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Technical Note - National Advisory Committee for Aeronautics
  • Language: en
  • Pages: 988
Index of NACA Technical Publications
  • Language: en
  • Pages: 306

Index of NACA Technical Publications

  • Type: Book
  • -
  • Published: 1956
  • -
  • Publisher: Unknown

None

A Selected Listing of NASA Scientific and Technical Reports for ...
  • Language: en
  • Pages: 750

A Selected Listing of NASA Scientific and Technical Reports for ...

  • Type: Book
  • -
  • Published: 1949
  • -
  • Publisher: Unknown

None

Report
  • Language: en
  • Pages: 48

Report

  • Type: Book
  • -
  • Published: 1958
  • -
  • Publisher: Unknown

None

Annual Report - National Advisory Committee for Aeronautics
  • Language: en

Annual Report - National Advisory Committee for Aeronautics

  • Type: Book
  • -
  • Published: 1957
  • -
  • Publisher: Unknown

Includes the Committee's Technical reports no. 1-1058, reprinted in v. 1-37.

A Compilation of Research Reports of Physical Research Division, Dynamic Loads Division, Loads Division, 1921 - 1973
  • Language: en
  • Pages: 134
Monthly Catalog of United States Government Publications
  • Language: en
  • Pages: 368

Monthly Catalog of United States Government Publications

  • Type: Book
  • -
  • Published: 1951
  • -
  • Publisher: Unknown

None

Studies of the Use of Freon-12 as a Wind-tunnel Testing Medium
  • Language: en
  • Pages: 668

Studies of the Use of Freon-12 as a Wind-tunnel Testing Medium

  • Type: Book
  • -
  • Published: 1953
  • -
  • Publisher: Unknown

A number of studies relating to the use of Freon-12 as a substitute medium for air in aerodynamic testing have been made. The use of Freon-12 instead of air makes possible large savings in wind-tunnel drive power. Because of the fact that the ratio of specific heats is approximately 1.13 for Freon-12 as compared with 1.4 for air, some differences exist between data obtained in Freon-12 and air. Methods for predicting aerodynamic characteristics of bodies in air from data obtained in Freon-12, however, have been developed from the concept of similarity of the streamline pattern. These methods, derived from consideration of two-dimensional flows, provide substantial agreement in all cases for which comparative data are available. These data consist of measurements throughout a range of Mach number from approximately 0.4 to 1.2 of pressure distributions and hinge moments on swept and unswept wings having aspect ratios ranging from 4.0 to 9.0, including cases where a substantial part of the wing was stalled.