NREL's S830 Airfoil (s830-nr) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NREL's S830 Airfoil (s830-nr) Reynolds number: 500,000 Max Cl/Cd: 95.25 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s830-nr-500000.txt Download as CSV file: xf-s830-nr-500000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.500 -0.0419 0.08659 0.08430 -0.1332 0.9611 0.0183
-12.250 -0.0324 0.08304 0.08074 -0.1359 0.9605 0.0189
-12.000 -0.0596 0.07252 0.07018 -0.1412 0.9579 0.0186
-8.500 -0.1072 0.01064 0.00549 -0.1552 0.8778 0.0144
-8.250 -0.1384 0.02488 0.01940 -0.1562 0.8816 0.0140
-8.000 -0.0680 0.02363 0.01809 -0.1576 0.8846 0.0129
-7.750 -0.0223 0.02342 0.01774 -0.1578 0.8803 0.0126
-7.500 0.0112 0.02329 0.01750 -0.1578 0.8722 0.0127
-7.250 0.0405 0.02306 0.01716 -0.1580 0.8626 0.0128
-7.000 0.0571 0.02273 0.01675 -0.1567 0.8505 0.0130
-6.750 0.0698 0.02229 0.01622 -0.1551 0.8384 0.0136
-6.500 0.0794 0.02174 0.01560 -0.1532 0.8272 0.0140
-6.000 0.0808 0.02029 0.01405 -0.1471 0.8050 0.0156
-5.750 0.0767 0.01962 0.01333 -0.1431 0.7948 0.0164
-5.500 0.0748 0.01875 0.01236 -0.1401 0.7852 0.0183
-5.250 0.0752 0.01767 0.01126 -0.1378 0.7756 0.0229
-5.000 0.0884 0.01644 0.01001 -0.1384 0.7677 0.0309
-4.750 0.1069 0.01536 0.00891 -0.1395 0.7596 0.0409
-4.500 0.1365 0.01400 0.00752 -0.1435 0.7530 0.0610
-4.250 0.1929 0.00941 0.00406 -0.1593 0.7455 0.4722
-4.000 0.2224 0.00970 0.00428 -0.1597 0.7392 0.4933
-3.750 0.2503 0.00999 0.00446 -0.1598 0.7323 0.5044
-3.500 0.2762 0.01042 0.00489 -0.1592 0.7256 0.5113
-3.250 0.3048 0.01080 0.00514 -0.1595 0.7193 0.5187
-3.000 0.3290 0.01110 0.00549 -0.1586 0.7125 0.5225
-2.500 0.3811 0.01167 0.00599 -0.1579 0.7003 0.5284
-2.250 0.4086 0.01178 0.00601 -0.1581 0.6942 0.5313
-2.000 0.4374 0.01183 0.00594 -0.1587 0.6885 0.5336
-1.750 0.4643 0.01171 0.00575 -0.1591 0.6823 0.5344
-1.500 0.4922 0.01164 0.00560 -0.1595 0.6768 0.5352
-1.250 0.5187 0.01159 0.00552 -0.1596 0.6710 0.5360
-1.000 0.5449 0.01157 0.00546 -0.1597 0.6650 0.5367
-0.500 0.5984 0.01159 0.00541 -0.1600 0.6538 0.5383
-0.250 0.6249 0.01161 0.00539 -0.1601 0.6484 0.5392
0.000 0.6536 0.01168 0.00538 -0.1607 0.6435 0.5402
0.250 0.6788 0.01168 0.00539 -0.1605 0.6382 0.5413
0.500 0.7054 0.01170 0.00538 -0.1607 0.6330 0.5425
0.750 0.7344 0.01178 0.00538 -0.1614 0.6284 0.5438
1.000 0.7601 0.01179 0.00539 -0.1614 0.6236 0.5452
1.250 0.7864 0.01182 0.00540 -0.1615 0.6187 0.5466
1.500 0.8146 0.01190 0.00541 -0.1620 0.6141 0.5481
1.750 0.8418 0.01198 0.00546 -0.1623 0.6096 0.5493
2.000 0.8666 0.01195 0.00546 -0.1621 0.6049 0.5507
2.250 0.8926 0.01202 0.00553 -0.1621 0.6007 0.5519
2.500 0.9224 0.01216 0.00564 -0.1630 0.5968 0.5530
2.750 0.9456 0.01221 0.00575 -0.1624 0.5928 0.5542
3.000 0.9700 0.01228 0.00586 -0.1621 0.5888 0.5554
3.250 0.9963 0.01238 0.00596 -0.1622 0.5851 0.5568
3.500 1.0270 0.01255 0.00609 -0.1632 0.5815 0.5583
