EBookClubs

Read Books & Download eBooks Full Online

EBookClubs

Read Books & Download eBooks Full Online

Book A Reynolds Number Study of Wing Leading Edge Effects on a Supersonic Transport Model at Mach 0 3

Download or read book A Reynolds Number Study of Wing Leading Edge Effects on a Supersonic Transport Model at Mach 0 3 written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-06-13 with total page 110 pages. Available in PDF, EPUB and Kindle. Book excerpt: A representative supersonic transport design was tested in the National Transonic Facility (NTF) in its original configuration with small-radius leading-edge flaps and also with modified large-radius inboard leading-edge flaps. Aerodynamic data were obtained over a range of Reynolds numbers at a Mach number of 0.3 and angles of attack up to 16 deg. Increasing the radius of the inboard leading-edge flap delayed nose-up pitching moment to a higher lift coefficient. Deflecting the large-radius leading-edge flap produced an overall decrease in lift coefficient and delayed nose-up pitching moment to even higher angles of attack as compared with the undeflected large- radius leading-edge flap. At angles of attack corresponding to the maximum untrimmed lift-to-drag ratio, lift and drag coefficients decreased while lift-to-drag ratio increased with increasing Reynolds number. At an angle of attack of 13.5 deg., the pitching-moment coefficient was nearly constant with increasing Reynolds number for both the small-radius leading-edge flap and the deflected large-radius leading-edge flap. However, the pitching moment coefficient increased with increasing Reynolds number for the undeflected large-radius leading-edge flap above a chord Reynolds number of about 35 x 10 (exp 6). Williams, M. Susan and Owens, Lewis R., Jr. and Chu, Julio Langley Research Center RTOP 537-03-22-06

Book A Reynolds Number Study of Wing Leading Edge Effects on a Supersonic Transport Model at Mach 0 3

Download or read book A Reynolds Number Study of Wing Leading Edge Effects on a Supersonic Transport Model at Mach 0 3 written by M. Susan Williams and published by . This book was released on 1999 with total page 112 pages. Available in PDF, EPUB and Kindle. Book excerpt: A representative supersonic transport design was tested in the National Transonic Facility (NTF) in its original configuration with small-radius leading-edge flaps and also with modified large-radius inboard leading-edge flaps. Aerodynamic data were obtained over a range of Reynolds numbers at a Mach number of 0.3 and angles of attack up to 16 deg. Increasing the radius of the inboard leading-edge flap delayed nose-up pitching moment to a higher lift coefficient. Deflecting the large-radius leading-edge flap produced an overall decrease in lift coefficient and delayed nose-up pitching moment to even higher angles of attack as compared with the undeflected large- radius leading-edge flap. At angles of attack corresponding to the maximum untrimmed lift-to-drag ratio, lift and drag coefficients decreased while lift-to-drag ratio increased with increasing Reynolds number. At an angle of attack of 13.5 deg., the pitching-moment coefficient was nearly constant with increasing Reynolds number for both the small-radius leading-edge flap and the deflected large-radius leading-edge flap. However, the pitching moment coefficient increased with increasing Reynolds number for the undeflected large-radius leading-edge flap above a chord Reynolds number of about 35 x 10 (exp 6).

Book Reynolds Number Effects on a Supersonic Transport at Transonic Conditions

Download or read book Reynolds Number Effects on a Supersonic Transport at Transonic Conditions written by R. A. Wahls and published by . This book was released on 2001 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:

Book Effect of Leading edge Contour and Vertical tail Configuration on the Low speed Stability Characteristics of a Supersonic Transport Model Having a Highly swept Arrow Wing

Download or read book Effect of Leading edge Contour and Vertical tail Configuration on the Low speed Stability Characteristics of a Supersonic Transport Model Having a Highly swept Arrow Wing written by and published by . This book was released on 1978 with total page 64 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Book NASA s Contributions to Aeronautics Flight environment operations flight testing and research

Download or read book NASA s Contributions to Aeronautics Flight environment operations flight testing and research written by and published by . This book was released on 2010 with total page 1064 pages. Available in PDF, EPUB and Kindle. Book excerpt: Two-volume collection of case studies on aspects of NACA-NASA research by noted engineers, airmen, historians, museum curators, journalists, and independent scholars. Explores various aspects of how NACA-NASA research took aeronautics from the subsonic to the hypersonic era.-publisher description.

