NREL's S805A Airfoil (s805a-nr) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NREL's S805A Airfoil (s805a-nr) Reynolds number: 200,000 Max Cl/Cd: 75.59 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s805a-nr-200000.txt Download as CSV file: xf-s805a-nr-200000.csv |
XFOIL Version 6.96
Calculated polar for: NREL's S805A 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
------ -------- --------- --------- -------- -------- --------
-10.000 -0.4207 0.09032 0.08690 -0.0480 1.0000 0.0532
-9.750 -0.4277 0.08575 0.08238 -0.0503 1.0000 0.0543
-9.500 -0.4422 0.07989 0.07658 -0.0545 1.0000 0.0552
-9.250 -0.4648 0.07457 0.07128 -0.0575 1.0000 0.0557
-9.000 -0.4880 0.07102 0.06773 -0.0570 1.0000 0.0555
-8.750 -0.5154 0.06870 0.06544 -0.0538 1.0000 0.0554
-8.500 -0.5419 0.06682 0.06356 -0.0492 1.0000 0.0554
-8.250 -0.5672 0.06509 0.06183 -0.0446 0.9994 0.0561
-8.000 -0.5669 0.05806 0.05402 -0.0515 0.9846 0.0603
-7.750 -0.5381 0.05325 0.04936 -0.0546 0.9786 0.0624
-7.500 -0.5086 0.04997 0.04597 -0.0581 0.9719 0.0677
-7.250 -0.4916 0.04549 0.04098 -0.0606 0.9594 0.0751
-7.000 -0.4629 0.04252 0.03801 -0.0626 0.9492 0.0797
-6.500 -0.4134 0.03085 0.02457 -0.0607 0.9235 0.0460
-6.250 -0.3848 0.02647 0.01976 -0.0612 0.9129 0.0418
-6.000 -0.3538 0.02426 0.01720 -0.0617 0.9004 0.0422
-5.750 -0.3233 0.02229 0.01490 -0.0618 0.8870 0.0422
-5.500 -0.2927 0.02052 0.01286 -0.0619 0.8738 0.0418
-5.250 -0.2635 0.01918 0.01135 -0.0618 0.8611 0.0423
-5.000 -0.2360 0.01813 0.01015 -0.0615 0.8492 0.0433
-4.750 -0.2098 0.01732 0.00922 -0.0609 0.8384 0.0452
-4.500 -0.1857 0.01665 0.00844 -0.0602 0.8277 0.0479
-4.250 -0.1654 0.01573 0.00752 -0.0590 0.8174 0.0510
-4.000 -0.1432 0.01518 0.00690 -0.0580 0.8090 0.0553
-3.750 -0.1224 0.01458 0.00623 -0.0568 0.8003 0.0630
-3.500 -0.1055 0.01350 0.00550 -0.0551 0.7933 0.1311
-3.250 -0.1119 0.01098 0.00528 -0.0498 0.7856 0.6228
-3.000 -0.0902 0.01137 0.00582 -0.0473 0.7798 0.7292
-2.750 -0.0676 0.01186 0.00625 -0.0454 0.7729 0.7681
-2.500 -0.0445 0.01259 0.00691 -0.0428 0.7676 0.7952
-2.250 -0.0222 0.01335 0.00765 -0.0400 0.7625 0.8167
-2.000 -0.0002 0.01430 0.00858 -0.0364 0.7573 0.8410
-1.750 0.0302 0.01513 0.00931 -0.0344 0.7530 0.8599
-1.500 0.0618 0.01530 0.00937 -0.0347 0.7484 0.8662
-1.250 0.0812 0.01519 0.00919 -0.0335 0.7431 0.8733
-1.000 0.1126 0.01519 0.00909 -0.0342 0.7390 0.8763
-0.750 0.1417 0.01520 0.00899 -0.0346 0.7355 0.8805
-0.500 0.1593 0.01513 0.00890 -0.0331 0.7304 0.8877
-0.250 0.1920 0.01516 0.00886 -0.0340 0.7261 0.8910
0.000 0.2216 0.01518 0.00880 -0.0345 0.7226 0.8953
0.250 0.2405 0.01516 0.00875 -0.0331 0.7190 0.9021
0.500 0.2721 0.01518 0.00877 -0.0341 0.7146 0.9050
0.750 0.3013 0.01518 0.00874 -0.0347 0.7106 0.9083
1.000 0.3252 0.01518 0.00868 -0.0342 0.7074 0.9130
1.250 0.3473 0.01518 0.00868 -0.0336 0.7038 0.9172
1.500 0.3774 0.01522 0.00876 -0.0344 0.6994 0.9199
1.750 0.4066 0.01525 0.00878 -0.0350 0.6956 0.9231
2.000 0.4314 0.01527 0.00877 -0.0347 0.6923 0.9273
2.250 0.4545 0.01532 0.00886 -0.0343 0.6884 0.9316
