NASA SC(2)-0412 AIRFOIL (sc20412-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA SC(2)-0412 AIRFOIL (sc20412-il) Reynolds number: 100,000 Max Cl/Cd: 30.43 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sc20412-il-100000-n5.txt Download as CSV file: xf-sc20412-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NASA SC(2)-0412 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.500 -0.8122 0.07759 0.07127 -0.0422 1.0000 0.0431
-12.250 -0.8536 0.06854 0.06195 -0.0474 1.0000 0.0428
-12.000 -0.8818 0.06248 0.05563 -0.0496 1.0000 0.0429
-11.750 -0.9031 0.05780 0.05070 -0.0503 1.0000 0.0432
-11.500 -0.9205 0.05394 0.04657 -0.0500 1.0000 0.0436
-11.250 -0.9350 0.05060 0.04294 -0.0488 1.0000 0.0441
-11.000 -0.9417 0.04718 0.03913 -0.0482 1.0000 0.0448
-10.750 -0.9428 0.04395 0.03543 -0.0473 1.0000 0.0456
-10.500 -0.9306 0.04206 0.03347 -0.0466 1.0000 0.0463
-10.250 -0.9166 0.04056 0.03190 -0.0459 1.0000 0.0474
-10.000 -0.9025 0.03907 0.03028 -0.0452 1.0000 0.0488
-9.750 -0.8882 0.03737 0.02836 -0.0444 1.0000 0.0505
-9.500 -0.8733 0.03548 0.02611 -0.0436 1.0000 0.0524
-9.250 -0.8555 0.03395 0.02448 -0.0427 1.0000 0.0538
-9.000 -0.8368 0.03278 0.02330 -0.0420 1.0000 0.0553
-8.750 -0.8179 0.03167 0.02209 -0.0412 1.0000 0.0575
-8.500 -0.7984 0.03046 0.02068 -0.0404 1.0000 0.0601
-8.250 -0.7785 0.02925 0.01938 -0.0395 1.0000 0.0622
-8.000 -0.7586 0.02829 0.01846 -0.0387 1.0000 0.0642
-7.750 -0.7382 0.02741 0.01755 -0.0378 1.0000 0.0671
-7.500 -0.7174 0.02654 0.01653 -0.0369 1.0000 0.0703
-7.250 -0.6973 0.02561 0.01565 -0.0360 1.0000 0.0729
-7.000 -0.6767 0.02484 0.01491 -0.0352 1.0000 0.0762
-6.750 -0.6556 0.02414 0.01414 -0.0344 1.0000 0.0803
-6.500 -0.6349 0.02334 0.01337 -0.0336 1.0000 0.0841
-6.250 -0.6136 0.02265 0.01272 -0.0329 1.0000 0.0886
-6.000 -0.5916 0.02207 0.01206 -0.0322 1.0000 0.0942
-5.750 -0.5698 0.02132 0.01143 -0.0318 1.0000 0.1001
-5.500 -0.5469 0.02076 0.01084 -0.0314 1.0000 0.1076
-5.250 -0.5236 0.02010 0.01030 -0.0313 1.0000 0.1168
-5.000 -0.4995 0.01952 0.00980 -0.0313 1.0000 0.1288
-4.750 -0.4747 0.01894 0.00933 -0.0314 1.0000 0.1468
-4.500 -0.4488 0.01833 0.00891 -0.0319 1.0000 0.1750
-4.250 -0.4212 0.01756 0.00847 -0.0329 1.0000 0.2275
-4.000 -0.3889 0.01637 0.00796 -0.0355 1.0000 0.3426
-3.750 -0.3666 0.01595 0.00856 -0.0345 1.0000 0.5030
-3.500 -0.3486 0.01646 0.00929 -0.0317 1.0000 0.5734
-3.250 -0.3225 0.01673 0.00950 -0.0315 1.0000 0.6115
-3.000 -0.2994 0.01714 0.00987 -0.0304 1.0000 0.6360
-2.750 -0.2653 0.01751 0.01014 -0.0316 0.9962 0.6585
-2.500 -0.2345 0.01802 0.01063 -0.0316 0.9914 0.6735
-2.250 -0.2064 0.01862 0.01122 -0.0308 0.9861 0.6885
-2.000 -0.1783 0.01929 0.01190 -0.0298 0.9812 0.7037
-1.750 -0.1510 0.01974 0.01235 -0.0290 0.9751 0.7174
-1.500 -0.1181 0.02004 0.01261 -0.0296 0.9707 0.7280
-1.250 -0.0883 0.02014 0.01270 -0.0299 0.9645 0.7345
