NREL's S822 Airfoil (s822-nr) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NREL's S822 Airfoil (s822-nr) Reynolds number: 100,000 Max Cl/Cd: 39.8 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s822-nr-100000-n5.txt Download as CSV file: xf-s822-nr-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NREL's S822 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
------ -------- --------- --------- -------- -------- --------
-16.000 -0.6028 0.10906 0.10348 -0.0675 1.0000 0.0273
-15.750 -0.6306 0.09963 0.09392 -0.0724 1.0000 0.0272
-15.500 -0.6566 0.09118 0.08531 -0.0769 1.0000 0.0271
-15.250 -0.6767 0.08436 0.07833 -0.0803 1.0000 0.0272
-15.000 -0.6958 0.07814 0.07192 -0.0833 1.0000 0.0273
-14.750 -0.7098 0.07321 0.06688 -0.0852 1.0000 0.0277
-14.500 -0.7195 0.06925 0.06287 -0.0863 1.0000 0.0282
-14.250 -0.7287 0.06569 0.05926 -0.0871 1.0000 0.0289
-14.000 -0.7389 0.06226 0.05576 -0.0877 1.0000 0.0297
-13.750 -0.7489 0.05905 0.05247 -0.0878 1.0000 0.0304
-13.500 -0.7585 0.05618 0.04948 -0.0873 1.0000 0.0310
-13.250 -0.7688 0.05358 0.04679 -0.0863 1.0000 0.0318
-13.000 -0.7805 0.05130 0.04440 -0.0845 1.0000 0.0328
-12.750 -0.7938 0.04942 0.04240 -0.0819 1.0000 0.0336
-12.500 -0.8081 0.04788 0.04076 -0.0785 1.0000 0.0342
-12.250 -0.8240 0.04649 0.03923 -0.0748 1.0000 0.0351
-12.000 -0.8201 0.04420 0.03691 -0.0753 0.9962 0.0370
-11.750 -0.8100 0.04211 0.03472 -0.0767 0.9909 0.0395
-11.500 -0.7980 0.04018 0.03261 -0.0776 0.9857 0.0426
-11.250 -0.7841 0.03833 0.03059 -0.0786 0.9813 0.0460
-11.000 -0.7751 0.03673 0.02891 -0.0787 0.9748 0.0491
-10.750 -0.7592 0.03526 0.02727 -0.0794 0.9704 0.0537
-10.500 -0.7499 0.03390 0.02583 -0.0787 0.9644 0.0579
-10.250 -0.7370 0.03269 0.02454 -0.0785 0.9589 0.0632
-10.000 -0.7186 0.03140 0.02315 -0.0791 0.9553 0.0699
-9.750 -0.7147 0.03056 0.02225 -0.0766 0.9477 0.0753
-9.500 -0.6983 0.02953 0.02115 -0.0762 0.9434 0.0833
-9.250 -0.6816 0.02866 0.02017 -0.0757 0.9390 0.0927
-9.000 -0.6733 0.02788 0.01939 -0.0735 0.9325 0.1012
-8.750 -0.6526 0.02700 0.01847 -0.0735 0.9289 0.1136
-8.500 -0.6285 0.02616 0.01760 -0.0741 0.9262 0.1290
-8.250 -0.6247 0.02574 0.01716 -0.0705 0.9186 0.1395
-8.000 -0.6038 0.02507 0.01649 -0.0702 0.9150 0.1566
-7.750 -0.5786 0.02441 0.01580 -0.0707 0.9124 0.1763
-7.500 -0.5718 0.02408 0.01545 -0.0675 0.9057 0.1913
-7.250 -0.5528 0.02358 0.01496 -0.0666 0.9015 0.2105
-7.000 -0.5284 0.02304 0.01444 -0.0667 0.8986 0.2337
