NREL's S830 Airfoil (s830-nr) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NREL's S830 Airfoil (s830-nr) Reynolds number: 500,000 Max Cl/Cd: 94.01 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s830-nr-500000-n5.txt Download as CSV file: xf-s830-nr-500000-n5.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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.000 -0.1647 0.08684 0.08425 -0.1363 0.9636 0.0056
-12.750 -0.1801 0.07801 0.07536 -0.1428 0.9622 0.0054
-12.500 -0.2023 0.06934 0.06655 -0.1489 0.9608 0.0053
-12.250 -0.2320 0.06330 0.06039 -0.1494 0.9547 0.0054
-12.000 -0.2482 0.05824 0.05518 -0.1515 0.9505 0.0053
-11.500 -0.2932 0.04670 0.04318 -0.1517 0.9378 0.0054
-11.000 -0.3225 0.03569 0.03131 -0.1479 0.9216 0.0054
-10.750 -0.3116 0.03353 0.02886 -0.1471 0.9141 0.0056
-10.500 -0.2899 0.03153 0.02658 -0.1477 0.9086 0.0056
-10.250 -0.2585 0.02998 0.02479 -0.1496 0.9044 0.0057
-10.000 -0.2266 0.02888 0.02350 -0.1510 0.8978 0.0057
-9.750 -0.1895 0.02796 0.02242 -0.1537 0.8922 0.0057
-9.500 -0.1540 0.02727 0.02158 -0.1555 0.8836 0.0058
-9.250 -0.1203 0.02666 0.02084 -0.1575 0.8732 0.0059
-9.000 -0.0927 0.02614 0.02021 -0.1585 0.8610 0.0061
-8.750 -0.0712 0.02569 0.01965 -0.1586 0.8477 0.0061
-8.500 -0.0547 0.02524 0.01910 -0.1577 0.8345 0.0062
-8.250 -0.0401 0.02480 0.01858 -0.1566 0.8220 0.0064
-8.000 -0.0271 0.02435 0.01804 -0.1552 0.8102 0.0065
-7.750 -0.0152 0.02389 0.01750 -0.1537 0.7992 0.0067
-7.500 -0.0051 0.02340 0.01696 -0.1519 0.7886 0.0070
-7.250 0.0035 0.02289 0.01637 -0.1500 0.7785 0.0070
-7.000 0.0114 0.02237 0.01578 -0.1479 0.7691 0.0072
-6.750 0.0162 0.02177 0.01513 -0.1453 0.7593 0.0078
-6.500 0.0205 0.02121 0.01451 -0.1426 0.7505 0.0081
-6.250 0.0174 0.02053 0.01379 -0.1388 0.7418 0.0089
-6.000 0.0124 0.01994 0.01316 -0.1344 0.7338 0.0089
-5.750 0.0150 0.01924 0.01242 -0.1317 0.7258 0.0095
-5.500 0.0215 0.01846 0.01157 -0.1300 0.7185 0.0108
-5.250 0.0320 0.01756 0.01064 -0.1292 0.7111 0.0134
-5.000 0.0483 0.01667 0.00970 -0.1294 0.7042 0.0165
-4.750 0.0698 0.01578 0.00878 -0.1307 0.6974 0.0211
-4.250 0.1266 0.01386 0.00684 -0.1361 0.6853 0.0453
-3.750 0.2197 0.00953 0.00346 -0.1533 0.6733 0.4446
-3.500 0.2483 0.00953 0.00347 -0.1539 0.6670 0.4681
-3.250 0.2757 0.00963 0.00351 -0.1541 0.6610 0.4821
-3.000 0.3034 0.00972 0.00352 -0.1543 0.6552 0.4913
-2.750 0.3302 0.00982 0.00359 -0.1544 0.6494 0.4962
-2.250 0.3850 0.00997 0.00355 -0.1548 0.6390 0.5043
-2.000 0.4113 0.01004 0.00361 -0.1548 0.6335 0.5070
-1.500 0.4643 0.01012 0.00358 -0.1549 0.6236 0.5092
-1.250 0.4905 0.01015 0.00357 -0.1549 0.6183 0.5101
-1.000 0.5160 0.01021 0.00356 -0.1547 0.6133 0.5111
-0.750 0.5423 0.01024 0.00355 -0.1548 0.6083 0.5121
-0.500 0.5681 0.01028 0.00356 -0.1547 0.6031 0.5133
-0.250 0.5935 0.01035 0.00357 -0.1546 0.5983 0.5145
0.000 0.6198 0.01040 0.00359 -0.1546 0.5940 0.5158
0.250 0.6462 0.01046 0.00361 -0.1547 0.5895 0.5171
0.500 0.6720 0.01053 0.00364 -0.1547 0.5850 0.5182
0.750 0.6975 0.01062 0.00368 -0.1546 0.5810 0.5193
1.000 0.7238 0.01067 0.00375 -0.1546 0.5770 0.5203
