NREL's S802 Airfoil (s802-nr) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NREL's S802 Airfoil (s802-nr) Reynolds number: 200,000 Max Cl/Cd: 91.32 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s802-nr-200000.txt Download as CSV file: xf-s802-nr-200000.csv |
XFOIL Version 6.96
Calculated polar for: NREL's S802 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
------ -------- --------- --------- -------- -------- --------
-11.250 -0.2814 0.12221 0.11901 -0.0403 1.0000 0.0420
-11.000 -0.2859 0.12117 0.11803 -0.0374 1.0000 0.0427
-10.750 -0.3522 0.11921 0.11562 -0.0462 1.0000 0.0416
-10.500 -0.3446 0.11671 0.11314 -0.0446 1.0000 0.0424
-10.250 -0.3416 0.11429 0.11076 -0.0436 1.0000 0.0436
-10.000 -0.3423 0.11192 0.10843 -0.0429 1.0000 0.0447
-9.750 -0.3460 0.10962 0.10619 -0.0421 1.0000 0.0457
-9.500 -0.3542 0.10760 0.10425 -0.0406 1.0000 0.0468
-9.250 -0.3686 0.10627 0.10300 -0.0382 1.0000 0.0478
-9.000 -0.3717 0.10165 0.09844 -0.0473 0.9959 0.0501
-8.750 -0.3634 0.09531 0.09211 -0.0594 0.9889 0.0505
-8.500 -0.3429 0.09143 0.08822 -0.0548 0.9883 0.0527
-8.250 -0.3208 0.08827 0.08504 -0.0577 0.9852 0.0554
-8.000 -0.3078 0.08369 0.08046 -0.0636 0.9781 0.0583
-7.750 -0.1941 0.06062 0.05751 -0.0820 0.9537 0.0663
-7.500 -0.1834 0.05579 0.05267 -0.0865 0.9494 0.0689
-7.250 -0.2777 0.06150 0.05811 -0.0982 0.9488 0.0648
-7.000 -0.2603 0.05878 0.05537 -0.0995 0.9411 0.0670
-6.750 -0.2359 0.05264 0.04889 -0.1093 0.9354 0.0739
-6.500 -0.2232 0.04690 0.04286 -0.1138 0.9265 0.0778
-6.250 -0.1940 0.04409 0.04004 -0.1162 0.9235 0.0810
-6.000 -0.1611 0.03949 0.03497 -0.1224 0.9207 0.0920
-5.750 -0.1359 0.02900 0.02324 -0.1245 0.9129 0.0536
-5.500 -0.1003 0.02479 0.01837 -0.1264 0.9095 0.0460
-5.250 -0.0624 0.02191 0.01496 -0.1286 0.9071 0.0443
-5.000 -0.0232 0.02012 0.01289 -0.1310 0.9051 0.0450
-4.750 0.0016 0.01933 0.01196 -0.1305 0.8976 0.0472
-4.500 0.0361 0.01811 0.01057 -0.1317 0.8939 0.0484
-4.250 0.0726 0.01706 0.00939 -0.1333 0.8912 0.0499
-4.000 0.0986 0.01612 0.00843 -0.1331 0.8853 0.0519
-3.750 0.1280 0.01538 0.00774 -0.1337 0.8802 0.0565
-3.500 0.1624 0.01468 0.00700 -0.1351 0.8768 0.0649
-3.250 0.1919 0.01392 0.00635 -0.1358 0.8718 0.0920
-3.000 0.2192 0.01272 0.00599 -0.1369 0.8663 0.2787
-2.750 0.2499 0.01181 0.00587 -0.1383 0.8627 0.4917
-2.500 0.2760 0.01169 0.00633 -0.1372 0.8596 0.6780
-2.250 0.2942 0.01211 0.00679 -0.1347 0.8531 0.7313
-2.000 0.3181 0.01242 0.00706 -0.1331 0.8487 0.7639
-1.750 0.3444 0.01265 0.00721 -0.1320 0.8455 0.7875
-1.500 0.3616 0.01297 0.00753 -0.1293 0.8406 0.8060
-1.250 0.3811 0.01319 0.00772 -0.1271 0.8357 0.8223
-1.000 0.4046 0.01328 0.00775 -0.1257 0.8321 0.8369
-0.750 0.4296 0.01335 0.00776 -0.1246 0.8294 0.8509
-0.500 0.4437 0.01358 0.00799 -0.1217 0.8236 0.8638
-0.250 0.4647 0.01365 0.00803 -0.1201 0.8195 0.8765
0.000 0.4889 0.01365 0.00799 -0.1190 0.8163 0.8888
0.250 0.5083 0.01367 0.00799 -0.1170 0.8127 0.9003
0.500 0.5216 0.01378 0.00813 -0.1141 0.8071 0.9119
0.750 0.5433 0.01374 0.00807 -0.1127 0.8031 0.9229
1.000 0.5700 0.01366 0.00795 -0.1122 0.8001 0.9332
1.250 0.5873 0.01377 0.00809 -0.1102 0.7949 0.9444
1.500 0.6111 0.01379 0.00812 -0.1095 0.7899 0.9539
1.750 0.6447 0.01373 0.00803 -0.1107 0.7863 0.9613
2.000 0.6812 0.01371 0.00798 -0.1124 0.7830 0.9675
