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
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).
Download or read book Experimental Investigation Base Pressure on Blunt trailing edge Wings at Supersonic Velocities written by Dean R. Chapman and published by . This book was released on 1952 with total page 852 pages. Available in PDF, EPUB and Kindle. Book excerpt: The pressres acting on the base of blunt-trailing-edge airfoils have been measured at Mach numbers of 1.25, 1.5, 2.0, and 3.1 and at Reynolds numbers from 0.2 to 3.8 million. Data are presented for 29 profiles both with laminar and with turbulent boundary layers approaching the trailing edges of the wings. The base pressure is found to be a function primarily of Mach number and the ratio of the boundary layer thickeness at the trailing edge to the trailing-edge thickness.
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:
Download or read book Investigation of the Effects of Model Scale and Stream Reynolds Number on the Aerodynamic Characteristics of Two Rectangular Wings at Supersonic Speeds on the Langley 9 inch Supersonic Tunnel written by Donald E. Coletti and published by . This book was released on 1955 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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:
Download or read book Transonic Aerodynamic Characteristics of a Tailless Fixed wing Supersonic Transport Model written by Edward J. Ray and published by . This book was released on 1966 with total page 84 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Reynolds Number Effects on Leading Edge Radius Variations of a Supersonic Transport at Transonic Conditions written by S. M. B. Rivers and published by . This book was released on 2001 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Effects of Unit Reynolds Number Nose Bluntness and Roughness on Boundary Layer Transition written by J. Leith Potter and published by . This book was released on 1960 with total page 166 pages. Available in PDF, EPUB and Kindle. Book excerpt: Condtions encountered in the high Mach number flow regime are show to profoundly affect the longitudinal extent of the boundary layer from beginning to end of transition, the distribution of fluctuation energy in the laminar layer, and effectiveness of surface roughness in promoting transition. A critical layer of intense local energy fluctuations was found at all Mach numbers studied. The existence of such a critical layer is predicted by stability theory. Hot-wire surveys of the laminar, transitional, and turbulent boundary layers are presented to illustrate the critical layer in laminar flow and subsequent development into the transition process. The relation between boundary layer transition on flat plates and cones in supersonic flow is explored and a process for correcting data to account for leading edge bluntness is devised. On the basis of a comparison of data corrected for the effects of leading edge geometry, it is shown that the Reynolds umber of transition on a cone is three times that on a vanishingly thin flate plate. Close agreement between data from various wind tunnels is demonstrated. Study of the effect of finite leading edges yields significant illustrations of the influence of unit Reynolds number on boundary layer transition. A correlation of the effects of surface roughness on transition is achieved. This treatment includes two- and three-dimensional roughness in both subsonic and supersonic streams. At this time only zero pressure gradients have been studied. The entire range of movement of transition from its position with no roughness up to its reaching the roughness element is describable by the procedure give. Examples of application of the correlation results show excellent agreement with experimental data from a variety of sources. Implications concerning tripping hypersonic boundary layers are discussed.
Download or read book A Selected Listing of NASA Scientific and Technical Reports for written by and published by . This book was released on 1957 with total page 388 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Aerodynamic Characteristics of a Three engine Supersonic Transport Model Having a Low Aspect ratio Variable sweep Warped Wing written by and published by . This book was released on 1964 with total page 70 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book NASA Scientific and Technical Publications written by and published by . This book was released on 1989 with total page 62 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Monthly Catalog of United States Government Publications written by United States. Superintendent of Documents and published by . This book was released on 1960 with total page 1812 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book NASA Scientific and Technical Reports written by United States. National Aeronautics and Space Administration Scientific and Technical Information Division and published by . This book was released on 1966 with total page 1440 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 1995 with total page 464 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Wind tunnel Investigation of Leading edge Thrust on Arrow Wings in Supersonic Flow written by Robert J. Mack and published by . This book was released on 1983 with total page 84 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Low speed Aerodynamic Characteristics of a Supersonic Transport Model with a High aspect ratio Variable sweep Warped Wing written by and published by . This book was released on 1964 with total page 62 pages. Available in PDF, EPUB and Kindle. Book excerpt:
