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Further Results of Natural Laminar Flow Flight Test Experiments
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Abstract
Flight test experiments were conducted to measure the extent and nature of natural laminar flow on a smoothed test region of a swept-wing business jet wing. Surface hot film aneraometry and sublimating chemicals were used for transition detection.
Surface pressure distributions were measured using pressure belts. Engine noise was monitored by a microphone attached to the wing surface to study possible acoustic effects on stability of the laminar boundary layer, Side-slip conditions were flown to simulate changes in effective wing sweep. Flight instrumentation and ground data analysis techniques and a method for measuring intermittency of turbulence are described, Correlation was obtained between the hot film gage signals and chemicals for transition detection. Cross-flow vortices were observed for some flight conditions. Results of spectral and statistical analysis of the hot film signals for various flight test conditions are presented.
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Authors
Citation
Wentz, W., Ahmed, A., and Nyenhuis, R., "Further Results of Natural Laminar Flow Flight Test Experiments," SAE Technical Paper 850862, 1985, https://doi.org/10.4271/850862.Also In
References
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