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Record Details

Record 15 of 18918
Accounting for Laminar Run & Trip Drag in Supersonic Cruise Performance Testing
Offline Availability: Go to Request Form
Author and Affiliation:
Goodsell, Aga M.(NASA Ames Research Center, Moffett Field, CA United States)
Kennelly, Robert A.(NASA Ames Research Center, Moffett Field, CA United States)
Abstract: An improved laminar run and trip drag correction methodology for supersonic cruise performance testing was derived. This method required more careful analysis of the flow visualization images which revealed delayed transition particularly on the inboard upper surface, even for the largest trip disks. In addition, a new code was developed to estimate the laminar run correction. Once the data were corrected for laminar run, the correct approach to the analysis of the trip drag became evident. Although the data originally appeared confusing, the corrected data are consistent with previous results. Furthermore, the modified approach, which was described in this presentation, extends prior historical work by taking into account the delayed transition caused by the blunt leading edges.
Publication Date: Dec 01, 1999
Document ID:
20000020881
(Acquired Mar 03, 2000)
Subject Category: AERODYNAMICS
Document Type: Conference Paper
Publication Information: 1999 NASA High-Speed Research Performance Workshop; Volume 1; Part 2; 1163-1196; (NASA/CP-1999-209704/VOL1/PT2); (SEE 20000020876)
Financial Sponsor: NASA Ames Research Center; Moffett Field, CA United States
Organization Source: NASA Ames Research Center; Moffett Field, CA United States
Description: 34p; In English
Distribution Limits: Unclassified; Publicly available; Unlimited
Rights: No Copyright
NASA Terms: FLOW VISUALIZATION; AERODYNAMIC DRAG; BOUNDARY LAYER TRANSITION; SUPERSONIC DRAG; AIRCRAFT DESIGN; LAMINAR BOUNDARY LAYER; SUPERSONIC TRANSPORTS; MACH NUMBER; REYNOLDS NUMBER; BLUNT LEADING EDGES
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