Further Results of Natural Laminar Flow Flight Test Experiments 850862
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.
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. Download Citation
Author(s):
W. H. Wentz, A. Ahmed, R. Nyenhuis
Affiliated:
Wichita State University, Cessna Aircraft Co.
Pages: 16
Event:
General Aviation Aircraft Meeting and Exposition
ISSN:
0148-7191
e-ISSN:
2688-3627
Also in:
General Aviation Aircraft Aerodynamics-SP-0621, SAE 1985 Transactions-V94-85
Related Topics:
Flight tests
Statistical analysis
Wings
Turbulence
Chemicals
Pressure
Acoustics
Noise
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