NASA SC(2)-0410 AIRFOIL (sc20410-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA SC(2)-0410 AIRFOIL (sc20410-il) Reynolds number: 200,000 Max Cl/Cd: 41.29 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sc20410-il-200000-n5.txt Download as CSV file: xf-sc20410-il-200000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.250 -0.8627 0.06882 0.06446 -0.0343 1.0000 0.0213
-12.000 -0.9052 0.05885 0.05419 -0.0405 1.0000 0.0211
-11.750 -0.9303 0.05286 0.04792 -0.0428 1.0000 0.0212
-11.500 -0.9477 0.04841 0.04321 -0.0433 1.0000 0.0213
-11.250 -0.9611 0.04483 0.03936 -0.0427 1.0000 0.0215
-11.000 -0.9658 0.04134 0.03554 -0.0427 1.0000 0.0219
-10.750 -0.9636 0.03813 0.03193 -0.0423 1.0000 0.0222
-10.500 -0.9558 0.03526 0.02868 -0.0418 1.0000 0.0226
-10.250 -0.9435 0.03279 0.02585 -0.0413 1.0000 0.0230
-10.000 -0.9278 0.03079 0.02358 -0.0408 1.0000 0.0234
-9.750 -0.9095 0.02937 0.02208 -0.0404 1.0000 0.0239
-9.500 -0.8899 0.02817 0.02080 -0.0400 1.0000 0.0244
-9.250 -0.8695 0.02701 0.01952 -0.0397 1.0000 0.0250
-9.000 -0.8487 0.02584 0.01822 -0.0392 1.0000 0.0258
-8.750 -0.8273 0.02469 0.01691 -0.0388 1.0000 0.0268
-8.500 -0.8053 0.02364 0.01568 -0.0383 1.0000 0.0281
-8.250 -0.7833 0.02267 0.01466 -0.0379 1.0000 0.0292
-8.000 -0.7604 0.02193 0.01391 -0.0376 1.0000 0.0305
-7.750 -0.7373 0.02112 0.01303 -0.0373 1.0000 0.0321
-7.500 -0.7139 0.02029 0.01208 -0.0369 1.0000 0.0339
-7.250 -0.6904 0.01945 0.01122 -0.0366 1.0000 0.0356
-7.000 -0.6662 0.01883 0.01060 -0.0365 1.0000 0.0377
-6.750 -0.6416 0.01827 0.00997 -0.0362 1.0000 0.0406
-6.500 -0.6169 0.01764 0.00934 -0.0362 1.0000 0.0436
-6.250 -0.5918 0.01716 0.00885 -0.0361 1.0000 0.0469
-6.000 -0.5664 0.01673 0.00836 -0.0359 1.0000 0.0504
-5.750 -0.5409 0.01614 0.00782 -0.0361 1.0000 0.0545
-5.500 -0.5151 0.01576 0.00740 -0.0360 1.0000 0.0592
-5.250 -0.4888 0.01523 0.00690 -0.0362 1.0000 0.0639
-5.000 -0.4624 0.01483 0.00651 -0.0364 1.0000 0.0694
-4.750 -0.4354 0.01441 0.00608 -0.0366 1.0000 0.0751
-4.500 -0.4083 0.01402 0.00571 -0.0369 1.0000 0.0830
-4.250 -0.3806 0.01363 0.00538 -0.0373 1.0000 0.0935
-4.000 -0.3526 0.01325 0.00508 -0.0379 1.0000 0.1091
-3.750 -0.3237 0.01280 0.00479 -0.0387 1.0000 0.1405
-3.500 -0.2927 0.01219 0.00451 -0.0402 1.0000 0.2087
-3.250 -0.2578 0.01131 0.00419 -0.0429 1.0000 0.3298
-3.000 -0.2205 0.01032 0.00418 -0.0458 1.0000 0.5294
-2.750 -0.1949 0.01044 0.00453 -0.0452 1.0000 0.6123
-2.500 -0.1650 0.01057 0.00468 -0.0456 0.9983 0.6399
-2.250 -0.1303 0.01069 0.00480 -0.0469 0.9950 0.6596
-2.000 -0.0969 0.01088 0.00500 -0.0478 0.9909 0.6799
-1.750 -0.0639 0.01114 0.00529 -0.0485 0.9864 0.6989
-1.500 -0.0300 0.01133 0.00551 -0.0495 0.9828 0.7109
