Record Details

Flight Tests of a Supersonic Natural Laminar Flow Airfoil
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Author and Affiliation:
Frederick, Michael A.(NASA Dryden Flight Research Center, Edwards, CA United States);
Banks, Daniel W.(NASA Dryden Flight Research Center, Edwards, CA United States);
Garzon, G. A.(Aerion Corp., Reno, NV, United States);
Matisheck, J. R.(Aerion Corp., Reno, NV, United States)
Abstract: A flight-test campaign of a supersonic natural laminar flow airfoil has been recently completed. The test surface was an 80-inch (203 cm) chord and 40-inch (102 cm) span article mounted on the centerline store location of an F-15B airplane (McDonnell Douglas Corporation, now The Boeing Company, Chicago, Illinois). The test article was designed with a leading edge sweep of effectively 0 deg to minimize boundary layer crossflow. The test article surface was coated with an insulating material to avoid significant heat transfer to and from the test article structure to maintain a quasi-adiabatic wall. An aircraft-mounted infrared camera system was used to determine boundary layer transition and the extent of laminar flow. The tests were flown up to Mach 2.0 and chord Reynolds numbers in excess of 30 million. The objectives of the tests were to determine the extent of laminar flow at high Reynolds numbers and to determine the sensitivity of the flow to disturbances. Both discrete (trip dots) and 2-D disturbances (forward-facing steps) were tested. A series of oblique shocks, of yet unknown origin, appeared on the surface, which generated sufficient crossflow to affect transition. Despite the unwanted crossflow, the airfoil performed well. The results indicate the sensitivity of the flow to the disturbances, which can translate into manufacturing tolerances, were similar to that of subsonic natural laminar flow wings.
Publication Date: Dec 01, 2015
Document ID:
20160000701
(Acquired Jan 13, 2016)
Subject Category: FLUID MECHANICS AND THERMODYNAMICS; AERODYNAMICS
Report/Patent Number: NASA/TM-2015-218940, DFRC-E-DAA-TN28448
Document Type: Technical Report
Financial Sponsor: NASA Dryden Flight Research Center; Edwards, CA United States
Organization Source: NASA Dryden Flight Research Center; Edwards, CA United States
Description: 33p; In English
Distribution Limits: Unclassified; Publicly available; Unlimited
Rights: Copyright; Distribution as joint owner in the copyright
NASA Terms: SUPERSONIC CRUISE AIRCRAFT RESEARCH; LAMINAR FLOW; SUPERSONIC AIRFOILS; AIRFOIL PROFILES; CHORDS (GEOMETRY); BOUNDARY LAYERS; LEADING EDGE SWEEP; SWEEP ANGLE; INSULATION; BOUNDARY LAYER TRANSITION; FLIGHT TESTS; INFRARED INSTRUMENTS; PRESSURE GRADIENTS; SENSITIVITY ANALYSIS
Other Descriptors: SUPERSONIC BOUNDARY LAYER; LAMINAR FLOW; BOUNDARY LAYER TRANSTITION
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