-6.750 -0.5113 0.02268 0.01409 -0.0653 0.8943 0.2543
-6.500 -0.4991 0.02239 0.01384 -0.0629 0.8885 0.2744
-6.250 -0.4756 0.02200 0.01344 -0.0626 0.8853 0.2992
-5.750 -0.4390 0.02145 0.01296 -0.0600 0.8766 0.3472
-5.500 -0.4189 0.02121 0.01274 -0.0589 0.8724 0.3729
-5.250 -0.3931 0.02091 0.01249 -0.0589 0.8697 0.4007
-5.000 -0.3644 0.02062 0.01223 -0.0593 0.8676 0.4303
-4.750 -0.3569 0.02064 0.01230 -0.0557 0.8605 0.4520
-4.500 -0.3334 0.02049 0.01220 -0.0551 0.8568 0.4795
-4.250 -0.3057 0.02034 0.01209 -0.0552 0.8544 0.5079
-4.000 -0.2757 0.02023 0.01201 -0.0556 0.8526 0.5357
-3.750 -0.2689 0.02044 0.01227 -0.0518 0.8450 0.5561
-3.500 -0.2434 0.02044 0.01227 -0.0513 0.8416 0.5808
-3.250 -0.2140 0.02045 0.01226 -0.0515 0.8393 0.6033
-3.000 -0.1832 0.02045 0.01223 -0.0520 0.8376 0.6252
-2.750 -0.1786 0.02078 0.01256 -0.0479 0.8295 0.6417
-2.500 -0.1516 0.02085 0.01262 -0.0477 0.8264 0.6592
-2.250 -0.1213 0.02090 0.01263 -0.0480 0.8242 0.6756
-2.000 -0.1015 0.02111 0.01283 -0.0465 0.8200 0.6904
-1.750 -0.0887 0.02138 0.01309 -0.0438 0.8138 0.7043
-1.500 -0.0608 0.02147 0.01315 -0.0437 0.8110 0.7183
-1.250 -0.0297 0.02156 0.01322 -0.0441 0.8090 0.7305
-1.000 -0.0238 0.02199 0.01367 -0.0402 0.8018 0.7416
-0.750 -0.0011 0.02216 0.01383 -0.0392 0.7978 0.7533
-0.500 0.0281 0.02222 0.01386 -0.0394 0.7954 0.7650
-0.250 0.0596 0.02228 0.01391 -0.0399 0.7936 0.7755
0.000 0.0581 0.02284 0.01449 -0.0349 0.7845 0.7859
0.250 0.0850 0.02291 0.01455 -0.0346 0.7816 0.7964
0.500 0.1155 0.02292 0.01455 -0.0350 0.7796 0.8066
1.000 0.1429 0.02353 0.01520 -0.0302 0.7675 0.8265
1.250 0.1731 0.02349 0.01516 -0.0304 0.7653 0.8357
1.500 0.2030 0.02345 0.01514 -0.0306 0.7628 0.8438
1.750 0.2038 0.02400 0.01572 -0.0263 0.7530 0.8555
2.000 0.2348 0.02388 0.01563 -0.0266 0.7506 0.8639
2.250 0.2669 0.02372 0.01549 -0.0271 0.7484 0.8720
2.500 0.2692 0.02429 0.01611 -0.0232 0.7381 0.8842
2.750 0.3030 0.02405 0.01591 -0.0239 0.7358 0.8917
3.250 0.3423 0.02426 0.01623 -0.0212 0.7228 0.9126
3.500 0.3824 0.02384 0.01587 -0.0229 0.7206 0.9189
4.000 0.4354 0.02381 0.01599 -0.0228 0.7073 0.9375
4.500 0.5005 0.02352 0.01587 -0.0247 0.6937 0.9534
5.000 0.5765 0.02291 0.01547 -0.0283 0.6792 0.9665
5.250 0.6117 0.02275 0.01543 -0.0299 0.6691 0.9735
5.500 0.6606 0.02188 0.01468 -0.0329 0.6624 0.9774
5.750 0.6948 0.02169 0.01461 -0.0343 0.6490 0.9853
6.000 0.7309 0.02138 0.01441 -0.0359 0.6344 0.9934
6.250 0.7541 0.02109 0.01420 -0.0351 0.6186 1.0000
