Download or read book The Effects of Compressibility on the Lift Pressure and Load Characteristics of a Tapered Wing of NACA 66 series Airfoil Sections written by Morton Cooper and published by . This book was released on 1948 with total page 59 pages. Available in PDF, EPUB and Kindle. Book excerpt: Results of tests of a 12-foot-span tapered wing of NACA 66-series sections at Mach numbers up to 0.69 indicated that the maximum lift coefficient varied appreciably with Mach number and was affected to a marked extent by the sharpness of the lending edge at the higher Mach numbers. No significant changes in span load distributions occurred through the Mach number range for all angles of attack below the stall. The formation of extensive local supersonic-flow regions caused the center of pressure to move forward at high angles of attack and high Mach numbers.

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 Effect of Compressibility on the Lift Pressure and Load Characteristics of a Tapered Wing of NACA 66 series Airfoil Sections written by Morton Cooper and published by . This book was released on 1948 with total page 59 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 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 Normal force Pressure and Load Characterstics of a Tapered Wing of NACA 66 series Airfoil Sections with Split Flaps written by F. E. West and published by . This book was released on 1948 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt: The effects of compressibility on the normal-force, pressure, and load characteristics of a 12-foot tapered wing of NACA 66-series airfoil sections equipped with split flaps is presented for Mach numbers up to 0.585 and an angle-of-attack range of -4 degrees through the stall. Both 55-percent-span and 98-percent-span split flaps deflected 60 degrees and having chords of 20-percent of the wing chord were tested.

Download or read book Effects of Compressibility on Normal force Pressure and Load Characteristics of a Tapered Wing of NACA 66 series Airfoil Sections with Split Flaps written by F. E. West and published by . This book was released on 1948 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt:

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 1948 with total page 322 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Technical Information Pilot written by and published by . This book was released on 1949 with total page 694 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book List of Technical Notes 1947 1953 written by United States. National Advisory Committee for Aeronautics and published by . This book was released on 1954 with total page 162 pages. Available in PDF, EPUB and Kindle. Book excerpt:

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 1370 pages. Available in PDF, EPUB and Kindle. Book excerpt:

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 Annual Report of the National Advisory Committee for Aeronautics written by United States. National Advisory Committee for Aeronautics and published by . This book was released on 1948 with total page 692 pages. Available in PDF, EPUB and Kindle. Book excerpt: Includes the Committee's Reports no. 1-1058, reprinted in v. 1-37.

Download or read book Report written by and published by . This book was released on 1945 with total page 620 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Report National Advisory Committee for Aeronautics written by United States. National Advisory Committee for Aeronautics and published by . This book was released on 1949 with total page 702 pages. Available in PDF, EPUB and Kindle. Book excerpt:

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 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 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.