Details of airfoil (aerofoil)(n64212mb-il) NACA 64(1)-212 MOD B NACA-NASA/AMES/Hicks 63(1)-212 MOD B airfoil
NASA NACA-CB-L4G10-1944 对带有0.20翼弦分裂式襟翼NACA 66(215)-216,66,1-212和65(下标1)-212机翼的风洞研究 NASA NACA-ACR-3L20-1943 对操纵面特性15的风洞研究.NACA 66(215)-014机翼上0.30翼弦普通襟翼的各种轮廓改装 NASA NACA-ARR-L4J05-1944 对带有0.32翼弦双开缝襟翼NACA 23021机翼的风洞研究 ...
t values, we can compute the coordinates for an entire airfoil using the following relationships:1. Pick values of x from 0 to the maximum chord c.2. Compute the mean camber line coordinates by plugging the values of m and p into the following equations for each of the x coordinates.
NASA NACA-CB-L4G10-1944 对带有0.20翼弦分裂式襟翼NACA 66(215)-216,66,1-212和65(下标1)-212机翼的风洞研究 NASA NACA-TN-4122-1957 当马赫数为3时,通过NACA空速管静态压力孔口气流的外部干扰效应 NASA NACA-TN-1417-1947 带有33.4%弦的襟翼和襟翼弦20.1%突出部分NACA 0009—64机翼的高速风洞试验 NASA...
Details of airfoil (aerofoil)(n64212ma-il) NACA 64(1)-212 MOD A NACA-NASA/AMES/Hicks 63(1)-212 MOD A airfoil