1996
DOI: 10.1175/1520-0469(1996)053<1187:tpittw>2.0.co;2
|View full text |Cite
|
Sign up to set email alerts
|

Transport Processes in the Tropical Warm Pool Boundary Layer. Part I: Spectral Composition of Fluxes

Help me understand this report

Search citation statements

Order By: Relevance

Paper Sections

Select...
1
1
1
1

Citation Types

2
26
0

Year Published

1999
1999
2015
2015

Publication Types

Select...
10

Relationship

0
10

Authors

Journals

citations
Cited by 29 publications
(28 citation statements)
references
References 0 publications
2
26
0
Order By: Relevance
“…1, this conceptual model is consistent with observational evidence (for more information see: Hacker 1992, 1993;Williams et al 1996). It is also strongly supported by our LES (see subsection 2(d)).…”
Section: Large-eddy Boundary-layer Modelsupporting
confidence: 90%
“…1, this conceptual model is consistent with observational evidence (for more information see: Hacker 1992, 1993;Williams et al 1996). It is also strongly supported by our LES (see subsection 2(d)).…”
Section: Large-eddy Boundary-layer Modelsupporting
confidence: 90%
“…A spectral decomposition of aircraft data (not presented) showed that T and q were anticorrelated on scales greater than about 1-5 km, consistent with previous ndings (e.g. Williams et al 1996). It is possible, therefore, that largerscale processes are creating the observed skewness anticorrelation for the aircraft data.…”
Section: Results (A) Comparison Of Momentssupporting
confidence: 86%
“…Attack angle is measured by means of flow angle sensors mounted on or near the nose of the aircraft. Most commonly, the flow angle is obtained from pressure difference measurements δ P between a set of ports either located directly on the nose of the aircraft (radome technique; see, e.g., Brown et al 1983), or on a probe mounted near the front of an aircraft (e.g., Williams et al, 1996)-usually on a boom projecting forward of the aircraft nose (e.g., Khelif et al 1999). It is difficult to quantify the drift that may occur in this measurement, but we proceed as follows: we use a typical differential pressure sensitivity factor of κ = 3.7 (rad) −1 (Brown et al 1983), where κ is defined by the relation…”
Section: Measurement Accuracymentioning
confidence: 99%