NACA 2R1 error when plotting coordinates
 

Hi guys,

I'm pretty new to plotting airfoil coordinates actually this is my first try. I want to get accurate airfoils for the Bf109B-E (NACA 2R1 14.2 [wing root] - NACA 2R1 11 [wing tip]) and the later Bf109F-K (NACA 2R1 14.2 [wing root] - NACA 2R1 11.35 [wing tip]).

The root airfoil stayed the same throughout the aircraft versions, but from the F-K version the wing tip airfoil changed slightly. I have got some coordinates for the NACA 2R1 airfoil from varying sources on the net and have input them onto the online plotter here: http://www.windandwet.com/windturbin...tter/index.php

The two sets that I have for this airfoil differ slightly for some reason. The first set is the NACA 2R1 12 and seems to work fine in the plotter giving me an airfoil shape:

1.00000 0.00130
0.94801 0.00900
0.89900 0.01645
0.85274 0.02355
0.80903 0.03023
0.76769 0.03639
0.72855 0.04206
0.69146 0.04730
0.65627 0.05212
0.62287 0.05652
0.59112 0.06048
0.56094 0.06400
0.53220 0.06711
0.50483 0.06984
0.47874 0.07219
0.45384 0.07419
0.43007 0.07586
0.40737 0.07721
0.38566 0.07827
0.36489 0.07906
0.34501 0.07957
0.32596 0.07984
0.30771 0.07986
0.29020 0.07963
0.27340 0.07918
0.25728 0.07855
0.24178 0.07778
0.22689 0.07687
0.21257 0.07581
0.19879 0.07458
0.18552 0.07314
0.17275 0.07154
0.16044 0.06982
0.14858 0.06797
0.13713 0.06605
0.12610 0.06402
0.11544 0.06188
0.10515 0.05961
0.09521 0.05721
0.08561 0.05468
0.07633 0.05200
0.06735 0.04917
0.05866 0.04618
0.05026 0.04300
0.04212 0.03961
0.03424 0.03595
0.02660 0.03192
0.01920 0.02740
0.01203 0.02200
0.00508 0.01459
0.00168 0.00854
0.00000 0.00000
0.00000 0.00000
0.00168 -0.00581
0.00508 -0.01009
0.01203 -0.01541
0.01920 -0.01924
0.02660 -0.02229
0.03424 -0.02475
0.04212 -0.02684
0.05026 -0.02865
0.05866 -0.03026
0.06735 -0.03169
0.07633 -0.03298
0.08561 -0.03416
0.09521 -0.03523
0.10515 -0.03615
0.11544 -0.03695
0.12610 -0.03763
0.13713 -0.03823
0.14858 -0.03874
0.16044 -0.03920
0.17275 -0.03959
0.18552 -0.03992
0.19879 -0.04018
0.21257 -0.04038
0.22689 -0.04052
0.24178 -0.04059
0.25728 -0.04058
0.27340 -0.04048
0.29020 -0.04032
0.30771 -0.04011
0.32596 -0.03985
0.34501 -0.03954
0.36489 -0.03917
0.38566 -0.03873
0.40737 -0.03822
0.43007 -0.03763
0.45384 -0.03695
0.47874 -0.03619
0.50483 -0.03534
0.53220 -0.03440
0.56094 -0.03335
0.59112 -0.03216
0.62287 -0.03086
0.65627 -0.02937
0.69146 -0.02765
0.72855 -0.02562
0.76769 -0.02322
0.80903 -0.02034
0.85274 -0.01688
0.89900 -0.01270
0.94801 -0.00762
1.00000 -0.00130

The second set is as follows, however it gives an error: error on line 22 at column 41: Entity 'nbsp' not defined