-1.000 -0.0562 0.02021 0.01276 -0.0306 0.9592 0.7392
-0.750 -0.0181 0.02018 0.01270 -0.0330 0.9558 0.7443
-0.500 0.0154 0.02007 0.01258 -0.0348 0.9490 0.7495
-0.250 0.0490 0.02005 0.01258 -0.0358 0.9439 0.7521
0.000 0.0826 0.02002 0.01258 -0.0370 0.9385 0.7552
0.250 0.1182 0.01990 0.01249 -0.0386 0.9304 0.7584
0.500 0.1618 0.01963 0.01225 -0.0417 0.9217 0.7616
0.750 0.2065 0.01926 0.01189 -0.0449 0.9108 0.7647
1.000 0.2462 0.01881 0.01149 -0.0464 0.8943 0.7670
1.250 0.2806 0.01836 0.01108 -0.0466 0.8721 0.7689
1.500 0.3124 0.01802 0.01078 -0.0465 0.8490 0.7709
1.750 0.3451 0.01772 0.01051 -0.0468 0.8259 0.7731
2.000 0.3759 0.01748 0.01028 -0.0468 0.7957 0.7754
2.250 0.4077 0.01726 0.01001 -0.0469 0.7541 0.7781
2.500 0.4394 0.01716 0.00977 -0.0470 0.6917 0.7813
2.750 0.4656 0.01736 0.00947 -0.0458 0.5675 0.7836
3.000 0.4834 0.01829 0.00955 -0.0436 0.4068 0.7857
3.250 0.5036 0.01919 0.00987 -0.0424 0.2961 0.7881
3.500 0.5267 0.01993 0.01021 -0.0419 0.2234 0.7908
3.750 0.5522 0.02054 0.01058 -0.0419 0.1811 0.7935
4.000 0.5790 0.02112 0.01100 -0.0421 0.1562 0.7960
4.250 0.6071 0.02167 0.01146 -0.0426 0.1384 0.7986
4.500 0.6315 0.02221 0.01194 -0.0421 0.1263 0.8005
4.750 0.6557 0.02272 0.01246 -0.0415 0.1163 0.8026
5.000 0.6802 0.02328 0.01303 -0.0410 0.1081 0.8051
5.250 0.7053 0.02389 0.01360 -0.0408 0.1013 0.8079
5.500 0.7316 0.02454 0.01430 -0.0407 0.0950 0.8109
5.750 0.7589 0.02519 0.01495 -0.0410 0.0892 0.8138
6.000 0.7850 0.02596 0.01572 -0.0410 0.0845 0.8162
6.250 0.8091 0.02661 0.01646 -0.0404 0.0798 0.8184
6.500 0.8328 0.02737 0.01719 -0.0399 0.0761 0.8211
6.750 0.8582 0.02823 0.01819 -0.0396 0.0722 0.8241
7.000 0.8841 0.02911 0.01915 -0.0395 0.0686 0.8271
7.250 0.9102 0.03007 0.02007 -0.0398 0.0658 0.8300
7.500 0.9356 0.03118 0.02139 -0.0396 0.0626 0.8324
7.750 0.9586 0.03219 0.02256 -0.0389 0.0597 0.8349
8.000 0.9816 0.03322 0.02364 -0.0384 0.0576 0.8379
8.250 1.0048 0.03456 0.02508 -0.0381 0.0556 0.8412
8.500 1.0276 0.03608 0.02694 -0.0377 0.0530 0.8447
8.750 1.0495 0.03738 0.02841 -0.0373 0.0510 0.8477
9.000 1.0691 0.03865 0.02979 -0.0364 0.0497 0.8505
9.250 1.0881 0.04032 0.03159 -0.0356 0.0485 0.8535
9.500 1.1019 0.04285 0.03466 -0.0341 0.0468 0.8567
9.750 1.1156 0.04509 0.03725 -0.0330 0.0452 0.8601
10.000 1.1289 0.04690 0.03930 -0.0318 0.0439 0.8635
10.250 1.1411 0.04844 0.04098 -0.0304 0.0430 0.8671
10.500 1.1529 0.05019 0.04283 -0.0291 0.0423 0.8711
10.750 1.1510 0.05367 0.04675 -0.0269 0.0417 0.8753
11.000 1.1369 0.05782 0.05143 -0.0238 0.0413 0.8792
11.250 1.1146 0.06174 0.05575 -0.0203 0.0410 0.8835
11.500 1.0890 0.06660 0.06098 -0.0185 0.0409 0.8880
11.750 1.0585 0.07270 0.06742 -0.0190 0.0408 0.8919
12.000 1.0211 0.08059 0.07563 -0.0221 0.0410 0.8952
12.250 0.9740 0.09281 0.08812 -0.0307 0.0414 0.8979
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