NASA SC(2)-0410 AIRFOIL (sc20410-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NASA SC(2)-0410 AIRFOIL (sc20410-il) Reynolds number: 200,000 Max Cl/Cd: 35.26 at α=2.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sc20410-il-200000.txt Download as CSV file: xf-sc20410-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: NASA SC(2)-0410 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.5223 0.09066 0.08693 -0.0229 1.0000 0.0776
-10.000 -0.5291 0.08539 0.08167 -0.0247 1.0000 0.0792
-9.750 -0.5435 0.07861 0.07493 -0.0279 1.0000 0.0806
-9.500 -0.5785 0.06802 0.06436 -0.0350 1.0000 0.0812
-9.250 -0.8131 0.05140 0.04630 -0.0424 1.0000 0.0516
-9.000 -0.7952 0.04988 0.04488 -0.0420 1.0000 0.0530
-8.750 -0.8120 0.03657 0.03007 -0.0418 1.0000 0.0428
-8.500 -0.7948 0.03340 0.02655 -0.0414 1.0000 0.0429
-8.250 -0.7750 0.03099 0.02391 -0.0411 1.0000 0.0435
-8.000 -0.7535 0.02908 0.02184 -0.0408 1.0000 0.0444
-7.750 -0.7310 0.02745 0.02003 -0.0404 1.0000 0.0458
-7.500 -0.7077 0.02603 0.01838 -0.0401 1.0000 0.0479
-7.250 -0.6833 0.02479 0.01684 -0.0396 1.0000 0.0499
-7.000 -0.6610 0.02256 0.01451 -0.0390 1.0000 0.0520
-6.750 -0.6373 0.02151 0.01347 -0.0385 1.0000 0.0548
-6.500 -0.6130 0.02058 0.01244 -0.0380 1.0000 0.0583
-6.250 -0.5893 0.01940 0.01118 -0.0374 1.0000 0.0626
-6.000 -0.5650 0.01868 0.01052 -0.0371 1.0000 0.0676
-5.750 -0.5399 0.01817 0.00990 -0.0367 1.0000 0.0724
-5.500 -0.5161 0.01704 0.00889 -0.0364 1.0000 0.0786
-5.250 -0.4907 0.01658 0.00839 -0.0361 1.0000 0.0850
-5.000 -0.4652 0.01565 0.00756 -0.0362 1.0000 0.0921
-4.750 -0.4390 0.01517 0.00704 -0.0361 1.0000 0.1000
-4.500 -0.4111 0.01435 0.00635 -0.0367 1.0000 0.1109
-4.250 -0.3823 0.01369 0.00578 -0.0375 1.0000 0.1277
-4.000 -0.3499 0.01270 0.00512 -0.0394 1.0000 0.1774
-3.750 -0.3051 0.01035 0.00489 -0.0451 1.0000 0.5769
-3.500 -0.2810 0.01070 0.00531 -0.0438 1.0000 0.6450
-3.250 -0.2572 0.01108 0.00566 -0.0425 1.0000 0.6743
-3.000 -0.2359 0.01151 0.00608 -0.0406 1.0000 0.6928
-2.750 -0.2147 0.01191 0.00649 -0.0387 1.0000 0.7083
-2.500 -0.1922 0.01228 0.00682 -0.0373 1.0000 0.7223
-2.250 -0.1751 0.01270 0.00729 -0.0344 1.0000 0.7308
-2.000 -0.1535 0.01303 0.00762 -0.0329 1.0000 0.7419
-1.750 -0.1340 0.01350 0.00809 -0.0308 1.0000 0.7557
-1.500 -0.1232 0.01405 0.00873 -0.0263 1.0000 0.7664
-1.250 -0.1081 0.01447 0.00918 -0.0232 1.0000 0.7776
-1.000 -0.0864 0.01475 0.00945 -0.0220 1.0000 0.7884
