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Book NASA SC 2 0714 Airfoil Data Corrected for Sidewall Boundary layer Effects in the Langley 0 3 meter Transonic Cryogenic Tunnel

Download or read book NASA SC 2 0714 Airfoil Data Corrected for Sidewall Boundary layer Effects in the Langley 0 3 meter Transonic Cryogenic Tunnel written by Renaldo V. Jenkins and published by . This book was released on 1989 with total page 64 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Book NASA Scientific and Technical Publications

Download or read book NASA Scientific and Technical Publications written by and published by . This book was released on 1990 with total page 92 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Book Scientific and Technical Aerospace Reports

Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1989 with total page 960 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Book The Aeronautical Journal

Download or read book The Aeronautical Journal written by and published by . This book was released on 1989 with total page 484 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Book Aerodynamic Performance and Pressure Distributions for a NASA SC 2 0714 Airfoil Tested in the Langley 0 3 meter Transonic Cryogenic Tunnel

Download or read book Aerodynamic Performance and Pressure Distributions for a NASA SC 2 0714 Airfoil Tested in the Langley 0 3 meter Transonic Cryogenic Tunnel written by Renaldo V. Jenkins and published by . This book was released on 1988 with total page 308 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Book Government Reports Announcements Index

Download or read book Government Reports Announcements Index written by and published by . This book was released on 1989-07 with total page 1534 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Book High Reynolds Number Tests of a NASA SC 3 0712 B Airfoil in the Langley 0 3 Meter Transonic Cryogenic Tunnel

Download or read book High Reynolds Number Tests of a NASA SC 3 0712 B Airfoil in the Langley 0 3 Meter Transonic Cryogenic Tunnel written by William Garland Johnson and published by . This book was released on 1985 with total page 170 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Book NASA Scientific and Technical Publications

Download or read book NASA Scientific and Technical Publications written by and published by . This book was released on 1989 with total page 64 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Book NASA Technical Paper

Download or read book NASA Technical Paper written by and published by . This book was released on 1979 with total page 40 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Book NASA SP

    NASA SP

    Book Details:
  • Author :
  • Publisher :
  • Release : 1962
  • ISBN :
  • Pages : 178 pages

Download or read book NASA SP written by and published by . This book was released on 1962 with total page 178 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Book NASA Scientific and Technical Publications

Download or read book NASA Scientific and Technical Publications written by United States. National Aeronautics and Space Administration and published by . This book was released on 1987 with total page 180 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Book Corrections for Attached Sidewall Boundary layer Effects in 2 dimensional Airfoil Testing

Download or read book Corrections for Attached Sidewall Boundary layer Effects in 2 dimensional Airfoil Testing written by and published by . This book was released on 1985 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt: The problems of sidewall boundary-layer effects in airfoil testing is treated by considering the changes in the flow area due to boundary-layer thinning under the influence of the airfoil flowfield. Using von Karman's momentum integral equation, it is shown that the sidewall boundary-layer thickness in the region of the airfoil can reduce to about half the undisturbed value under the conditions prevailing in testing of supercritical airfoils. A Mach number correction due to this increased width of the flow passage is proposed. Using the small disturbance approximation, the effect of the sidewall boundary-layers is shown to be equivalent to a change in the test Mach number and also in the airfoil thickness. Comparison of the results of this approach with other similarity rules and correlation of the experimental data demonstrate the applicability of the analysis presented from low speeds to transonic speeds.