2.250 0.7098 0.01388 0.00822 -0.1131 0.7763 0.9756
2.500 0.7493 0.01377 0.00810 -0.1155 0.7714 0.9811
2.750 0.7870 0.01375 0.00807 -0.1176 0.7657 0.9882
3.000 0.8184 0.01372 0.00808 -0.1185 0.7580 1.0000
3.250 0.8510 0.01361 0.00795 -0.1194 0.7516 1.0000
3.500 0.8764 0.01364 0.00800 -0.1191 0.7426 1.0000
3.750 0.9078 0.01355 0.00793 -0.1198 0.7347 1.0000
4.000 0.9386 0.01344 0.00782 -0.1203 0.7254 1.0000
4.250 0.9667 0.01342 0.00785 -0.1204 0.7154 1.0000
4.500 1.0002 0.01327 0.00768 -0.1214 0.7064 1.0000
4.750 1.0280 0.01322 0.00770 -0.1214 0.6950 1.0000
5.000 1.0555 0.01317 0.00770 -0.1213 0.6827 1.0000
5.250 1.0834 0.01310 0.00766 -0.1212 0.6693 1.0000
5.500 1.1103 0.01303 0.00765 -0.1209 0.6542 1.0000
5.750 1.1358 0.01297 0.00764 -0.1204 0.6364 1.0000
6.000 1.1602 0.01294 0.00763 -0.1196 0.6144 1.0000
6.250 1.1814 0.01298 0.00769 -0.1183 0.5846 1.0000
6.500 1.1999 0.01314 0.00776 -0.1163 0.5365 1.0000
6.750 1.2102 0.01377 0.00794 -0.1130 0.4630 1.0000
7.000 1.2134 0.01489 0.00859 -0.1087 0.3899 1.0000
7.250 1.2146 0.01608 0.00940 -0.1043 0.3273 1.0000
7.500 1.2156 0.01732 0.01031 -0.1001 0.2746 1.0000
7.750 1.2182 0.01859 0.01131 -0.0963 0.2293 1.0000
8.000 1.2230 0.01985 0.01235 -0.0931 0.1923 1.0000
8.250 1.2289 0.02111 0.01343 -0.0902 0.1647 1.0000
8.500 1.2354 0.02240 0.01458 -0.0874 0.1442 1.0000
8.750 1.2425 0.02373 0.01581 -0.0849 0.1286 1.0000
9.000 1.2517 0.02499 0.01702 -0.0828 0.1159 1.0000
9.250 1.2624 0.02620 0.01826 -0.0808 0.1056 1.0000
9.500 1.2712 0.02763 0.01967 -0.0788 0.0979 1.0000
9.750 1.2825 0.02888 0.02093 -0.0771 0.0908 1.0000
10.000 1.2933 0.03033 0.02240 -0.0754 0.0848 1.0000
10.250 1.3062 0.03155 0.02367 -0.0740 0.0795 1.0000
10.500 1.3185 0.03325 0.02529 -0.0726 0.0747 1.0000
10.750 1.3329 0.03441 0.02664 -0.0714 0.0708 1.0000
11.000 1.3462 0.03572 0.02799 -0.0702 0.0670 1.0000
11.250 1.3658 0.03746 0.02965 -0.0695 0.0630 1.0000
11.500 1.3793 0.03875 0.03115 -0.0683 0.0604 1.0000
11.750 1.3926 0.04015 0.03267 -0.0671 0.0574 1.0000
12.000 1.4064 0.04162 0.03418 -0.0662 0.0547 1.0000
12.250 1.4293 0.04369 0.03631 -0.0659 0.0516 1.0000
12.500 1.4381 0.04532 0.03817 -0.0644 0.0496 1.0000
12.750 1.4467 0.04706 0.04009 -0.0632 0.0473 1.0000
13.000 1.4557 0.04881 0.04191 -0.0621 0.0453 1.0000
13.250 1.4736 0.05150 0.04463 -0.0618 0.0424 1.0000
13.500 1.4721 0.05361 0.04701 -0.0600 0.0411 1.0000
13.750 1.4731 0.05599 0.04963 -0.0587 0.0395 1.0000
14.000 1.4742 0.05835 0.05217 -0.0577 0.0378 1.0000
14.250 1.4768 0.06053 0.05442 -0.0569 0.0362 1.0000
14.500 1.4836 0.06416 0.05810 -0.0564 0.0342 1.0000
14.750 1.4740 0.06748 0.06173 -0.0554 0.0334 1.0000
15.000 1.4644 0.07126 0.06581 -0.0549 0.0325 1.0000
15.250 1.4552 0.07523 0.07003 -0.0547 0.0314 1.0000
15.500 1.4479 0.07908 0.07408 -0.0549 0.0303 1.0000
15.750 1.4412 0.08291 0.07804 -0.0554 0.0293 1.0000
16.000 1.4395 0.08622 0.08140 -0.0559 0.0283 1.0000
16.250 1.4334 0.09085 0.08612 -0.0567 0.0275 1.0000
16.500 1.4126 0.09786 0.09340 -0.0585 0.0271 1.0000
16.750 1.3924 0.10457 0.10039 -0.0612 0.0269 1.0000
17.000 1.3712 0.11199 0.10808 -0.0647 0.0268 1.0000
17.250 1.3486 0.12021 0.11655 -0.0692 0.0267 1.0000
17.500 1.3249 0.12927 0.12585 -0.0747 0.0268 1.0000
17.750 1.2999 0.13928 0.13607 -0.0812 0.0269 1.0000
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