORCE WRIGHT AERONAUTICAL LABORATORIES B AIR FORCE SYSTEMS COMMAND ' WRIGHT-PATTERSON AIR FORCE BASE, OHIO 45433 S t 0 NVOTICE ,hen g;overnment drawings, specifications, or other 2ata are used for any purpose 3ther than in connection w.ith a definitely related ;overnment procurement operation, the 'nited States s;overrnenc thereby incurs no responsibility nor any obligation whatsoever; and the fact that the c7overnment ma,.; have formulated, furnished, or in any. way suppljed the said drawings, specifications, or other data, is not to be re-l7arded by :m.pli;cati;on or otherv.ise as in any manner licensina the holder or any othter person or coroorat-;on, or conveying any rig.hts or permission to manufacture use, or sell ant; oatented invention that may in any way be related thereto. Th.:s report h as been reviewed by the Office of P ublic Affairs (ASD/PA) and is releasable to the Mational Technical information Service (NVTIS). At NTIS, it will be ava; 7able to the),eneral public, including foreign nations. Ths echnicail reoort has been reviewed and is approved for publication. DL-NTIS SEDIJY2K LEWIS E. SURBER Senior Aerospace Enqincor Technical Manaqe-r FOR THE COMMANDER a-ess .-as 2-naflcea, ifyou wish to be removed from our mailing list, or-s: c noonter emprloyed by y;our orz-anizatiocn please noti fy AFWAL/FI: :, 4 j o ne. .3 maintain a c urrent mailing list". 3,-'c: so.~ not be returned unless return i's required by security-~-n :ntrct~~ b.'17ations, or noti;ce on, a st'ec~fi-c document.

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Section: Statistical Model Developmentmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 97%

Section: Introductionmentioning

confidence: 99%

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Statistical analysis method for prediction of maximum inlet distortion

Sedlock

1985

Journal of Propulsion and Power

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“…Many statistical methods, for example Kotycka (9) and Stevens (6), have been developed to predict the maximum dynamic distortion level. It is assumed that the time-variant pressure data are random and stationary with a normal distribution.…”

Section: Psd Analysismentioning

confidence: 99%

“…In this case average parameters cannot accurately indicate the distortion property. Recently many statistical methods (6) have been developed to predict the maximum distortion level. The measured standard pressure deviation of each measuring point is used to form a synthesized fluctuating pressure component.…”

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confidence: 99%

Experimental Investigation of Dynamic Distortion Properties in Transonic Flow Diffuser

Xijun¹,

Huaiti²,

Dong³

1989

International Journal of Turbo and Jet Engines

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This paper provides a description of experimental studies of various dynamic distortion properties in a two-dimensional transonic diffuser. Based upon the measured dynamic pressure across the diffuser discharge section, the APRM«^ aplitude power density and probability density function have been analyzed. The results indicate that the dynamic distortion is closely related to the terminal shock wave stability of transonic diffuser, and the distribution of Δί'^^ and PSD are important properties for dynamic distortion. NomenclatureIntroduction b = Channel height This paper provides a description of experimental f = frequency studies of dynamic distortion properties in a two-L = diffuser length dimensional transonic diffuser. Dynamic distortion is Μ = Mach number one of the important subjects of inlet/engine compap = pressure tibility technique. It greatly affects the performance Ρ(Δρ) = probability density function and stability of the propulsion system. Recently t = time several specialists have shown their interest in investiTu = turbulence factor gating dynamic distortion mechanisms, prediction u = flow velocity methods of peak level of dynamic distortion and χ = streamwise coordinate (χ = 0 at difdynamic distortion simulation technology /1-4/. This fuser throat, positive streamwise) paper intends to provide a better understanding of y = vertical coordiante (y = 0 on the the dynamic distortion property and to support diffuser centerline, positive upward) development of flowfield prediction and simulation W = diffuser width for supersonic inlet. AR = area ratio of diffuser Dynamic distortion of inlet diffuser is increased APD = amplitude probability density funcwith the supercritical degree increase, so distortion is tion closely related to the transonic flow of diffuser. Most PSD = power spectral density function importantly, the formation of turbulence type of ΔΡ = fluctuating pressure dynamic distortion is produced by shock wave/ boundary layer interaction, combined with a subsonic, Subscripts adverse pressure gradient behind the terminal shock wave. 1 = inlet station For quantitative determination of dynamic distor-2 = exit station tion in a transonic diffuser, experiments of superc = cut-off filter critical transonic flow in a diffuser have been e = core flow performed. Generally, dynamic distortion has a ranav = average dom property. In the experimental investigation, the RMS = root-mean-square dynamic measuring technique was used. Dynamic

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