1960
DOI: 10.2514/8.8501
|View full text |Cite
|
Sign up to set email alerts
|

The Effect of Controlled Three-Dimensional Roughness on Boundary-Layer Transition at Supersonic Speeds

Help me understand this report

Search citation statements

Order By: Relevance

Paper Sections

Select...
3
1
1

Citation Types

1
11
1

Year Published

1965
1965
2019
2019

Publication Types

Select...
6
1

Relationship

0
7

Authors

Journals

citations
Cited by 43 publications
(13 citation statements)
references
References 2 publications
1
11
1
Order By: Relevance
“…The effect of the experimental parameters on the repeatability of these cases will be explained in this section. The effect of small changes in experimental conditions on transition is consistent with historical data showing that, for critical roughness, the transition location moves quickly forward for small changes in conditions [43,44].…”
Section: Repeatability Of Transition For Small Roughness Heightssupporting
confidence: 88%
See 1 more Smart Citation
“…The effect of the experimental parameters on the repeatability of these cases will be explained in this section. The effect of small changes in experimental conditions on transition is consistent with historical data showing that, for critical roughness, the transition location moves quickly forward for small changes in conditions [43,44].…”
Section: Repeatability Of Transition For Small Roughness Heightssupporting
confidence: 88%
“…These conditions include roughness shape, freestream Mach number, and wind-tunnel test geometry, all of which could affect Re k;crit . For example, Van Driest et al [43,44] calculate Re k using the boundary-layer edge conditions instead of the local conditions. Smith and Clutter [42] show observations of critical roughness at supersonic speeds, but for two-dimensional roughness, using conditions behind a normal shock to calculate Re k .…”
Section: B Effect Of Roughness Height On Rms Pressurementioning
confidence: 99%
“…The figure is redrawn from Fig. 12 in [11], and the Mach number at the boundary-layer edge was M e 1:9. Van Driest and McCauley measured transition due to an azimuthal row of spherical roughness elements, on a 5-deg half-angle sharp cone at zero angle of attack, in the 12-in.…”
Section: Typical Effects Of Roughnessmentioning
confidence: 99%
“…Van Driest and McCauley measured transition due to an azimuthal row of spherical roughness elements, on a 5-deg half-angle sharp cone at zero angle of attack, in the 12-in. (305-mm) supersonic wind tunnel at the Jet Propulsion Laboratory [11]. The freestream Mach number was varied from 1.97 to 3.84 by varying the flexibleplate nozzle.…”
Section: Typical Effects Of Roughnessmentioning
confidence: 99%
See 1 more Smart Citation