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- W2022672403 abstract "A 1/15-scale model of the F-16C aircraft was tested at subsonic and transonic speeds to determine the effects of small nose-probe chines on the high angle-of-attack aerodynamic and stability characteristics. Off-body flow visualization using a laser vapor screen technique and six-component forces and moments were obtained at freestream Mach numbers of 0.30, 0.60, and 0.80. The nose-probe chines generated strong vortices interacting with the vortices generated over the smooth forebody or over the strakes. These vortices in turn led to global flow unsteadiness and model dynamics at the high angles of attack. The test results underscore the sensitivity of the high angle-of-attack flow field to small geometry changes in the nose region." @default.
- W2022672403 created "2016-06-24" @default.
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- W2022672403 date "1990-01-08" @default.
- W2022672403 modified "2023-09-27" @default.
- W2022672403 title "Impact of nose-probe chines on the vortex flows about the F-16C" @default.
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- W2022672403 doi "https://doi.org/10.2514/6.1990-386" @default.
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