Download or read book Effects of Compressibility on the Maximum Lift Characteristics and Spanwise Load Distribution of a 12 foot span Fighter type Wing of NACA 230 series Airfoil Sections written by E. O. Pearson and published by . This book was released on 1945 with total page 48 pages. Available in PDF, EPUB and Kindle. Book excerpt: Force and pressure-distribution measurements were made on a fighter-type wing model of conventional NACA 230-series airfoil sections in the Langley 16-foot high-speed tunnel to determine the effects of compressibility on the maximum lift characteristics and the span-wise load distribution. The range of angle of attack investigated was from -10 to +24 degrees. The Mach range of from 0.20 to 0.70 at small and medium angles of attack and from 0.15 to 0.625 at very large angles of attack. Maximum lift coefficient increased up to a Mach number of 0.3, decreased rapidly to a Mach number of 0.55, and then decreased moderately. At high speeds, maximum lift coefficient was reached at from 10 to 12 degrees beyond the stalling angle. In high-speed stalls, resultant load underwent a moderate shift outward.
Download or read book Effects of Compressibility on Lift and Load Characteristics of a Tapered Wing of NACA 64 210 Airfoil Sections Up to a Mach Number of 0 60 written by F. E. West and published by . This book was released on 1949 with total page 56 pages. Available in PDF, EPUB and Kindle. Book excerpt: The effects of compressibility on the lift, pressure, pitching-moment, and load characteristics of a 12-foot tapered wing having NACA 64-210 airfoil sections and aspect ratio of 6 is presented for Mach numbers up to 0.60 and an angle-of-attack range of -4 degrees up through the stall.
Download or read book The Spanwise Distribution of Lift for Minimum Induced Drag of Wings Having a Given Lift and a Given Bending Moment written by Robert T. Jones and published by . This book was released on 1950 with total page 708 pages. Available in PDF, EPUB and Kindle. Book excerpt: The problem of the minimum induced drag of wings having a given lift and a given span is extended to include cases in which the bending moment to be supported by the wing is also given. Expressions for the spanwise load distribution and the minimum drag in terms of the lateral position of the load centroid are given. The results show a 15-percent reduction of the induced drag with a 15-percent increase in span over that for an elliptic loading having the same total lift and bending moment.
Download or read book Calculation of Tunnel induced Upwash Velocities for Swept and Yawed Wings written by S. Katzoff and published by . This book was released on 1948 with total page 670 pages. Available in PDF, EPUB and Kindle. Book excerpt: The tunnel-induced upwash for a wing of any plan form and load distribution in a rectangular tunnel may be found with the aid of only two charts. One is given in the present paper. The second must be computed for each tunnel. The second chart is given for an open tunnel of 2:1 width-height ratio, a closed tunnel of 2:5 width-height ratio, and a closed tunnel of 10:7 width-height ratio.
Download or read book Technical Note National Advisory Committee for Aeronautics written by United States. National Advisory Committee for Aeronautics and published by . This book was released on 1950 with total page 856 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Technical Note written by and published by . This book was released on 1947 with total page 566 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Further Experiments on the Flow and Heat Transfer in a Heated Turbulent Air Jet written by Stanley Corrsin and published by . This book was released on 1949 with total page 696 pages. Available in PDF, EPUB and Kindle. Book excerpt: Measurements have been made of the mean total-head and temperature fields in a round turbulent jet with various initial temperatures.
Download or read book Theory and Procedure for Determining Loads and Motions in Chine immersed Hydrodynamic Impacts of Prismatic Bodies written by Emanuel Schnitzer and published by . This book was released on 1952 with total page 740 pages. Available in PDF, EPUB and Kindle. Book excerpt: A theoretical method is derived for computing the motions and hydrodynamic loads during water landings of prismatic bodies involving appreciable immersion of the chines. A simplified method of computation covering flat-plate and V-bottom bodies with beam-loading coefficients greater than unity is given as a separate section. Comparisons of theory with experiment are presented as plots of impact lift coefficient and maximum draft-beam ratio against flight-path angle and as time histories of loads and motions. Fair agreement is found to exist for chine-immersed landings for angles of dead rise of 0 degrees and 30 degrees, beam-loading coefficients from 1 to 36.5, flight-path angles from 2 to 90 degrees, and trims from 6 to 45 degrees.