1.250 0.7496 0.01074 0.00383 -0.1546 0.5729 0.5214
1.500 0.7750 0.01084 0.00392 -0.1544 0.5688 0.5225
1.750 0.8003 0.01096 0.00402 -0.1543 0.5650 0.5236
2.000 0.8265 0.01104 0.00413 -0.1544 0.5610 0.5248
2.250 0.8521 0.01115 0.00424 -0.1543 0.5569 0.5260
2.500 0.8775 0.01127 0.00436 -0.1542 0.5532 0.5273
2.750 0.9027 0.01141 0.00448 -0.1541 0.5499 0.5287
3.000 0.9289 0.01151 0.00460 -0.1542 0.5467 0.5301
3.250 0.9546 0.01162 0.00473 -0.1542 0.5433 0.5314
3.500 0.9800 0.01174 0.00487 -0.1541 0.5400 0.5327
3.750 1.0051 0.01189 0.00500 -0.1540 0.5368 0.5339
4.000 1.0299 0.01204 0.00517 -0.1538 0.5338 0.5351
4.250 1.0555 0.01215 0.00535 -0.1538 0.5308 0.5364
4.500 1.0805 0.01228 0.00553 -0.1537 0.5275 0.5377
4.750 1.1053 0.01243 0.00573 -0.1535 0.5245 0.5391
5.000 1.1299 0.01260 0.00593 -0.1533 0.5217 0.5406
5.250 1.1544 0.01278 0.00613 -0.1531 0.5192 0.5422
5.500 1.1794 0.01294 0.00635 -0.1530 0.5168 0.5437
5.750 1.2040 0.01309 0.00656 -0.1528 0.5140 0.5452
6.000 1.2283 0.01326 0.00678 -0.1526 0.5110 0.5466
6.250 1.2523 0.01344 0.00701 -0.1523 0.5082 0.5480
6.500 1.2764 0.01364 0.00724 -0.1521 0.5058 0.5493
6.750 1.3001 0.01385 0.00749 -0.1518 0.5031 0.5506
7.000 1.3199 0.01404 0.00780 -0.1507 0.4966 0.5518
7.250 1.3335 0.01440 0.00815 -0.1485 0.4857 0.5531
7.500 1.3461 0.01480 0.00855 -0.1462 0.4724 0.5544
7.750 1.3629 0.01513 0.00894 -0.1447 0.4621 0.5557
8.000 1.3788 0.01554 0.00937 -0.1431 0.4528 0.5572
8.250 1.3925 0.01603 0.00988 -0.1411 0.4411 0.5587
8.500 1.4087 0.01647 0.01036 -0.1396 0.4299 0.5603
8.750 1.4221 0.01703 0.01093 -0.1377 0.4160 0.5619
9.000 1.4319 0.01776 0.01164 -0.1353 0.3979 0.5633
9.250 1.4328 0.01893 0.01269 -0.1317 0.3671 0.5645
9.500 1.4231 0.02075 0.01431 -0.1268 0.3255 0.5655
9.750 1.4108 0.02293 0.01631 -0.1219 0.2865 0.5665
10.000 1.4019 0.02513 0.01835 -0.1179 0.2524 0.5674
10.250 1.3937 0.02745 0.02055 -0.1143 0.2210 0.5684
10.500 1.3876 0.02978 0.02278 -0.1112 0.1937 0.5694
10.750 1.3813 0.03229 0.02519 -0.1084 0.1676 0.5705
11.000 1.3760 0.03485 0.02766 -0.1060 0.1443 0.5716
11.250 1.3710 0.03752 0.03025 -0.1038 0.1222 0.5727
11.500 1.3673 0.04021 0.03288 -0.1019 0.1036 0.5738
11.750 1.3654 0.04284 0.03546 -0.1003 0.0884 0.5750
12.000 1.3654 0.04538 0.03799 -0.0990 0.0759 0.5764
12.500 1.3691 0.05034 0.04296 -0.0970 0.0572 0.5790
12.750 1.3722 0.05279 0.04542 -0.0962 0.0504 0.5801
13.000 1.3743 0.05539 0.04804 -0.0955 0.0442 0.5812
13.250 1.3784 0.05784 0.05054 -0.0949 0.0390 0.5824
13.500 1.3821 0.06037 0.05312 -0.0944 0.0347 0.5835
13.750 1.3857 0.06297 0.05577 -0.0940 0.0307 0.5846
14.000 1.3899 0.06554 0.05840 -0.0937 0.0275 0.5858
14.250 1.3935 0.06820 0.06110 -0.0934 0.0244 0.5871
14.500 1.3975 0.07087 0.06383 -0.0933 0.0216 0.5884
14.750 1.4007 0.07365 0.06665 -0.0931 0.0187 0.5899
15.000 1.4046 0.07641 0.06946 -0.0931 0.0163 0.5914
15.500 1.4123 0.08198 0.07514 -0.0932 0.0126 0.5941
15.750 1.4154 0.08491 0.07811 -0.0933 0.0110 0.5953
16.000 1.4195 0.08774 0.08101 -0.0935 0.0095 0.5964
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