Download or read book High Reynolds Number Test of the Boeing Tr77 Airfoil in the Langley 0 3 Meter Transonic Cryogenic Tunnel written by National Aeronautics and Space Adm Nasa and published by Independently Published. This book was released on 2018-11-06 with total page 80 pages. Available in PDF, EPUB and Kindle. Book excerpt: A Boeing TR77 airfoil associated with the Advanced Technology Airfoil Test (ATAT) program was tested in the Langley 0.3 m Transonic Cryogenic Tunnel. Limited analysis of the data indicated that increasing Reynolds number for a fixed Mach number resulted in increased normal-force, nose-down pitching moment, and decreased drag coefficient. Increasing Mach number while keeping the Reynolds number constant yielded the expected increase in normal-force slopes, nose-down pitching moment coefficients, and decrease in angle of attack associated with maximum normal-force coefficient. Turbulent boundary layer flow was achieved over the airfoil at low Reynolds numbers for the test Mach number range using aluminum discs. Chu, Julio and Flechner, Stuart G. and Hill, Acquilla S. and Rozendaal, Roger A. Langley Research Center...
Download or read book High Reynolds Number Test of the Boeing TR77 Airfoil in the Langley 0 3 meter Transonic Cryogenic Tunnel written by and published by . This book was released on 1990 with total page 84 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book High Reynolds Number Tests of the NASA SC 2 0012 Airfoil in the Langley 0 3 meter Transonic Cryogenic Tunnel written by Raymond E. Mineck and published by . This book was released on 1987 with total page 64 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book High Reynolds Number Tests of the NASA SC 2 0012 Airfoil in the Langley 0 3 Meter Transonic Cryogenic Tunnel written by Raymond E. Mineck and published by . This book was released on 1987 with total page 64 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Pressure Distributions from High Reynolds Number Tests of a Boeing BAC 1 Airfoil in the Langley 0 3 meter Transonic Cryogenic Tunnel written by William G. Jr Johnson and published by . This book was released on 1985 with total page 282 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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 176 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Pressure Distributions from High Reynolds Number Tests of a Boeing BAC I 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 276 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book High Reynolds Number Tests of the Cast 10 2 DOA 2 Airfoil in the Langley 0 3 meter Transonic Cryogenic Tunnel Phase 2 written by and published by . This book was released on 1984 with total page 310 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Pressure Distribution from High Reynolds Number Tests of a NASA SC 3 0712 B Airfoil in the Langley 0 3 meter Transonic Cryogenic Tunnel written by and published by . This book was released on 1985 with total page 416 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book High Reynolds Number Tests of the NASA SC 2 0012 Airfoil in the Langley 0 3 Meter Transonic Cryogenic Tunnel written by Raymond E. Mineck and published by . This book was released on 1987 with total page 55 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Pressure Distributions from 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 416 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book High Reynolds Number Tests of a Douglas DLBA 032 Airfoil in the Langley 0 3 meter Transonic Cryogenic Tunnel written by and published by . This book was released on 1986 with total page 132 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Pressure Distributions from High Reynolds Number Transonic Tests of an NACA 0012 Airfoil in the Langley 0 3 meter Transonic Cryogenic Tunnel written by and published by . This book was released on 1987 with total page 400 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1992 with total page 1572 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Reynolds Number Tests of an NPL 9510 Airfoil in the Langley 0 3 meter Transonic Cryogenic Tunnel written by Renaldo V. Jenkins and published by . This book was released on 1983 with total page 92 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Simulation of Flight Test Conditions in the Langley Pilot Transonic Cryogenic Tunnel written by Robert A. Kilgore and published by . This book was released on 1974 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt: The theory and advantages of the cryogenic tunnel concept are briefly reviewed. The unique ability to vary temperature independently of pressure and Mach number allows, in addition to large reductions in model loads and tunnel power, the independent determination of Reynolds number, Mach number, and aeroelastic effects on the aerodynamic characteristics of the model. Various combinations of Reynolds number and dynamic pressure are established to represent accurately flight variations of aeroelastic deformation with altitude changes. The consequences of the thermal and caloric imperfections of the test gas under cryogenic conditions were examined and found to be insignificant for operating pressures up to 5 atm. The characteristics of the Langley pilot transonic cryogenic tunnel are described and the results of initial tunnel operation are presented. Tests of a two-dimensional airfoil at a Mach number of 0.85 show identical pressure distributions for a chord Reynolds number of 8,600,000 obtained first at a stagnation pressure of 4.91 atm at a stagnation temperature of 322.0 K and then at a stagnation pressure of 1.19 atm at a stagnation temperature of 116.5 K.
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:
