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
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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
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Author : F. E. West
language : en
Publisher:
Release Date : 1949
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 has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1949 with Aerofoils categories.
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.
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
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Author : E. O. Pearson
language : en
Publisher:
Release Date : 1945
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 has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1945 with Aerodynamic load categories.
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.
The Effects Of Compressibility On The Lift Pressure And Load Characteristics Of A Tapered Wing Of Naca 66 Series Airfoil Sections
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Author : Morton Cooper
language : en
Publisher:
Release Date : 1948
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 has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1948 with Aerodynamic load categories.
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.
The Effect Of Compressibility On The Lift Pressure And Load Characteristics Of A Tapered Wing Of Naca 66 Series Airfoil Sections
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Author : Morton Cooper
language : en
Publisher:
Release Date : 1948
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 has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1948 with categories.
Effects Of Compressibility On Normal Force Pressure And Load Characterstics Of A Tapered Wing Of Naca 66 Series Airfoil Sections With Split Flaps
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Author : F. E. West
language : en
Publisher:
Release Date : 1948
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 has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1948 with Aerofils categories.
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.
Effect Of Compressibility On The Pressures And Forces Acting On A Modified Naca 65 3 019 Airfoil Having A 0 20 Chord Flap
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Author : W. F. Lindsey
language : en
Publisher:
Release Date : 1946
Effect Of Compressibility On The Pressures And Forces Acting On A Modified Naca 65 3 019 Airfoil Having A 0 20 Chord Flap written by W. F. Lindsey and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1946 with Aerodynamic load categories.
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.
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
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Author : G. Chester Furlong
language : en
Publisher:
Release Date : 1950
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 has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1950 with Aerofoils categories.
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.
Effects Of Mach Number Variation Between 0 07 And 0 34 And Reynolds Number Variation Between 970 000 And 8 100 000 On The Maximum Lift Coefficient Of A Wing Of Naca 64 210 Airfoil Sections
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Author : James E. Fitzpatrick
language : en
Publisher:
Release Date : 1952
Effects Of Mach Number Variation Between 0 07 And 0 34 And Reynolds Number Variation Between 970 000 And 8 100 000 On The Maximum Lift Coefficient Of A Wing Of Naca 64 210 Airfoil Sections written by James E. Fitzpatrick and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1952 with Airplanes categories.
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.
Effects Of Compressibility On Normal Force Pressure And Load Characteristics Of A Tapered Wing Of Naca 66 Series Airfoil Sections With Split Flaps
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Author : F. E. West
language : en
Publisher:
Release Date : 1948
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 has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1948 with categories.
A Scale And Turbulence Effects On The Lift And Drag Characteristics Of The Naca 653 418
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Author : John H. Quinn
language : en
Publisher:
Release Date : 1944
A Scale And Turbulence Effects On The Lift And Drag Characteristics Of The Naca 653 418 written by John H. Quinn and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1944 with Aerodynamics categories.
Summary: An investigation in two NACA wind tunnels has determined the effect of Reynolds number and stream turbulence on the lift and drag characteristics of a low-drag airfoil, the NACA 653-418, a=1.0 section, particularly at low Reynolds numbers, to give an indication of the performance of low-drag wings in low-scale tests. The results are correlated with similar data for the same airfoil section in the NACA two-dimensional low-turbulence pressure tunnel to provide data over a range of Reynolds number from 0.19 to 9.0 x 106. Large increases in minimum drag coefficient were found as the Reynolds number decreased. This effect was particularly marked at Reynolds numbers below 1.5 x 106. At Reynolds numbers below 1.5 x 106, stream turbulence had little effect on the drag characteristics of the NACA 653-418 airfoil section when compared on the basis of test Reynolds number but, at higher Reynolds numbers, stream turbulence had a detrimental effect on drag. Large decreases in maximum lift coefficient were found with decreasing Reynolds number; most of this decrease was encountered at Reynolds numbers above 2.0 x 106. Marked differences in maximum lift were apparent between the results obtained at high and low turbulence. When compared on the basis of effective Reynolds number, however, fair agreement was reached between the data obtained under both turbulence conditions.