Public Domain Aeronautical Software (PDAS)

Sample cases are shown that illustrate the input to the naca456 program for a number of typical airfoils. Only the data between &NACA and / is read by the program. The rest is helpful commentary.

#### 0012

NACA 0012 - four digit airfoil First two digits indicate no camber Last two digits indicate max t/c=12 percent &NACA NAME='NACA 0012', PROFILE='4', TOC=0.12, CAMBER='0'/

[ Examine output for this airfoil. Coarse output.]

#### 6412

NACA 6412 - This airfoil combines a 0012 thickness (four digit) with a two-digit 64 camber line. A 64 camber line has 6% max camber at 40% chord. &NACA NAME='NACA 6412', dencode=2, PROFILE='4', TOC=0.12, CAMBER='2', cmax=0.06, xmaxc=0.4/

[ Examine output for this airfoil. Fine output. ]

#### 16-015

NACA 16-015 - This airfoil is identical to a 0015-45 airfoil. The modified four-digit thickness has a leading edge index of 4 and the maximum thickness is at 50% chord &NACA NAME='NACA 16-015 [same as 0015-45]' profile='4m', leIndex=4, xmaxt=0.5, camber='0'/

[ Examine output for this airfoil. Fine output. ]

#### 23012

NACA 23012 - This airfoil combines a 230 mean line (three-digit) with a 0012 thickness (four digit). A 230 mean line has CL=0.3 and maximum camber at 15% chord. &NACA NAME = 'NACA 23012', dencode = 3, PROFILE = '4', TOC = 0.12, CAMBER = '3', CL = 0.3, XCMAX = 0.15/

[ Examine output for this airfoil. Very fine output. ]

#### 63A010

First three characters: 63A series thickness Fourth character: no camber (CL design=0) Last two digits: 10 percent t/c &NACA NAME='NACA 63A010', PROFILE='63A', TOC=0.10, CAMBER='0'/

[ Examine output for this airfoil. Coarse output. ]

#### 63A409

NACA 63A409 First three characters: 63A series thickness Fourth character: CL design=0.4 (63A airfoils always use 6-series modified mean line) Last two digits: 9 percent t/c &NACA NAME='NACA 63A409', PROFILE='63A', TOC=.09, CAMBER='6M', CL=0.4/

[ Examine output for this airfoil. Coarse output. ]

#### 64A005.92 and 64A004.29 (F-22)

F22 Airfoils - Sometimes, the thickness to chord ratio is not an exact integer in percent. For example, the F-22 uses a uncambered 64A section with 5.92 percent thickness at the root and 4.29 percent thickness at the tip. If it were 6 percent, we would write it as 64A006, but to make it 5.92 we write 64A005.92 for the designation. If there is a possibility of confusion, parentheses are sometimes employed, as in 65A(3.7)(11.32) where the design cl is 0.37 and the thickness to chord is 11.32 percent

NACA 64A005.92 First three characters: 64A series thickness Fourth character: CL design=0.0 (uncambered) Last five characters: 5.92 percent t/c &NACA name = 'NACA 64A005.92', profile= '64A', toc = .0592, camber = '6M', cl = 0.0, dencode=2/

[ Examine output for this airfoil. Fine output. ]

NACA 64A004.29 First three characters: 64A series thickness Fourth character: CL design=0.0 (uncambered) Last five characters: 4.29 percent t/c &NACA name = 'NACA 64A004.29', profile= '64A', toc = .0429, camber = '6M', cl = 0.0, dencode=2/

[ Examine output for this airfoil. Fine output. ]

Public Domain Aeronautical Software (PDAS)