Book Reynolds Number Effects on a Supersonic Transport at Subsonic High lift Conditions

Download or read book Reynolds Number Effects on a Supersonic Transport at Subsonic High lift Conditions written by L. R. Owens and published by . This book was released on 2001 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:

Book Low speed Effects of High lift Devices on the Aerodynamic Characteristics of a Supersonic Transport Model with Outboard Tails

Download or read book Low speed Effects of High lift Devices on the Aerodynamic Characteristics of a Supersonic Transport Model with Outboard Tails written by William C. Sleeman and published by . This book was released on 1963 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Book A Comparison of Transition Reynolds Numbers from 12 in and 40 in Supersonic Tunnels

Download or read book A Comparison of Transition Reynolds Numbers from 12 in and 40 in Supersonic Tunnels written by C. J. Schueler and published by . This book was released on 1963 with total page 42 pages. Available in PDF, EPUB and Kindle. Book excerpt: Transition Reynolds number measurements on a hollow cylinder in the von Karman Gas Dynamics Facility's 12-inch and 40-inch supersonic tunnels show that the highest transition Reynolds numbers were obtained in the 40-inch tunnel, although the variations with unit Reynolds number were the same at Mach numbers 3 to 5. The influence of nose bluntness in the 40-inch tunnel corresponds closely with the results obtained in the 12-inch tunnel.

Book 39th AIAA Aerospace Sciences Meeting and Exhibit

Download or read book 39th AIAA Aerospace Sciences Meeting and Exhibit written by and published by . This book was released on 2001 with total page 656 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Book NASA Reference Publication

Download or read book NASA Reference Publication written by and published by . This book was released on 1977 with total page 1092 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Book NASA Langley Scientific and Technical Information Output 2001

Download or read book NASA Langley Scientific and Technical Information Output 2001 written by and published by . This book was released on 2002 with total page 166 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Book Effects of Leading edge Blunting on the Local Heat Transfer and Pressure Distributions Over Flat Plates in Supersonic Flow

Download or read book Effects of Leading edge Blunting on the Local Heat Transfer and Pressure Distributions Over Flat Plates in Supersonic Flow written by Marcus O. Creager and published by . This book was released on 1957 with total page 54 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation of the effect of leading-edge thickness on the flow over flat plates with square and cylindrical blunting was conducted at a Mach number of 4 and free-stream Reynolds numbers per inch of 2380 and 6600. Surface pressures were measured on a series of models whose leading-edge thicknesses ranged from 0.25 to 1 inch. Heat-transfer rates were measured from a flat plate which was blunted by a 1-inch-diameter cylindrical leading edge. All tests were performed with the instrumented surfaces at zero angle of sweep and zero angle of attack. For the test condition, the bow shock wave was detached and leading-edge shape had no effect on surface pressures aft of two leading-edge thicknesses. The surface pressures could be predicted by a combination of shock-wave boundary-layer interaction theory and blast wave theory. This combination applied equally well to similar data of other investigations. An empirical expression for local Reynolds number at the boundary-layer edge was found to correlate both the present data and data from other investigations covering a wide range of conditions. The local Reynolds number per inch was found to be lower than free-stream Reynolds number per inch, nearly constant for the test length, and to have negligible dependence on leading-edge bluntness. This reduction depends on the square root of the ratio of total pressures across the normal bow shock wave. The local Nusselt number was found to depend only on the local Reynolds number for the present tests, and is predicted by the familiar Pohlhausen flat-plate theory. As compared to the sharp condition, blunting the leading edge of flat plates, with consequent reduction of local total pressure, was found to increase the heat-transfer coefficients in the region where surface static pressures were high and to reduce the coefficients where the surface static pressures approached the free-stream value.