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Record Details

Record 31 of 53173
Transonic Loads Characteristics of a 3-Percent-Thick 60 deg Delta-Wing-Body
Offline Availability: Go to Request Form
Author and Affiliation:
Swihart, John M.(NASA Langley Research Center, Hampton, VA, United States)
Foss, Willard E., Jr.(NASA Langley Research Center, Hampton, VA, United States)
Abstract: An investigation has been made in the Langley 16-foot transonic tunnel to determine the aerodynamic loading characteristics of a 3-percent-thick, aspect-ratio - 2.06, 60 deg delta-wing-body combination. The Mach number range was from 0.80 t o 1.05 and the average Reynolds number based on wing mean aerodynamic chord was 10 x 10(exp 6). The angle-of-attack range was from 0 deg to 26 deg but was limited at the highest Mach numbers by tunnel drive power. Pressure distributions, spanwise loadings, integrated wing coefficients, and tabulated pressure coefficients are presented for the range of Mach numbers and angles of attack. The results indicate that a free leading-edge separation vortex is the dominant flow-field phenomenon at all Mach numbers and that, consequently, there are only slight changes in the spanwise loadings with Mach number. There is a slight outboard shift in center of pressure with an increase in Mach number. The chord-wise position of the center of pressure varies from 46 t o 55 percent of the mean aerodynamic chord when the Mach number i s increased from 0.80 to l.05.
Publication Date: May 01, 1961
Document ID:
20040008224
(Acquired Jan 28, 2004)
Subject Category: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
Report/Patent Number: NASA-TN-D-830, L-1543
Document Type: Technical Report
Financial Sponsor: NASA; Washington, DC, United States
Organization Source: NASA Langley Research Center; Hampton, VA, United States
Description: 128p; In English
Distribution Limits: Unclassified; Publicly available; Unlimited
Rights: No Copyright
NASA Terms: TRANSONIC WIND TUNNELS; LOADS (FORCES); AERODYNAMIC LOADS; DELTA WINGS; FLOW DISTRIBUTION; PRESSURE DISTRIBUTION; AIRFOIL PROFILES; ANGLE OF ATTACK; ASPECT RATIO; CENTER OF PRESSURE; CHORDS (GEOMETRY)
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