NREL's S801 Airfoil (s801-nr) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NREL's S801 Airfoil (s801-nr) Reynolds number: 500,000 Max Cl/Cd: 118.76 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s801-nr-500000.txt Download as CSV file: xf-s801-nr-500000.csv |
XFOIL Version 6.96
Calculated polar for: NREL's S801 Airfoil
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.1784 0.08777 0.08557 -0.0814 0.9769 0.0282
-10.500 -0.1936 0.07744 0.07526 -0.0889 0.9735 0.0297
-10.250 -0.2134 0.06811 0.06597 -0.0926 0.9643 0.0302
-10.000 -0.2038 0.06555 0.06341 -0.0934 0.9541 0.0306
-9.750 -0.1908 0.06223 0.06007 -0.0959 0.9475 0.0312
-9.500 -0.1792 0.05791 0.05573 -0.0999 0.9397 0.0321
-9.250 -0.1817 0.04842 0.04623 -0.1094 0.9345 0.0329
-9.000 -0.3339 0.04292 0.03992 -0.1280 0.9271 0.0306
-8.750 -0.3289 0.03149 0.02764 -0.1345 0.9112 0.0232
-8.500 -0.3101 0.02720 0.02282 -0.1369 0.8948 0.0230
-8.250 -0.2928 0.02395 0.01908 -0.1372 0.8791 0.0226
-8.000 -0.2735 0.02169 0.01643 -0.1369 0.8657 0.0227
-7.750 -0.2519 0.02001 0.01443 -0.1366 0.8545 0.0228
-7.500 -0.2291 0.01878 0.01293 -0.1361 0.8444 0.0231
-7.250 -0.2057 0.01783 0.01176 -0.1356 0.8355 0.0236
-7.000 -0.1818 0.01676 0.01046 -0.1353 0.8278 0.0243
-6.750 -0.1590 0.01552 0.00914 -0.1348 0.8204 0.0249
-6.500 -0.1345 0.01478 0.00833 -0.1344 0.8137 0.0256
-6.250 -0.1097 0.01418 0.00765 -0.1342 0.8077 0.0262
-6.000 -0.0850 0.01364 0.00705 -0.1338 0.8015 0.0269
-5.750 -0.0591 0.01317 0.00649 -0.1337 0.7963 0.0277
-5.500 -0.0336 0.01277 0.00604 -0.1335 0.7910 0.0289
-5.250 -0.0074 0.01245 0.00565 -0.1334 0.7859 0.0297
-5.000 0.0182 0.01178 0.00492 -0.1334 0.7816 0.0312
-4.750 0.0451 0.01144 0.00454 -0.1335 0.7776 0.0328
-4.500 0.0720 0.01115 0.00423 -0.1336 0.7734 0.0349
-4.250 0.0995 0.01087 0.00389 -0.1337 0.7696 0.0377
-4.000 0.1277 0.01061 0.00361 -0.1340 0.7662 0.0450
-3.750 0.1552 0.01001 0.00329 -0.1345 0.7628 0.1087
-3.500 0.1825 0.00955 0.00312 -0.1350 0.7592 0.1830
-3.250 0.2105 0.00914 0.00298 -0.1356 0.7557 0.2616
-3.000 0.2393 0.00870 0.00284 -0.1364 0.7527 0.3604
-2.750 0.2689 0.00809 0.00272 -0.1375 0.7500 0.5124
-2.500 0.2968 0.00788 0.00293 -0.1377 0.7474 0.6422
-2.250 0.3247 0.00799 0.00308 -0.1376 0.7447 0.6796
-2.000 0.3530 0.00815 0.00321 -0.1376 0.7418 0.7028
-1.750 0.3811 0.00834 0.00337 -0.1374 0.7390 0.7195
-1.500 0.4088 0.00853 0.00354 -0.1372 0.7365 0.7312
-1.250 0.4378 0.00868 0.00363 -0.1374 0.7342 0.7397
-1.000 0.4654 0.00885 0.00380 -0.1372 0.7320 0.7468
-0.750 0.4933 0.00896 0.00390 -0.1372 0.7295 0.7545
-0.500 0.5200 0.00906 0.00402 -0.1368 0.7268 0.7595
-0.250 0.5481 0.00917 0.00412 -0.1369 0.7243 0.7658
0.000 0.5762 0.00927 0.00419 -0.1369 0.7219 0.7712
0.250 0.6038 0.00938 0.00430 -0.1367 0.7196 0.7757
0.500 0.6326 0.00954 0.00442 -0.1370 0.7171 0.7811
0.750 0.6596 0.00958 0.00449 -0.1369 0.7142 0.7858
1.000 0.6857 0.00964 0.00459 -0.1364 0.7110 0.7896
1.250 0.7132 0.00971 0.00466 -0.1363 0.7079 0.7938
1.500 0.7423 0.00977 0.00469 -0.1367 0.7047 0.7976
1.750 0.7712 0.00985 0.00474 -0.1370 0.7010 0.8005
2.000 0.7966 0.00982 0.00477 -0.1365 0.6964 0.8028
2.250 0.8236 0.00982 0.00478 -0.1363 0.6916 0.8052
2.500 0.8523 0.00987 0.00479 -0.1365 0.6869 0.8076
2.750 0.8782 0.00985 0.00482 -0.1362 0.6813 0.8100
