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 PDF Download

Author: F. E. West
Publisher:
ISBN:
Category : Aerofoils
Languages : en
Pages : 56

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Book Description
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.

Author: E. O. Pearson
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 48

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Book Description
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.

Author: Morton Cooper
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 59

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Book Description
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.

Author: Morton Cooper
Publisher:
ISBN:
Category :
Languages : en
Pages : 59

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Book Description

Author: F. E. West
Publisher:
ISBN:
Category : Aerofils
Languages : en
Pages : 44

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Book Description
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.

Author: W. F. Lindsey
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 94

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Book Description
An investigation has been conducted in the Langley rectangular high-speed tunnel to determine the effect of compressibility on the pressure distribution for a modified NACA 65,3-019 airfoil having a 0.20-chord flap. The investigation was made for an angle-of-attack range extending from -2 to 12 deg at 0.20 flap deflections from 0 to -12 degree. Test data were obtained for Mach numbers from 0.28 to approximately 0.74. The results show that the effectiveness of the trailing-edge-type control surface rapidly decreased and approached zero as the Mach number increased above the critical value.

Author: G. Chester Furlong
Publisher:
ISBN:
Category : Aerofoils
Languages : en
Pages : 52

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Book Description
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.

Author: F. E. West
Publisher:
ISBN:
Category :
Languages : en
Pages : 44

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Book Description

Author: Langley Aeronautical Laboratory
Publisher: Hassell Street Press
ISBN: 9781014098665
Category :
Languages : en
Pages : 48

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Book Description
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.

Author: James E. Fitzpatrick
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 34

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Book Description
The effects of Mach number and Reynolds number on the maximum lift coefficient of a wing of NACA 64-210 airfoil sections are presented. The wing was tested with and without partial-span and full-span slip flaps deflected 60 degrees. Peak maximum lift coefficients were measured at Mach numbers between 0.12 and 0.20, depending on the Reynolds number range and flap configuration.