100.0006 0.1491
99.9410 0.1592
99.7622 0.1897
99.4646 0.2405
99.0491 0.3115
98.5164 0.4025
97.8680 0.5136
97.1053 0.6444
96.2302 0.7947
95.2446 0.9643
94.1509 1.1527
92.9516 1.3596
91.6496 1.5844
90.2479 1.8266
88.7496 2.0854
87.1584 2.3599
85.4777 2.6493
83.7116 2.9523
81.8640 3.2679
79.9391 3.5945
77.9413 3.9306
75.8750 4.2745
73.7451 4.6242
71.5561 4.9776
69.3131 5.3324
67.0209 5.6863
64.6849 6.0366
62.3101 6.3806
59.9019 6.7154
57.4657 7.0381
55.0070 7.3455
52.5313 7.6347
50.0445 7.9026
47.5523 8.1461
45.0604 8.3622
42.5749 8.5480
40.1018 8.7009
37.6471 8.8182
35.2170 8.8980
32.8178 8.9380
30.4556 8.9368
28.1368 8.8931
25.8676 8.8059
23.6542 8.6749
21.5028 8.5000
19.4196 8.2817
17.4106 8.0208
15.4818 7.7184
13.6389 7.3764
11.8877 6.9966
10.2337 6.5815
8.6824 6.1335
7.2391 5.6554
5.9093 5.1505
4.6987 4.6216
3.6130 4.0721
2.6585 3.5060
1.8428 2.9277
1.1741 2.3441
0.6600 1.7663
0.3045 1.2132
0.0994 0.7139
0.0138 0.3010
0.0000 0.000000
0.0119 -0.1813
0.0191 -0.2415
0.0279 -0.3002
0.0639 -0.4748
0.1546 -0.7569
0.3401 -1.1267
0.6579 -1.5507
1.1292 -1.9917
1.7545 -2.4222
2.5261 -2.8270
3.4342 -3.1994
4.4696 -3.5376
5.6246 -3.8420
6.8928 -4.1132
8.2684 -4.3525
9.7461 -4.5613
11.3209 -4.7410
12.9880 -4.8928
14.7424 -5.0184
16.5795 -5.1190
18.4944 -5.1962
20.4822 -5.2515
22.5380 -5.2863
24.6567 -5.3022
26.8332 -5.3005
29.0622 -5.2828
31.3385 -5.2504
33.6568 -5.2046
36.0114 -5.1467
38.3971 -5.0777
40.8080 -4.9987
43.2386 -4.9105
45.6833 -4.8139
48.1362 -4.7096
50.5917 -4.5980
53.0440 -4.4795
55.4874 -4.3546
57.9161 -4.2234
60.3244 -4.0861
62.7067 -3.9430
65.0574 -3.7940
67.3709 -3.6395
69.6418 -3.4796
71.8648 -3.3146
74.0347 -3.1448
76.1463 -2.9706
78.1946 -2.7926
80.1749 -2.6114
82.0826 -2.4279
83.9131 -2.2428
85.6623 -2.0574
87.3260 -1.8727
88.9005 -1.6900
90.3821 -1.5108
91.7675 -1.3365
93.0535 -1.1685
94.2373 -1.0085
95.3163 -0.8580
96.2879 -0.7185
97.1503 -0.5915
97.9013 -0.4783
98.5396 -0.3802
99.0636 -0.2983
99.4724 -0.2336
99.7649 -0.1868
99.9407 -0.1585
99.9994 -0.1491

I am pasting both sets of coordinates into the plotter as they appear above. Can anyone spot which part is in error on the second set?

Does anyone have the confirmed airfoil coordinates for NACA 2R1 14.2 [wing root] - NACA 2R1 11 [wing tip] and (NACA 2R1 14.2 [wing root] - NACA 2R1 11.35 [wing tip]?

My aim is to export a .svg version of the airfoils for use in some drawings.

Any help would be really appreciated. Thank you.

What is your idea, what you want to do ?

Hi Fokke,

I basically want to draw and eventually model in a CAD program an early Bf109 and a late Bf109. So I would like to ascertain what the accurate airfoil coordinates were for the original aircraft. There are coordinates on the net that I have found as per above, but I would like to confirm what is correct.

Thanks.

The first set of Coordinates that I posted above are for the NACA 2R(1)12. I have read that the 12 denotes a maximum thickness of 12%. The maximum thickness of the early Bf109 airfoil shape was 14.2% [wing root] and 11% [wing tip] with the later versions being 14.2% [wing root] 11.35% [wing tip]. Is that correct?

The first set of coordinates were a set with better resolution and sourced from a Japanese website which also also has the following official coordinates for the 2R(1)12:

The first set of Coordinates that I posted above are for the NACA 2R(1)12. I have read that the 12 denotes a maximum thickness of 12%. The maximum thickness of the early Bf109 airfoil shape was 14.2% [wing root] and 11% [wing tip] with the later versions being 14.2% [wing root] 11.35% [wing tip]. Is that correct?

The first set of coordinates were a set with better resolution and sourced from a Japanese website which also also has the following official coordinates for the 2R(1)12:

http://www.rcuniverse.com/forum/atta...mentid=2208063

There is also some coordinates for the 2R(1)15 airfoil on page 514 of Report 572 National Advisory Committee for Aeronautics (figure 17). Could someone explain the formula for getting the correct coordinates for:

NACA 2R1 14.2
NACA 2R1 11
NACA 2R1 11.35

Any help is appreciated.

Hi , I made this for my models , I use the original airfoil for my F-G -K modifications of fokkerc models
Yes it is correct - with the later versions being 14.2% [wing root] 11.35% [wing tip] !

Hi Fokke, thanks. Some nice looking models you have there!

So I have the higher resolution coordinates for NACA 2R1 12. So presumably these are the original NACA 2R1 coordinates at 12%? So I need to calculate the original coordinates from the 12% coordinates (reverse percentage) so I can then multiply those original 2R1 coordinates by 14.2%, 11% and then 11.35% which will give me the early and late Bf109 airfoil coordinates? Is that correct?