Download or read book Index of NACA Technical Publications written by United States. National Advisory Committee for Aeronautics and published by . This book was released on 1949 with total page 616 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Effects of Mach Number Up to 0 34 and Reynolds Number Up to 8 000 000 on the Maximum Lift Coefficient of a Wing of NACA 66 series Airfoil Sections written by G. Chester Furlong and published by . This book was released on 1950 with total page 52 pages. Available in PDF, EPUB and Kindle. Book excerpt: The effects of Mach numbers up to 0.34 and Reynolds number up to 8,000,000 on the maximum lift coefficient of the wing of NACA 66-weries airfoil sections are presented. The wing was tested with full-span and partial-span split flaps deflected 60 degrees and without flaps. The results indicated that the peak values of maximum lift coefficient occurred at free-stream Mach numbers of approximately 0.212 and 0.227 for the flaps-retracted configuration and 0.138 and 0.196 for the full-span flaps-deflected configuration for tunnel pressures of 33 and 14.7 pounds per square inch, respectively.
Download or read book A Selected Listing of NASA Scientific and Technical Reports for written by and published by . This book was released on 1949 with total page 664 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Effects of Compressibility on the Maximum Lift Characteristics and Spanwise Load Distribution of a 12 foot span Fighter type Wing of NACA 230 series Airfoil Sections written by Langley Aeronautical Laboratory and published by Hassell Street Press. This book was released on 2021-09-09 with total page 48 pages. Available in PDF, EPUB and Kindle. Book excerpt: This work has been selected by scholars as being culturally important and is part of the knowledge base of civilization as we know it. This work is in the public domain in the United States of America, and possibly other nations. Within the United States, you may freely copy and distribute this work, as no entity (individual or corporate) has a copyright on the body of the work. Scholars believe, and we concur, that this work is important enough to be preserved, reproduced, and made generally available to the public. To ensure a quality reading experience, this work has been proofread and republished using a format that seamlessly blends the original graphical elements with text in an easy-to-read typeface. We appreciate your support of the preservation process, and thank you for being an important part of keeping this knowledge alive and relevant.
Download or read book Dynamometer stand Investigation of the Muffler Used in the Demonstration of Light airplane Noise Reduction written by K. R. Czarnecki and published by . This book was released on 1948 with total page 670 pages. Available in PDF, EPUB and Kindle. Book excerpt: The attenuation characteristics of the muffler used in the demonstration of light airplane noise reduction were investigated on the ground dynamometer stand at the Langley full-scale tunnel. Sound, back pressure, and engine power output were measured. The ground tests indicated that a reduction of 10 to 15 decibels was to be expected from this muffler.
Download or read book Wartime Report written by and published by . This book was released on 194? with total page 690 pages. Available in PDF, EPUB and Kindle. Book excerpt: Reproductions of reports, some declassified, of research done at Langley Memorial Aeronautical Laboratory during World War II. The order of reports does not represent when they were chronologically issued. Reference to the original version of each report is included.
Download or read book Collection and Analysis of Wind tunnel Data on the Characteristics of Isolated Tail Surfaces with and Without End Plates written by WIlliam R. Bates and published by . This book was released on 1947 with total page 538 pages. Available in PDF, EPUB and Kindle. Book excerpt: The aerodynamic characteristics of 19 isolated tail surfaces have been determined by wind-tunnel tests and tests have also been made of rectangular airfoils of various aspect ratios with and without double end plates of various shapes. Thes data from these tests have been collected and analyzed.
Download or read book Wartime Report written by United States. National Advisory Committee for Aeronautics and published by . This book was released on with total page 300 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Theory of Wing Sections written by Ira H. Abbott and published by Courier Corporation. This book was released on 2012-04-26 with total page 704 pages. Available in PDF, EPUB and Kindle. Book excerpt: Concise compilation of subsonic aerodynamic characteristics of NACA wing sections, plus description of theory. 350 pages of tables.
