airfoil excel sheet
DESCRIPTION
airfoilTRANSCRIPT
x y camber line thickness chord length max camber max thicknessupper lower 255 14 29
0 0 0 0 0 5.49019607843 11.372549025 6 -4 1 10
10 10 -5 2.5 15 location of max camber=12515 12 -6 3 18 4.9019607843120 15 -6.5 4.25 21.525 17 -7 5 2430 19 -7 6 2635 21 -7 7 2840 22 -6 8 2845 23 -6 8.5 2950 24 -5 9.5 2955 25 -4 10.5 2960 25 -3 11 2865 25 -3 11 2870 26 -2 12 2875 26 -1 12.5 2780 27 -0.5 13.25 27.585 27 0 13.5 2790 27 0 13.5 2795 27 0.2 13.6 26.8
100 27 0.3 13.65 26.7105 27 0.4 13.7 26.6110 27 0.5 13.75 26.5115 27 1 14 26120 27 1 14 26125 27 1 14 26130 27 1 14 26135 26 1 13.5 25140 26 1.5 13.75 24.5145 25 1.9 13.45 23.1150 25 2 13.5 23155 25 2 13.5 23160 24 2 13 22165 24 2.1 13.05 21.9170 23 2.1 12.55 20.9175 22 2 12 20180 21 3 12 18185 19.9 3 11.45 16.9190 18 3 10.5 15195 17 2.5 9.75 14.5200 16 2 9 14205 15 1.5 8.25 13.5210 14 1.5 7.75 12.5215 12.5 1 6.75 11.5220 11 1 6 10225 9 0 4.5 9
0 10 20 30 40 50 60 70 80 90100
110120
130140
150160
170180
190200
210220
230240
250
-10
-5
0
5
10
15
20
25
30
upperPolynomial (upper)lowerPolynomial (lower)camber linePolynomial (camber line)
230 7 0 3.5 7235 6 0 3 6240 5 -1 2 6245 2.5 -1 0.75 3.5250 1 -1 0 2255 0 0 0 0
airfoil name5512
0 10 20 30 40 50 60 70 80 90100
110120
130140
150160
170180
190200
210220
230240
250
-10
-5
0
5
10
15
20
25
30
upperPolynomial (upper)lowerPolynomial (lower)camber linePolynomial (camber line)
0 10 20 30 40 50 60 70 80 90100
110120
130140
150160
170180
190200
210220
230240
250
-10
-5
0
5
10
15
20
25
30
upperPolynomial (upper)lowerPolynomial (lower)camber linePolynomial (camber line)