Download or read book A Review of Some Reynolds Number Effects Related to Bodies at High Angles of Attack written by Edward C. Polhamus and published by . This book was released on 1984 with total page 134 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Effects of Reynolds Number and Body Corner Radius on Aerodynamic Characteristics of a Space Shuttle type Vehicle at Subsonic Mach Numbers written by Leland Howard Jorgenson and published by . This book was released on 1972 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt: Static aerodynamic forces and moments were measured to study the effects of Reynolds number and body corner radius on the aerodynamic characteristics of a straight wing space shuttle orbiter at subsonic speeds. A 0.02-scale model was tested at Mach numbers from 0.3 to 0.9 and Reynolds numbers from about 600,000 to 3 million, based on body width. The body alone and the body with its wing and horizontal tail attached were tested at angles of attack from 35 to 75 degrees. The effects of rounding the body corners at the junctures connecting the bottom and sides were investigated for corner radii from 0 to 8.5 percent of the body width. At low subsonic Mach numbers (free stream Mach number approximately equal 0.3) the aerodynamic characteristics are affected significantly by changes in Reynolds number and body corner radius. With increase in Mach number to free stream Mach number = 0.9 the effect of Reynolds number seems to vanish, but a significant effect of body corner radius remains.

Download or read book Reynolds Number Effects at High Angles of Attack written by David F. Fisher and published by . This book was released on 1998 with total page 38 pages. Available in PDF, EPUB and Kindle. Book excerpt: Lessons learned from comparision between ground-based tests and flight measurements for the high-angle-of-attack programs on the F-18 High Alpha Research Vehicle (HARV), the X-29 forward-swept wing aircraft, and the X-31 enhanced fighter maneuverability aircraft are presented. On all three vehicles, Reynolds number effects were evident on the forebodies at high angles of attack. The correlation between flight and wind tunnel forebody pressure distributions for the F-18 HARV were improved by using twin longitudinal grit strips on the forebody of the wind-tunnel model. Pressure distributions obtained on the X-29 wind-tunnel model at flight Reynolds numbers showed excellent correlation with the flight data up to [alpha]=50 deg. Above [alpha]=50 deg. the pressure distributions for both flight and wind tunnel became asymmetric and showed poorer agreement, possibly because of the different surface finish of the model and aircraft. The detrimental effect of a very sharp nose apex was demonstrated on the X-31 aircraft. Grit strips on the forebody of the X-31 reduced the randomness but increased the magnitude of the asymmetry. Nose strakes were required to reduce the forebody yawing moment asymmetries and the grit strips on the flight test noseboom improved the aircraft.

Download or read book Effects of Reynolds Number and Flow Incidence on the Force Characteristics of a Family of Flat front Cylinders written by Vernard E. Lockwood and published by . This book was released on 1967 with total page 50 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Effect of Flow Incidence and Reynolds Number on Low speed Aerodynamic Characteristics of Several Noncircular Cylinders with Applications to Directional Stability and Spinning written by Edward Charles Polhamus and published by . This book was released on 1959 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Experimental Study of the Effects of Reynolds Number on High Angle of Attack Aerodynamic Characteristics of Forebodies During Rotary Motion written by and published by . This book was released on 1995 with total page 132 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Reynolds Number Influences in Aeronautics written by and published by . This book was released on 1993 with total page 178 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Aerodynamics of the Model Airplane Airfoil measurements written by Franz Wilhelm Schmitz and published by . This book was released on 1967 with total page 218 pages. Available in PDF, EPUB and Kindle. Book excerpt:

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 Computational Study of the Effect of Reynolds Number on a Body of Revolution at High Angles of Attack written by Mark John Rist and published by . This book was released on 1995 with total page 118 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book NASA Technical Memorandum written by and published by . This book was released on 1988 with total page 700 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Summary of Low Speed Airfoil Data written by Michael S. Selig and published by Soartech. This book was released on 1995 with total page 320 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Pressure and Force Characteristics of Noncircular Cylinders as Affected by Reynolds Number with a Method Included for Determining the Potential Flow about Arbitrary Shapes written by Edward Charles Polhamus and published by . This book was released on 1959 with total page 48 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Flight Reynolds Number Effects on a Contoured Boattail Nozzle at Subsonic Speeds written by Roger Chamberlin and published by . This book was released on 1974 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Longitudinal Aerodynamic Characteristics of Two Blunted Cone Reentry Configurations at Mach Numbers from 17 6 to 22 2 Including Some Reynolds Number Effects written by Dal V. Maddalon and published by . This book was released on 1966 with total page 42 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book NASA Technical Note written by and published by . This book was released on 1977 with total page 506 pages. Available in PDF, EPUB and Kindle. Book excerpt:

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