-1.250 0.0033 0.01143 0.00559 -0.0505 0.9776 0.7210
-1.000 0.0361 0.01155 0.00577 -0.0512 0.9733 0.7272
-0.750 0.0708 0.01159 0.00583 -0.0525 0.9685 0.7330
-0.500 0.1088 0.01150 0.00573 -0.0546 0.9623 0.7376
-0.250 0.1482 0.01136 0.00560 -0.0569 0.9547 0.7398
0.000 0.1862 0.01118 0.00545 -0.0585 0.9410 0.7418
0.250 0.2221 0.01101 0.00530 -0.0596 0.9208 0.7440
0.500 0.2569 0.01087 0.00516 -0.0606 0.8997 0.7461
0.750 0.2895 0.01076 0.00499 -0.0609 0.8664 0.7482
1.000 0.3192 0.01072 0.00487 -0.0607 0.8233 0.7503
1.250 0.3476 0.01078 0.00477 -0.0604 0.7722 0.7526
1.750 0.3968 0.01157 0.00470 -0.0581 0.5644 0.7569
2.000 0.4172 0.01257 0.00492 -0.0568 0.3941 0.7585
2.250 0.4409 0.01337 0.00519 -0.0563 0.2765 0.7604
2.500 0.4661 0.01403 0.00546 -0.0562 0.1914 0.7625
2.750 0.4929 0.01450 0.00574 -0.0562 0.1446 0.7647
3.000 0.5204 0.01492 0.00601 -0.0563 0.1156 0.7669
3.250 0.5484 0.01530 0.00629 -0.0565 0.0964 0.7692
3.500 0.5768 0.01566 0.00661 -0.0568 0.0851 0.7715
3.750 0.6032 0.01605 0.00699 -0.0565 0.0770 0.7730
4.000 0.6296 0.01643 0.00738 -0.0562 0.0701 0.7748
4.250 0.6559 0.01689 0.00786 -0.0559 0.0649 0.7770
4.500 0.6827 0.01727 0.00828 -0.0558 0.0596 0.7794
4.750 0.7090 0.01780 0.00878 -0.0557 0.0549 0.7819
5.000 0.7365 0.01818 0.00922 -0.0557 0.0505 0.7844
5.250 0.7632 0.01872 0.00973 -0.0557 0.0466 0.7869
5.500 0.7888 0.01921 0.01032 -0.0552 0.0435 0.7887
5.750 0.8142 0.01973 0.01090 -0.0548 0.0407 0.7907
6.000 0.8390 0.02041 0.01158 -0.0544 0.0381 0.7930
6.250 0.8648 0.02100 0.01230 -0.0541 0.0355 0.7955
6.500 0.8907 0.02157 0.01291 -0.0539 0.0332 0.7983
6.750 0.9157 0.02238 0.01371 -0.0537 0.0316 0.8013
7.000 0.9399 0.02325 0.01477 -0.0530 0.0301 0.8036
7.250 0.9636 0.02417 0.01583 -0.0523 0.0288 0.8061
7.500 0.9874 0.02507 0.01684 -0.0517 0.0277 0.8091
7.750 1.0111 0.02598 0.01784 -0.0512 0.0269 0.8122
8.000 1.0342 0.02712 0.01902 -0.0507 0.0261 0.8155
8.250 1.0565 0.02847 0.02064 -0.0499 0.0253 0.8181
8.500 1.0776 0.02986 0.02232 -0.0489 0.0243 0.8207
8.750 1.0982 0.03120 0.02389 -0.0480 0.0235 0.8238
9.000 1.1184 0.03256 0.02547 -0.0472 0.0228 0.8272
9.250 1.1378 0.03402 0.02712 -0.0463 0.0224 0.8309
9.500 1.1552 0.03547 0.02875 -0.0452 0.0220 0.8340
9.750 1.1710 0.03708 0.03053 -0.0439 0.0216 0.8376
10.000 1.1838 0.03926 0.03296 -0.0424 0.0213 0.8417
10.250 1.1893 0.04260 0.03681 -0.0403 0.0211 0.8460
10.500 1.1861 0.04654 0.04129 -0.0375 0.0208 0.8495
10.750 1.1734 0.05117 0.04644 -0.0343 0.0206 0.8535
11.000 1.1501 0.05580 0.05149 -0.0306 0.0206 0.8584
11.250 1.1207 0.06107 0.05710 -0.0283 0.0206 0.8632
11.500 1.0873 0.06776 0.06412 -0.0292 0.0206 0.8676
11.750 1.0477 0.07803 0.07467 -0.0359 0.0208 0.8720
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