Greetings, all
I have attached some aerofoil data for a Clark Y foil. This data is also
available in my spread sheet.
The Reynolds number is given in the heading as
5.00E+04, 1.00E+05, 5.00E+05, 1.00E+06 and 3.00E+06. I need to find Cl and
Cd at an AoA for a Reynolds number:
GetCl(AoA, Re)
GetCd(AoA, RE)
Interpolation functions are easy enough to find.
Here<http://www.vbaexpress.com/forum/showthread.php?41522-Linear-Interpolation&p=263514&viewfull=1#post263514>is
one that also includes sorting. But I need to run this over the
"two-dimensional" array that is the aerofoil data. Not all aerofoil AoA's
are the same for the different Re (xfoil was used to obtain this data).
This means that creating an array would have blanks at some AoA's, unless I
interpolate to fill in the gaps.
I was thinking that I might write a code to create an array of cl and cd
for each Re-number at the AoA, but the AoA is not always a neat number.
However, neither is the Reynolds number.
How would you do it? Could you use an interpolation function such as the
one I linked to (not a preference, so I'm impartial)?
Thanks in advance
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CLARK_Y 5.00E+04 CLARK_Y 1.00E+05 CLARK_Y
5.00E+05 CLARK_Y 1.00E+06 CLARK_Y 3.00E+06
AOA CL CD AOA CL CD AOA CL
CD AOA CL CD AOA CL CD
-5 -0.4467 0.07923 -5.2 -0.4446 0.0632 -5 -0.1411
0.01247 -5 -0.1526 0.00989 -5 -0.1653 0.0074
-4 -0.3817 0.04728 -4 -0.2578 0.03062 -4 -0.0357
0.01105 -4 -0.0448 0.0089 -4 -0.0534 0.0069
-3 -0.2767 0.03638 -3 -0.1074 0.02584 -3 0.0705
0.00986 -3 0.0646 0.00822 -3 0.0594 0.00664
-2 -0.182 0.03198 -2 0.0424 0.0227 -2 0.1773
0.00884 -2 0.1744 0.00764 -2 0.1724 0.0064
-1 -0.0797 0.02921 -1 0.2137 0.01943 0 0.376
0.00653 3 0.7424 0.00647 -1 0.2844 0.00615
0 0.0505 0.02935 0 0.3683 0.01874 1 0.5441
0.00677 4 0.8325 0.00758 1 0.505 0.00576
1 0.2391 0.03329 1 0.4963 0.01815 2 0.6427
0.00709 5 0.9312 0.00837 5 0.9494 0.00662
2 0.3906 0.03595 2 0.6086 0.01771 3 0.7388
0.00762 6 1.0329 0.00908 6 1.0505 0.0073
3 0.5383 0.03747 3 0.7168 0.01736 4 0.8316
0.00847 7 1.1337 0.00989 7 1.1424 0.00886
4 0.6728 0.03815 4 0.8221 0.01728 5 0.9218
0.00976 8 1.2222 0.01155 8 1.2366 0.01025
5 0.7697 0.04054 5 0.9224 0.01794 6 1.0178
0.01085 9 1.3004 0.01381 9 1.3183 0.01249
6 0.8873 0.04163 6 1.0194 0.01939 7 1.1144
0.01189 10 1.3668 0.01631 10 1.4067 0.01391
7 0.9316 0.04846 7 1.1098 0.02092 8 1.209
0.01294 11 1.413 0.01977 11 1.4851 0.01543
8 1.1052 0.04266 8 1.1976 0.02289 9 1.2854
0.01511 12 1.4606 0.02341 12 1.5523 0.01735
9 1.1955 0.04366 9 1.2771 0.02526 10 1.3444
0.01793 13 1.4944 0.02854 13 1.6098 0.01996
10 1.2915 0.0459 10 1.3255 0.02802 11 1.3944
0.02132 14 1.5113 0.03596 14 1.6638 0.02308
11 1.2969 0.0559 11 1.3488 0.03146 12 1.4143
0.02724 15 1.5151 0.04588 15 1.6987 0.02804
12 0.9223 0.11926 12 1.3692 0.0366 13 1.4317
0.03435 16 1.5051 0.05897 16 1.7298 0.03393
13 0.9408 0.13786 15 1.3011 0.07272 14 1.4281
0.04474 17 1.4693 0.07731 17 1.7451 0.04209
14.2 1.3197 0.07568 16 1.3051 0.08483 15 1.4078
0.05879 18 1.4096 0.10081 18 1.7432 0.05324
16.1 0.8982 0.20038 17 1.2843 0.10237 16 1.3753
0.07612 19 1.3772 0.12119 19 1.7107 0.06956
17 0.9357 0.21549 18 1.0187 0.19113 17 1.3575
0.09265 20 1.3526 0.14076 20 1.6536 0.09092
18 0.9772 0.23463 19 1.0262 0.21529 18 1.3445
0.10878 21 1.3378 0.15911 21 1.5891 0.11484
19 0.9892 0.24529 20 1.0276 0.24384 19 1.3486
0.1209 22 1.3309 0.17639 22 1.5246 0.14007
20 1.0082 0.25566 21 1.0534 0.25775 20 1.3372
0.13822 23 1.3334 0.19123 23 1.4701 0.16505
21 1.0368 0.26832 22 1.0809 0.27119 21 1.324
0.15654 24 1.3266 0.20962 24 1.4197 0.19091
22 1.0665 0.28073 23 1.1107 0.28394 22 1.3026
0.17792 25 1.3135 0.23062 25 1.3812 0.216
23 1.1012 0.29562 24 1.1495 0.29863 23 1.2607
0.2074 90 0 1 26 1.3631 0.23713
24 1.133 0.309 26 1.1981 0.31913 90 0
1 27 1.3594 0.2551
25 1.1653 0.32292 27 1.2267 0.33025
28 1.3643 0.27058
26 1.1861 0.32806 28 1.2568 0.3418
29 1.3706 0.28563
27 1.2138 0.339 29 1.2806 0.35104
30 1.3749 0.30153
28 1.2428 0.35099 30 1.3062 0.36114
31 1.3734 0.3207
29 1.2714 0.36329 32 1.3539 0.38002
90 0 1
30 1.2944 0.37014 33 1.3759 0.38947
31 1.3189 0.38 34 1.3963 0.39753
33 1.3644 0.39801 35 1.4149 0.40595
34 1.385 0.40689 36 0.7997 0.41505
35 1.4044 0.41545 37 0.7996 0.42711
36 1.4219 0.42239 90 0 1
38 1.4529 0.43582
90 0 1