6.500 0.7581 0.02090 0.01401 -0.0309 0.6024 1.0000
6.750 0.7582 0.02114 0.01427 -0.0267 0.5821 1.0000
7.000 0.7765 0.02099 0.01411 -0.0249 0.5573 1.0000
7.250 0.7934 0.02100 0.01409 -0.0231 0.5246 1.0000
7.500 0.8182 0.02083 0.01376 -0.0221 0.4812 1.0000
7.750 0.8373 0.02104 0.01370 -0.0206 0.4324 1.0000
8.000 0.8484 0.02171 0.01410 -0.0183 0.3875 1.0000
8.250 0.8569 0.02258 0.01475 -0.0159 0.3481 1.0000
8.500 0.8644 0.02358 0.01554 -0.0136 0.3107 1.0000
8.750 0.8717 0.02464 0.01643 -0.0114 0.2769 1.0000
9.000 0.8798 0.02574 0.01739 -0.0094 0.2461 1.0000
9.500 0.8976 0.02802 0.01942 -0.0059 0.1915 1.0000
9.750 0.9072 0.02919 0.02049 -0.0044 0.1692 1.0000
10.000 0.9169 0.03040 0.02162 -0.0030 0.1494 1.0000
10.250 0.9265 0.03165 0.02280 -0.0016 0.1332 1.0000
10.500 0.9362 0.03293 0.02404 -0.0002 0.1190 1.0000
10.750 0.9463 0.03422 0.02535 0.0010 0.1067 1.0000
11.000 0.9562 0.03556 0.02670 0.0022 0.0962 1.0000
11.250 0.9649 0.03701 0.02813 0.0034 0.0875 1.0000
11.500 0.9736 0.03849 0.02964 0.0045 0.0796 1.0000
11.750 0.9827 0.04000 0.03120 0.0056 0.0730 1.0000
12.000 0.9902 0.04163 0.03286 0.0067 0.0668 1.0000
12.250 0.9984 0.04330 0.03458 0.0077 0.0621 1.0000
12.500 1.0070 0.04495 0.03633 0.0085 0.0574 1.0000
12.750 1.0121 0.04690 0.03831 0.0094 0.0538 1.0000
13.000 1.0211 0.04866 0.04021 0.0102 0.0500 1.0000
13.250 1.0289 0.05054 0.04220 0.0109 0.0470 1.0000
13.500 1.0348 0.05258 0.04432 0.0115 0.0445 1.0000
13.750 1.0399 0.05481 0.04654 0.0122 0.0423 1.0000
14.000 1.0476 0.05691 0.04888 0.0127 0.0399 1.0000
14.250 1.0528 0.05923 0.05136 0.0131 0.0376 1.0000
14.500 1.0571 0.06167 0.05391 0.0133 0.0360 1.0000
14.750 1.0605 0.06423 0.05656 0.0135 0.0347 1.0000
15.000 1.0637 0.06696 0.05931 0.0137 0.0333 1.0000
15.250 1.0638 0.07017 0.06279 0.0136 0.0321 1.0000
15.500 1.0620 0.07363 0.06654 0.0132 0.0308 1.0000
15.750 1.0587 0.07733 0.07045 0.0126 0.0296 1.0000
16.000 1.0546 0.08124 0.07455 0.0118 0.0287 1.0000
16.250 1.0493 0.08542 0.07890 0.0107 0.0280 1.0000
16.500 1.0432 0.08984 0.08348 0.0092 0.0274 1.0000
16.750 1.0365 0.09442 0.08819 0.0075 0.0268 1.0000
17.000 1.0295 0.09919 0.09308 0.0055 0.0262 1.0000
17.500 1.0051 0.11125 0.10547 -0.0003 0.0254 1.0000
17.750 0.9857 0.11918 0.11364 -0.0049 0.0253 1.0000
18.000 0.9644 0.12797 0.12266 -0.0102 0.0253 1.0000
18.250 0.9391 0.13829 0.13318 -0.0167 0.0254 1.0000
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