2.500 0.4850 0.01539 0.00897 -0.0352 0.6836 0.9342
2.750 0.5158 0.01542 0.00901 -0.0361 0.6795 0.9372
3.000 0.5447 0.01546 0.00903 -0.0366 0.6760 0.9409
3.250 0.5652 0.01553 0.00921 -0.0357 0.6701 0.9456
3.500 0.5992 0.01553 0.00923 -0.0372 0.6648 0.9478
3.750 0.6333 0.01553 0.00924 -0.0386 0.6598 0.9504
4.000 0.6591 0.01552 0.00932 -0.0386 0.6520 0.9548
4.250 0.6881 0.01539 0.00913 -0.0388 0.6459 0.9585
4.500 0.7216 0.01531 0.00917 -0.0403 0.6363 0.9608
4.750 0.7569 0.01518 0.00907 -0.0419 0.6282 0.9630
5.000 0.7891 0.01503 0.00897 -0.0429 0.6189 0.9664
5.250 0.8140 0.01494 0.00896 -0.0425 0.6097 0.9714
5.500 0.8519 0.01474 0.00878 -0.0446 0.6003 0.9733
5.750 0.8847 0.01457 0.00872 -0.0459 0.5888 0.9764
6.000 0.9143 0.01437 0.00862 -0.0464 0.5755 0.9805
6.250 0.9442 0.01414 0.00847 -0.0469 0.5599 0.9846
6.500 0.9774 0.01390 0.00832 -0.0482 0.5403 0.9883
6.750 1.0067 0.01376 0.00827 -0.0488 0.5151 0.9932
7.000 1.0363 0.01371 0.00828 -0.0496 0.4776 0.9979
7.250 1.0470 0.01391 0.00832 -0.0468 0.4230 1.0000
7.750 1.0209 0.01497 0.00883 -0.0325 0.3265 1.0000
8.250 1.0060 0.01680 0.01009 -0.0217 0.2305 1.0000
8.500 1.0050 0.01796 0.01100 -0.0178 0.1892 1.0000
8.750 1.0059 0.01922 0.01205 -0.0145 0.1564 1.0000
9.000 1.0083 0.02054 0.01322 -0.0117 0.1314 1.0000
9.250 1.0109 0.02195 0.01450 -0.0091 0.1138 1.0000
9.500 1.0152 0.02335 0.01585 -0.0069 0.1005 1.0000
9.750 1.0218 0.02472 0.01723 -0.0050 0.0906 1.0000
10.000 1.0267 0.02630 0.01877 -0.0032 0.0836 1.0000
10.250 1.0368 0.02757 0.02009 -0.0019 0.0768 1.0000
10.500 1.0440 0.02919 0.02168 -0.0005 0.0715 1.0000
10.750 1.0558 0.03039 0.02297 0.0005 0.0659 1.0000
11.000 1.0637 0.03202 0.02453 0.0016 0.0603 1.0000
11.250 1.0752 0.03322 0.02591 0.0023 0.0554 1.0000
11.500 1.0834 0.03480 0.02747 0.0031 0.0509 1.0000
11.750 1.0938 0.03639 0.02917 0.0041 0.0467 1.0000
12.000 1.1024 0.03797 0.03082 0.0048 0.0426 1.0000
12.250 1.1097 0.03995 0.03282 0.0057 0.0381 1.0000
12.500 1.1175 0.04171 0.03472 0.0064 0.0345 1.0000
12.750 1.1265 0.04400 0.03693 0.0074 0.0306 1.0000
13.000 1.1348 0.04595 0.03912 0.0081 0.0287 1.0000
13.250 1.1428 0.04808 0.04143 0.0088 0.0268 1.0000
13.500 1.1497 0.05019 0.04361 0.0093 0.0253 1.0000
13.750 1.1601 0.05316 0.04663 0.0100 0.0235 1.0000
14.000 1.1589 0.05579 0.04951 0.0103 0.0228 1.0000
14.250 1.1585 0.05877 0.05275 0.0105 0.0220 1.0000
14.500 1.1562 0.06211 0.05632 0.0106 0.0213 1.0000
14.750 1.1520 0.06584 0.06030 0.0104 0.0209 1.0000
15.000 1.1452 0.06984 0.06451 0.0099 0.0205 1.0000
15.250 1.1356 0.07437 0.06928 0.0091 0.0203 1.0000
15.500 1.1238 0.07928 0.07442 0.0078 0.0201 1.0000
15.750 1.1080 0.08501 0.08040 0.0060 0.0201 1.0000
16.000 1.0876 0.09180 0.08745 0.0032 0.0202 1.0000
16.250 1.0662 0.09911 0.09500 -0.0003 0.0203 1.0000
16.500 1.0396 0.10799 0.10413 -0.0051 0.0205 1.0000
16.750 1.0105 0.11823 0.11461 -0.0112 0.0209 1.0000
17.000 0.9774 0.13050 0.12709 -0.0190 0.0215 1.0000
17.250 0.9414 0.14500 0.14174 -0.0283 0.0224 1.0000
17.500 0.9077 0.16044 0.15721 -0.0373 0.0232 1.0000
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