Naca Profile

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Ordinates And Theoretical Pressure Distribution Data For Naca 6 And 6a Series Airfoil Sections With Thicknesses From 2 To 21 And From 2 To 15 Percent Chord Respectively

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Author : Elizabeth W. Patterson
language : en
Publisher:
Release Date : 1961

Ordinates And Theoretical Pressure Distribution Data For Naca 6 And 6a Series Airfoil Sections With Thicknesses From 2 To 21 And From 2 To 15 Percent Chord Respectively written by Elizabeth W. Patterson and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1961 with Aerofoils categories.

Summary: Basic thickness forms of the NACA 63-, 64-, 65- series and NACA 63A-, 64A-, 65 A-series airfoil sections are tabulated for thicknesses of 2, 3, 4, and 5 percent chord. Also presented for these thin airfoil sections are theoretical values of pressures and velocity ratios required to obtain theoretical airfoil pressure distributions. In addition, for each family of airfoil sections, cross plots are presented from which ordinates and pressure distributions can be easily obtained for airfoil sections of thicknesses intermediate to those presented in this report, in NACA Report 824 (from 6 to 21 percent chord for the NACA 6-series), and in NACA Report 903 (from 6 to 15 percent chord for the NACA 6A-series).

Airfoil Section Data Obtained In The N A C A Variable Density Tunnel As Affected By Support Interference And Other Corrections

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Author : Eastman Nixon Jacobs
language : en
Publisher:
Release Date : 1939

Airfoil Section Data Obtained In The N A C A Variable Density Tunnel As Affected By Support Interference And Other Corrections written by Eastman Nixon Jacobs and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1939 with Aerodynamics categories.

A Test Of Naca 66 2 116

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Author : William J. Underwood
language : en
Publisher:
Release Date : 1942

A Test Of Naca 66 2 116 written by William J. Underwood and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1942 with Aerodynamic load categories.

Tests were made at the Langley two-dimensional low-turbulence pressure tunnel of a mode of the NACA 66,2-116, a = 0.6 airfoil section representing the root section of the wing for the XP-63 airplane.

Investigation In The Langley 19 Foot Pressure Tunnel Of Two Wings Of Naca 65 210 And 64 210 Airfoil Sections With Various Type Flaps

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Author : James C. Sivells
language : en
Publisher:
Release Date : 1948

Investigation In The Langley 19 Foot Pressure Tunnel Of Two Wings Of Naca 65 210 And 64 210 Airfoil Sections With Various Type Flaps written by James C. Sivells and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1948 with Aerofoils categories.

An investigation has been conducted in the Langley 19-foot pressure tunnel to determine the maximum lift and stalling characteristics of two thin wings equipped with several types of flaps. Split, single slotted, and double slotted flaps were tested on one wing which had NACA 65-210 airfoil sections and split and double slotted flaps were tested on the other, which had NACA 64-210 airfoil sections. Both wings had zero sweep, an aspect ratio of 9, and a ratio of root to tip chord of 2.5. Wings were tested with and without a representative fuselage and with and without leading-edge roughness.

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.

Tests Of An Area Suction Flap On An Naca 64a010 Airfoil At High Subsonic Speeds

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Author : Donald W. Smith
language : en
Publisher:
Release Date : 1960

Tests Of An Area Suction Flap On An Naca 64a010 Airfoil At High Subsonic Speeds written by Donald W. Smith and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1960 with Aerodynamics categories.

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.

High Tip Speed Static Thrust Tests Of A Rotor Having Naca 63 215 A018 Airfol Sections With And Without Vortex Generators Installed

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Author : James P. Shivers
language : en
Publisher:
Release Date : 1960

High Tip Speed Static Thrust Tests Of A Rotor Having Naca 63 215 A018 Airfol Sections With And Without Vortex Generators Installed written by James P. Shivers and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1960 with Aerofoils categories.

Wind Tunnel Investigation Of The Boundary Layer On An Naca 0009 Airfoil Having 0 25 And 0 50 Airfoil Chord Plain Sealed Flaps

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Author : Jack D. Brewer
language : en
Publisher:
Release Date : 1948

Wind Tunnel Investigation Of The Boundary Layer On An Naca 0009 Airfoil Having 0 25 And 0 50 Airfoil Chord Plain Sealed Flaps written by Jack D. Brewer and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1948 with Aerofoils categories.

An investigation was conducted in the Langley 4- by 6-foot tunnel to determine the boundary-layer characteristics of an NACA 0009 airfoil equipped with 0.25- and 0.50-airfoil chord plain sealed flaps. The tests were made to define as thoroughly as possible the characteristics of two of the configurations used in a comprehensive investigation of control surface characteristics and also to provide additional data for comparison with previous boundary-layer analyses. The measured velocity profiles and the boundary-layer parameters determined from them are presented.

Comparison Of Pitching Moments Produced By Plain Flaps And By Spoilers And Some Aerodynamic Characteristics Of An Naca 23012 Airfoil With Various Types Of Aileron

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Author : Paul E. Purser
language : en
Publisher:
Release Date : 1945

Comparison Of Pitching Moments Produced By Plain Flaps And By Spoilers And Some Aerodynamic Characteristics Of An Naca 23012 Airfoil With Various Types Of Aileron written by Paul E. Purser and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1945 with Aerodynamics categories.

An analysis and comparison has been made of the pitching moment characteristics of airfoils with plain flaps and spoilers. Sectional characteristics of airfoil having retractable slotted flap with plain, slot-lip, or retractable ailerons are presented for a large range of aileron deflections. The analysis indicated that pitching moments produced by spoilers were less positive than those produced by plain flaps of equal effectiveness, also that pitching moments created by the spoiler increased less with the Mach number than similar moments produced by plain flaps. Positive values of pitching moment decreased as devices were located nearer airfoil leading edge.