-0.750 -0.0711 0.01502 0.00977 -0.0192 1.0000 0.7956
-0.500 -0.0463 0.01518 0.00993 -0.0190 1.0000 0.8035
-0.250 -0.0175 0.01533 0.01011 -0.0191 0.9964 0.8091
0.000 0.0302 0.01536 0.01014 -0.0234 0.9893 0.8155
0.250 0.0764 0.01526 0.01006 -0.0272 0.9821 0.8184
0.500 0.1257 0.01499 0.00983 -0.0314 0.9720 0.8198
0.750 0.1730 0.01466 0.00954 -0.0350 0.9605 0.8216
1.000 0.2235 0.01421 0.00915 -0.0389 0.9483 0.8236
1.250 0.2718 0.01368 0.00869 -0.0422 0.9337 0.8260
1.500 0.3132 0.01325 0.00831 -0.0443 0.9166 0.8287
1.750 0.3509 0.01292 0.00801 -0.0459 0.8942 0.8310
2.000 0.3808 0.01262 0.00773 -0.0454 0.8643 0.8329
2.250 0.4072 0.01242 0.00749 -0.0441 0.8205 0.8348
2.500 0.4330 0.01238 0.00727 -0.0428 0.7489 0.8366
2.750 0.4542 0.01288 0.00710 -0.0407 0.5843 0.8386
3.000 0.4693 0.01450 0.00739 -0.0387 0.3195 0.8411
3.250 0.4917 0.01590 0.00790 -0.0386 0.1652 0.8439
3.500 0.5205 0.01667 0.00842 -0.0394 0.1282 0.8462
3.750 0.5456 0.01719 0.00888 -0.0389 0.1124 0.8480
4.000 0.5704 0.01772 0.00938 -0.0384 0.1016 0.8503
4.250 0.5951 0.01848 0.01003 -0.0379 0.0931 0.8527
4.500 0.6231 0.01886 0.01050 -0.0380 0.0858 0.8552
4.750 0.6502 0.01979 0.01134 -0.0382 0.0789 0.8576
5.000 0.6799 0.02026 0.01188 -0.0388 0.0724 0.8600
5.250 0.7070 0.02142 0.01296 -0.0391 0.0665 0.8622
5.500 0.7330 0.02200 0.01370 -0.0385 0.0622 0.8644
5.750 0.7586 0.02278 0.01448 -0.0382 0.0580 0.8672
6.000 0.7846 0.02422 0.01603 -0.0380 0.0542 0.8702
6.250 0.8124 0.02516 0.01714 -0.0380 0.0508 0.8733
6.500 0.8408 0.02636 0.01842 -0.0384 0.0485 0.8761
6.750 0.8647 0.02828 0.02041 -0.0380 0.0467 0.8786
7.000 0.8870 0.03062 0.02311 -0.0371 0.0457 0.8814
7.250 0.9090 0.03275 0.02569 -0.0361 0.0450 0.8845
7.500 0.9300 0.03528 0.02867 -0.0351 0.0440 0.8879
7.750 0.9490 0.03830 0.03216 -0.0343 0.0430 0.8912
8.000 0.9595 0.04227 0.03663 -0.0321 0.0434 0.8943
8.250 0.9669 0.04687 0.04169 -0.0301 0.0443 0.8980
8.500 0.9735 0.05167 0.04679 -0.0288 0.0454 0.9021
9.250 0.9010 0.08116 0.07804 -0.0249 0.0691 0.9141
9.500 0.9089 0.08454 0.08141 -0.0244 0.0683 0.9184
9.750 0.9141 0.09294 0.08968 -0.0252 0.0671 0.9217
10.000 0.8888 0.09700 0.09392 -0.0249 0.0670 0.9279
10.250 0.8620 0.10272 0.09978 -0.0284 0.0669 0.9341
10.500 0.8306 0.11267 0.10984 -0.0391 0.0668 0.9403
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Polar data table (+)
Polar graphs
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