Download or read book Wind Tunnel Force and Moment Tests excluding Drag at Mach Number 2 58 on Three fin and Four fin Models of the Skylark High Altitude Research Vehicle written by D. F. Morrison and published by . This book was released on 1962 with total page 45 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Keywords Index to U S Government Technical Reports permuted Title Index written by United States. Department of Commerce. Office of Technical Services and published by . This book was released on 1963 with total page 836 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Keywords Index to U S Government Technical Reports written by and published by . This book was released on 1962 with total page 1160 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Longitudinal Airplane Dynamics Wind Tunnel Test Equipment written by O. B. Tufts and published by . This book was released on 1955 with total page 246 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Wind Tunnel Investigation of the Forces and Moments Acting on a Cruciform Finned Model with Fixed and Freely Spinning Tail Assemblies at a Mach Number of 2 0 written by William E. DeGrafft and published by . This book was released on 1963 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt: Spinning cruciform finned models were tested to determine the normal force, pitching moment, side force and yawing moment characteristics at a Mach number of 2.0 and a free stream Reynolds number of 3.98 x 10 to the 6th power per foot. The models had fin cant angles of 0, 2 and 4 degrees. In addition the models with the 2 and 4 degree fin cant angles were constructed so that the fin assembly could rotate either with the body as a single unit or rotate freely with the body locked. The tests showed that for the spin rates developed during the test, the normal force and pitching moments for all models are independ ent of spin rate and fin cant angle. The yawing moment is reduced on the average by a factor of 0.76 if the fins are allowed to rotate freely while the body is held stationary. (Author).
Download or read book Wind Tunnel Magnus Testing of a Canted Fin Or Self rotating Configuration written by Anders S. Platou and published by . This book was released on 1971 with total page 30 pages. Available in PDF, EPUB and Kindle. Book excerpt: A source of error in the wind tunnel measurement of Magnus forces and moments on a self-rotating configuration has been detected, and means of overcoming the error are presented. The error is due to a normal force interaction brought about by the roll of the angle of attack plane which in turn is due to a small yaw angle of the model at zero angle of attack. The error is not a balance interaction error. The error can completely mask the true Magnus characteristics and can lead the experimenter to wrong conclusions. Although a computed correction may be made to existing data, the best method of eliminating the error is to obtain balance readings with and without spin at each angle of attack of interest.
Download or read book Investigation of Aerodynamic Effects of External Combustion Below Flat plate Model in 10 by 10 foot Wind Tunnel at Mach 2 4 written by Robert G. Dorsch and published by . This book was released on 1960 with total page 34 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book CFD Wing pylon finned Store Mutual Interference Wind Tunnel Experiment written by E. Rolland Heim and published by . This book was released on 1991 with total page 74 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Wind Tunnel Rolling Moment Measurements on a Wingless Model Having Three Stabilising Fins skylark at M written by B. E. Pecover and published by . This book was released on 1960 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Wind Tunnel Investigation of Nozzle Hinge Moments on Two Launch Vehicle Models at Mach Numbers 1 60 2 00 and 2 40 written by and published by . This book was released on 1964 with total page 62 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Large scale Wind tunnel Tests of a Deflected Slipstream STOL Model with Wings of Various Aspect Ratios written by V. Robert Page and published by . This book was released on 1968 with total page 58 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Wind Tunnel and Model Testing Panel written by North Atlantic Treaty Organization. Advisory Group for Aeronautical Research and Development and published by . This book was released on 1955 with total page 352 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Reports on Wind Tunnel Experiments in Aerodynamics written by Jerome Clarke Hunsaker and published by . This book was released on 1916 with total page 120 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Wind tunnel Tests of a 0 03 scale Model at Mach Number from 0 6 to 2 53 written by James C. Daugherty and published by . This book was released on 1979 with total page 216 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Transonic Wind Tunnel Test of a 14 Percent Thick Oblique Wing written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-08-04 with total page 436 pages. Available in PDF, EPUB and Kindle. Book excerpt: An experimental investigation was conducted at the ARC 11- by 11-Foot Transonic Wind Tunnel as part of the Oblique Wing Research Aircraft Program to study the aerodynamic performance and stability characteristics of a 0.087-scale model of an F-8 airplane fitted with an oblique wing designed by Rockwell International. The 10.3 aspect ratio, straight-tapered wing of 0.14 thickness/chord ratio was tested at two different mounting heights above the fuselage. Additional tests were conducted to assess low-speed behavior with and without flaps, aileron effectiveness at representative flight conditions, and transonic drag divergence with 0 degree wing sweep. Longitudinal stability data were obtained at sweep angles of 0, 30, 45, 60, and 65 degrees, at Mach numbers ranging from 0.25 to 1.40. Test Reynolds numbers varied from 3.2 to 6.6 x 10 exp 6/ft. and angle of attack ranged from -5 to +18 degrees. Most data were taken at zero sideslip, but a few runs were at sideslip angles of +/- 5 degrees. The raised wing position proved detrimental overall, although side force and yawing moment were reduced at some conditions. Maximum lift coefficient with the flaps deflected was found to fall short of the value predicted in the preliminary design document. The performance and trim characteristics of the present wing are generally inferior to those obtained for a previously tested wing designed at ARC. Kennelly, Robert A., Jr. and Kroo, Ilan M. and Strong, James M. and Carmichael, Ralph L. Ames Research Center NASA-TM-102230, A-89236, NAS 1.15:102230 RTOP 533-06-01...
Download or read book High Speed Wind Tunnel Testing written by Alan Pope and published by John Wiley & Sons. This book was released on 1965-01-15 with total page 496 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Wind tunnel flight Correlation 1981 written by L. Wayne McKinney and published by . This book was released on 1982 with total page 244 pages. Available in PDF, EPUB and Kindle. Book excerpt:
