NREL's S830 Airfoil (s830-nr) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: NREL's S830 Airfoil (s830-nr) Reynolds number: 1,000,000 Max Cl/Cd: 117.82 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s830-nr-1000000.txt Download as CSV file: xf-s830-nr-1000000.csv |
XFOIL Version 6.96
Calculated polar for: NREL's S830 Airfoil
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.750 -0.0028 0.11796 0.11621 -0.1274 0.9743 0.0086
-14.500 0.0042 0.11430 0.11254 -0.1302 0.9740 0.0087
-10.250 -0.2251 0.02921 0.02554 -0.1677 0.9378 0.0077
-10.000 -0.2055 0.02621 0.02222 -0.1678 0.9336 0.0075
-9.750 -0.1928 0.02502 0.02088 -0.1659 0.9227 0.0076
-9.500 -0.1557 0.02357 0.01916 -0.1656 0.9194 0.0072
-9.250 -0.1272 0.02305 0.01849 -0.1649 0.9096 0.0071
-9.000 -0.0941 0.02269 0.01800 -0.1653 0.8988 0.0071
-8.750 -0.0656 0.02230 0.01747 -0.1662 0.8832 0.0072
-8.500 -0.0432 0.02197 0.01701 -0.1660 0.8669 0.0075
-8.250 -0.0258 0.02174 0.01667 -0.1646 0.8516 0.0076
-8.000 -0.0126 0.02147 0.01630 -0.1628 0.8376 0.0076
-7.750 -0.0022 0.02112 0.01586 -0.1606 0.8241 0.0077
-7.500 0.0063 0.02070 0.01536 -0.1583 0.8123 0.0078
-7.250 0.0125 0.02022 0.01480 -0.1557 0.8004 0.0077
-7.000 0.0182 0.01969 0.01422 -0.1532 0.7893 0.0077
-6.750 0.0193 0.01904 0.01350 -0.1500 0.7791 0.0079
-6.250 0.0115 0.01781 0.01216 -0.1416 0.7599 0.0080
-6.000 0.0126 0.01702 0.01131 -0.1389 0.7514 0.0080
-5.750 0.0173 0.01599 0.01022 -0.1373 0.7430 0.0082
-5.500 0.0298 0.01486 0.00902 -0.1374 0.7355 0.0087
-5.250 0.0505 0.01389 0.00801 -0.1386 0.7280 0.0098
-5.000 0.0766 0.01281 0.00685 -0.1411 0.7211 0.0124
-4.750 0.1100 0.01155 0.00559 -0.1453 0.7141 0.0263
-4.500 0.1394 0.01104 0.00504 -0.1471 0.7072 0.0373
-4.250 0.1694 0.01061 0.00463 -0.1488 0.7011 0.0519
-4.000 0.1996 0.01016 0.00421 -0.1505 0.6946 0.0788
-3.750 0.2530 0.00735 0.00246 -0.1610 0.6887 0.4631
-3.500 0.2813 0.00738 0.00250 -0.1614 0.6826 0.4809
-3.250 0.3084 0.00751 0.00253 -0.1615 0.6764 0.4898
-3.000 0.3361 0.00757 0.00259 -0.1618 0.6707 0.4961
-2.750 0.3633 0.00772 0.00268 -0.1618 0.6646 0.5019
-2.500 0.3901 0.00783 0.00270 -0.1619 0.6587 0.5042
-2.250 0.4174 0.00784 0.00271 -0.1621 0.6529 0.5079
-2.000 0.4437 0.00792 0.00274 -0.1620 0.6468 0.5099
-1.750 0.4700 0.00801 0.00280 -0.1619 0.6413 0.5122
-1.500 0.4965 0.00806 0.00282 -0.1620 0.6357 0.5139
-1.250 0.5219 0.00811 0.00281 -0.1618 0.6301 0.5149
-1.000 0.5483 0.00814 0.00280 -0.1618 0.6251 0.5158
-0.750 0.5746 0.00817 0.00280 -0.1618 0.6198 0.5168
-0.500 0.5999 0.00824 0.00281 -0.1616 0.6145 0.5176
-0.250 0.6262 0.00829 0.00282 -0.1616 0.6097 0.5184
0.000 0.6528 0.00833 0.00283 -0.1617 0.6047 0.5192
0.250 0.6783 0.00835 0.00284 -0.1616 0.5997 0.5208
0.500 0.7042 0.00841 0.00288 -0.1616 0.5950 0.5221
0.750 0.7307 0.00845 0.00293 -0.1616 0.5903 0.5233
1.000 0.7562 0.00854 0.00299 -0.1615 0.5854 0.5244
1.250 0.7811 0.00866 0.00308 -0.1612 0.5807 0.5256
1.500 0.8081 0.00871 0.00315 -0.1614 0.5768 0.5269
1.750 0.8343 0.00880 0.00323 -0.1614 0.5725 0.5282
2.000 0.8596 0.00891 0.00333 -0.1613 0.5683 0.5296
2.250 0.8852 0.00904 0.00343 -0.1612 0.5643 0.5310
2.500 0.9121 0.00911 0.00352 -0.1614 0.5608 0.5322
2.750 0.9381 0.00921 0.00361 -0.1614 0.5569 0.5332
3.000 0.9630 0.00934 0.00373 -0.1612 0.5530 0.5340
3.250 0.9883 0.00944 0.00383 -0.1611 0.5490 0.5359
3.500 1.0147 0.00950 0.00393 -0.1612 0.5459 0.5374
3.750 1.0405 0.00959 0.00406 -0.1612 0.5425 0.5388
4.000 1.0656 0.00972 0.00420 -0.1610 0.5392 0.5401
4.250 1.0902 0.00988 0.00436 -0.1608 0.5358 0.5414
4.500 1.1159 0.01001 0.00451 -0.1608 0.5328 0.5428
4.750 1.1418 0.01011 0.00465 -0.1608 0.5301 0.5443
5.000 1.1673 0.01022 0.00480 -0.1607 0.5272 0.5456
5.250 1.1922 0.01036 0.00496 -0.1606 0.5241 0.5470
5.500 1.2165 0.01054 0.00514 -0.1603 0.5211 0.5481
5.750 1.2417 0.01073 0.00533 -0.1602 0.5180 0.5491
6.000 1.2661 0.01081 0.00548 -0.1600 0.5153 0.5508
6.250 1.2878 0.01093 0.00565 -0.1592 0.5092 0.5526
6.500 1.3067 0.01116 0.00587 -0.1579 0.5003 0.5541
6.750 1.3270 0.01134 0.00608 -0.1569 0.4916 0.5556
7.000 1.3472 0.01159 0.00635 -0.1559 0.4852 0.5571
7.250 1.3693 0.01176 0.00657 -0.1552 0.4789 0.5585
7.500 1.3876 0.01208 0.00688 -0.1539 0.4715 0.5600
7.750 1.4111 0.01224 0.00710 -0.1535 0.4659 0.5613
8.000 1.4300 0.01255 0.00742 -0.1524 0.4584 0.5627
8.250 1.4503 0.01282 0.00772 -0.1514 0.4511 0.5638
8.500 1.4675 0.01320 0.00810 -0.1500 0.4419 0.5647
8.750 1.4872 0.01349 0.00843 -0.1491 0.4316 0.5664
9.000 1.4997 0.01404 0.00895 -0.1469 0.4132 0.5681
9.250 1.5050 0.01494 0.00972 -0.1436 0.3812 0.5695
9.500 1.4967 0.01652 0.01105 -0.1384 0.3314 0.5706
9.750 1.4800 0.01868 0.01291 -0.1322 0.2788 0.5716
10.000 1.4662 0.02090 0.01487 -0.1269 0.2333 0.5726
10.250 1.4634 0.02264 0.01650 -0.1234 0.2054 0.5739
10.500 1.4553 0.02484 0.01854 -0.1195 0.1739 0.5751
10.750 1.4472 0.02719 0.02074 -0.1160 0.1447 0.5763
11.000 1.4429 0.02942 0.02287 -0.1131 0.1211 0.5774
11.250 1.4390 0.03176 0.02512 -0.1105 0.1016 0.5784
11.500 1.4369 0.03407 0.02737 -0.1083 0.0843 0.5793
11.750 1.4349 0.03649 0.02972 -0.1063 0.0695 0.5801
12.000 1.4376 0.03859 0.03182 -0.1048 0.0602 0.5809
12.250 1.4405 0.04075 0.03398 -0.1035 0.0521 0.5826
12.500 1.4421 0.04310 0.03633 -0.1022 0.0444 0.5840
12.750 1.4445 0.04545 0.03869 -0.1011 0.0380 0.5853
13.000 1.4487 0.04767 0.04094 -0.1002 0.0331 0.5865
13.250 1.4519 0.05005 0.04335 -0.0993 0.0288 0.5878
13.500 1.4563 0.05235 0.04568 -0.0986 0.0253 0.5891
13.750 1.4601 0.05476 0.04812 -0.0979 0.0226 0.5904
14.000 1.4651 0.05710 0.05050 -0.0974 0.0200 0.5918
14.250 1.4690 0.05959 0.05302 -0.0969 0.0178 0.5931
14.500 1.4737 0.06204 0.05552 -0.0965 0.0159 0.5943
14.750 1.4775 0.06461 0.05813 -0.0961 0.0140 0.5953
15.000 1.4823 0.06713 0.06069 -0.0959 0.0127 0.5962
15.250 1.4854 0.06986 0.06347 -0.0956 0.0112 0.5974
15.500 1.4909 0.07238 0.06606 -0.0956 0.0103 0.5991
15.750 1.4949 0.07508 0.06883 -0.0955 0.0092 0.6007
16.000 1.4984 0.07789 0.07169 -0.0955 0.0082 0.6021
16.250 1.5030 0.08057 0.07444 -0.0956 0.0075 0.6036
16.500 1.5063 0.08342 0.07735 -0.0957 0.0067 0.6051
16.750 1.5090 0.08641 0.08041 -0.0958 0.0060 0.6065
17.000 1.5137 0.08916 0.08322 -0.0961 0.0054 0.6080
17.250 1.5158 0.09229 0.08641 -0.0964 0.0048 0.6093
17.500 1.5184 0.09535 0.08953 -0.0968 0.0043 0.6105
17.750 1.5210 0.09840 0.09266 -0.0972 0.0037 0.6116
18.000 1.5210 0.10184 0.09615 -0.0977 0.0031 0.6125
18.250 1.5231 0.10506 0.09947 -0.0983 0.0026 0.6145
18.500 1.5229 0.10860 0.10307 -0.0990 0.0021 0.6162
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