F-16XL wing pressure distributions and shock fence results from Mach 1.4 to Mach 2.0
By: Stephen F. Landers and John A. Saltzman [with] Lisa J. Bjarke.
Contributors: Bjarke, Lisa J.; Saltzman, John A.; Hugh L. Dryden Flight Research Center.
Series: NASA/TM -- 97-206219; NASA technical memorandum -- 97-206219.
Publisher: National Aeronautics and Space Administration, Dryden Flight Research Center; National Technical Information Service, [distributor
Published: 1997
Place of publication: Edwards, Calif; Springfield, VA
Language: eng
Number of pages: 41
Subjects: Aerodynamics, Supersonic.; Airplanes -- Wings.; F-16 (Jet fighter plane); Laminar flow.; Supersonic planes -- Design and construction.
Notes: "October 1997."

"Performing organization report number H-2055"--Report documentation page.

Includes bibliographical references.

Prepared by NASA Dryden Flight Research Center 529 31 24 00 24 00