3.000 0.9058 0.00983 0.00480 -0.1362 0.6756 0.8122
3.250 0.9343 0.00987 0.00481 -0.1365 0.6699 0.8142
3.500 0.9598 0.00982 0.00482 -0.1361 0.6634 0.8158
3.750 0.9866 0.00981 0.00481 -0.1359 0.6577 0.8174
4.000 1.0123 0.00982 0.00487 -0.1355 0.6513 0.8191
4.250 1.0379 0.00981 0.00489 -0.1351 0.6441 0.8208
4.500 1.0637 0.00982 0.00493 -0.1347 0.6363 0.8224
4.750 1.0889 0.00982 0.00496 -0.1342 0.6274 0.8244
5.000 1.1139 0.00984 0.00503 -0.1337 0.6178 0.8265
5.250 1.1385 0.00988 0.00508 -0.1332 0.6060 0.8283
5.500 1.1624 0.00993 0.00514 -0.1325 0.5911 0.8299
5.750 1.1840 0.00997 0.00520 -0.1313 0.5705 0.8315
6.000 1.2015 0.01015 0.00530 -0.1292 0.5363 0.8334
6.250 1.2114 0.01066 0.00556 -0.1257 0.4824 0.8358
6.500 1.2172 0.01144 0.00604 -0.1217 0.4263 0.8382
6.750 1.2211 0.01224 0.00658 -0.1174 0.3736 0.8408
7.000 1.2251 0.01307 0.00716 -0.1132 0.3265 0.8434
7.250 1.2310 0.01390 0.00779 -0.1096 0.2851 0.8457
7.500 1.2370 0.01473 0.00843 -0.1060 0.2478 0.8483
7.750 1.2437 0.01556 0.00911 -0.1026 0.2158 0.8512
8.000 1.2526 0.01635 0.00979 -0.0998 0.1890 0.8543
8.250 1.2621 0.01717 0.01051 -0.0972 0.1659 0.8572
8.500 1.2714 0.01804 0.01129 -0.0947 0.1454 0.8601
8.750 1.2803 0.01890 0.01209 -0.0921 0.1287 0.8630
9.000 1.2901 0.01977 0.01292 -0.0898 0.1146 0.8663
9.250 1.3005 0.02068 0.01380 -0.0877 0.1026 0.8700
9.500 1.3121 0.02157 0.01469 -0.0859 0.0930 0.8738
9.750 1.3224 0.02251 0.01566 -0.0839 0.0846 0.8778
10.000 1.3308 0.02362 0.01675 -0.0818 0.0769 0.8828
10.250 1.3432 0.02454 0.01773 -0.0803 0.0715 0.8881
10.500 1.3514 0.02571 0.01891 -0.0783 0.0661 0.8940
10.750 1.3617 0.02678 0.02006 -0.0766 0.0621 0.9013
11.000 1.3720 0.02780 0.02116 -0.0750 0.0584 0.9115
11.250 1.3769 0.02919 0.02261 -0.0728 0.0545 0.9350
11.500 1.3877 0.03037 0.02389 -0.0717 0.0520 1.0000
11.750 1.4007 0.03160 0.02518 -0.0709 0.0495 1.0000
12.000 1.4111 0.03304 0.02664 -0.0699 0.0470 1.0000
12.250 1.4132 0.03522 0.02884 -0.0683 0.0441 1.0000
12.500 1.4273 0.03638 0.03008 -0.0677 0.0427 1.0000
12.750 1.4399 0.03766 0.03143 -0.0670 0.0406 1.0000
13.000 1.4503 0.03916 0.03296 -0.0663 0.0386 1.0000
13.250 1.4539 0.04132 0.03514 -0.0651 0.0365 1.0000
13.500 1.4634 0.04296 0.03686 -0.0644 0.0351 1.0000
13.750 1.4744 0.04447 0.03845 -0.0638 0.0336 1.0000
14.000 1.4840 0.04615 0.04019 -0.0632 0.0323 1.0000
14.250 1.4916 0.04806 0.04214 -0.0626 0.0309 1.0000
14.500 1.4933 0.05063 0.04477 -0.0618 0.0295 1.0000
14.750 1.4977 0.05297 0.04720 -0.0612 0.0285 1.0000
15.000 1.5067 0.05485 0.04919 -0.0608 0.0275 1.0000
15.250 1.5142 0.05693 0.05136 -0.0605 0.0264 1.0000
15.500 1.5212 0.05911 0.05361 -0.0603 0.0253 1.0000
15.750 1.5244 0.06178 0.05632 -0.0601 0.0242 1.0000
16.000 1.5196 0.06548 0.06009 -0.0599 0.0231 1.0000
16.250 1.5276 0.06769 0.06243 -0.0599 0.0223 1.0000
16.500 1.5332 0.07023 0.06508 -0.0601 0.0212 1.0000
16.750 1.5379 0.07295 0.06789 -0.0604 0.0201 1.0000
17.000 1.5382 0.07630 0.07130 -0.0608 0.0192 1.0000
17.250 1.5303 0.08089 0.07596 -0.0615 0.0182 1.0000
17.500 1.5341 0.08395 0.07917 -0.0621 0.0174 1.0000
17.750 1.5350 0.08748 0.08282 -0.0629 0.0165 1.0000
18.000 1.5342 0.09136 0.08679 -0.0640 0.0157 1.0000
18.250 1.5285 0.09607 0.09159 -0.0655 0.0150 1.0000
18.500 1.5157 0.10203 0.09764 -0.0675 0.0144 1.0000
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