[항공기술] (영어,영문) Forces acting on an airplane, Airfoil, NACA airfoil

소개글

[항공기술] (영어,영문) Forces acting on an airplane, Airfoil, NACA airfoil에 대한 보고서 자료입니다.

목차

⧉ Forces acting on an airplane
⧉ Airfoil
⧉ NACA airfoil

본문내용

asis on maximizing laminar flow. The airfoil is described using six digits in the following sequence
The number "6" indicating the series.
One digit describing the distance of the minimum pressure area in tens of percent of chord.
The subscript digit gives the range of lift coefficient in tenths above and below the design lift coefficient in which favorable pressure gradients exist on both surfaces
A hyphen.
One digit describing the design lift coefficient in tenths.
Two digits describing the maximum thickness as percent of chord.
For example, the NACA 612-315 a=0.5 has the area of minimum pressure 10% of the chord back, maintains low drag 0.2 above and below the lift coefficient of 0.3, has a maximum thickness of 15% of the chord, and maintains laminar flow over 50% of the chord.

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