02.11.2014 Views

Phase II Final Report - NASA's Institute for Advanced Concepts

Phase II Final Report - NASA's Institute for Advanced Concepts

Phase II Final Report - NASA's Institute for Advanced Concepts

SHOW MORE
SHOW LESS

Create successful ePaper yourself

Turn your PDF publications into a flip-book with our unique Google optimized e-Paper software.

Chapter 3.0 Vehicle Design<br />

3.3 Wing Aerodynamics<br />

Figures 3-91 through 3-93 show the streamwise velocity contour at three spanwise stations. The<br />

last location (z= -0.5m) is approximately at the center of the blown flap. The streamwise separation<br />

is clearly evident and these figures must be compared with the corresponding figures <strong>for</strong> the<br />

blown flap case. These three views along the wing show stagnation points and regions where lift<br />

is being produced.<br />

Figure 3-91: U Velocity Contours on Symmetry Plane<br />

Figure 3-92: U Velocity Contours at Span Location z = -0.26<br />

103

Hooray! Your file is uploaded and ready to be published.

Saved successfully!

Ooh no, something went wrong!