3.750 1.0507 0.01262 0.00621 -0.1628 0.5779 0.5599
4.000 1.0746 0.01270 0.00632 -0.1625 0.5740 0.5615
4.250 1.1005 0.01281 0.00643 -0.1625 0.5706 0.5631
4.500 1.1297 0.01296 0.00657 -0.1633 0.5675 0.5645
4.750 1.1605 0.01310 0.00671 -0.1644 0.5644 0.5660
5.000 1.1828 0.01317 0.00688 -0.1637 0.5614 0.5674
5.250 1.2068 0.01328 0.00707 -0.1634 0.5582 0.5687
5.500 1.2318 0.01341 0.00725 -0.1632 0.5550 0.5702
5.750 1.2598 0.01358 0.00745 -0.1637 0.5521 0.5718
6.000 1.2934 0.01383 0.00772 -0.1654 0.5494 0.5736
6.250 1.3141 0.01395 0.00794 -0.1644 0.5468 0.5754
6.500 1.3360 0.01409 0.00815 -0.1637 0.5434 0.5773
6.750 1.3554 0.01423 0.00832 -0.1624 0.5383 0.5790
7.000 1.3700 0.01441 0.00850 -0.1602 0.5304 0.5803
7.250 1.3797 0.01453 0.00865 -0.1570 0.5212 0.5818
7.500 1.3946 0.01473 0.00891 -0.1550 0.5139 0.5833
7.750 1.4099 0.01494 0.00919 -0.1530 0.5071 0.5847
8.000 1.4269 0.01520 0.00950 -0.1514 0.5002 0.5862
8.250 1.4423 0.01545 0.00985 -0.1495 0.4937 0.5877
8.500 1.4599 0.01577 0.01017 -0.1481 0.4871 0.5894
8.750 1.4745 0.01607 0.01059 -0.1462 0.4796 0.5912
9.250 1.5029 0.01687 0.01149 -0.1424 0.4625 0.5948
9.500 1.5151 0.01738 0.01203 -0.1402 0.4528 0.5963
9.750 1.5246 0.01796 0.01264 -0.1377 0.4404 0.5981
10.000 1.5318 0.01869 0.01341 -0.1349 0.4235 0.5996
10.250 1.5343 0.01969 0.01440 -0.1315 0.3987 0.6010
10.500 1.5264 0.02131 0.01590 -0.1269 0.3633 0.6022
10.750 1.5064 0.02386 0.01821 -0.1211 0.3177 0.6033
11.000 1.4883 0.02664 0.02079 -0.1161 0.2792 0.6044
11.250 1.4700 0.02973 0.02369 -0.1117 0.2425 0.6055
11.500 1.4562 0.03277 0.02659 -0.1081 0.2106 0.6067
11.750 1.4436 0.03592 0.02961 -0.1051 0.1819 0.6079
12.000 1.4329 0.03911 0.03268 -0.1026 0.1565 0.6091
12.250 1.4244 0.04227 0.03575 -0.1005 0.1338 0.6104
12.500 1.4165 0.04552 0.03891 -0.0987 0.1143 0.6115
12.750 1.4117 0.04863 0.04196 -0.0973 0.0971 0.6125
13.000 1.4076 0.05175 0.04505 -0.0961 0.0822 0.6141
13.250 1.4048 0.05480 0.04810 -0.0951 0.0702 0.6154
13.500 1.4032 0.05783 0.05113 -0.0943 0.0602 0.6167
13.750 1.4023 0.06087 0.05418 -0.0936 0.0519 0.6181
14.000 1.4007 0.06405 0.05736 -0.0931 0.0448 0.6194
14.250 1.4025 0.06689 0.06024 -0.0927 0.0395 0.6208
14.500 1.4035 0.06988 0.06327 -0.0924 0.0348 0.6222
14.750 1.4046 0.07292 0.06633 -0.0922 0.0305 0.6237
15.000 1.4072 0.07583 0.06929 -0.0921 0.0271 0.6252
15.250 1.4083 0.07895 0.07242 -0.0921 0.0240 0.6266
15.500 1.4114 0.08186 0.07539 -0.0922 0.0215 0.6280
15.750 1.4136 0.08490 0.07848 -0.0924 0.0191 0.6296
16.000 1.4167 0.08789 0.08156 -0.0926 0.0171 0.6313
16.250 1.4201 0.09084 0.08457 -0.0929 0.0154 0.6329
16.500 1.4201 0.09429 0.08809 -0.0932 0.0140 0.6344
16.750 1.4241 0.09722 0.09112 -0.0936 0.0128 0.6360
17.000 1.4261 0.10042 0.09438 -0.0941 0.0118 0.6377
17.250 1.4254 0.10406 0.09810 -0.0947 0.0108 0.6392
17.500 1.4290 0.10708 0.10122 -0.0953 0.0099 0.6409
17.750 1.4313 0.11032 0.10452 -0.0961 0.0091 0.6425
18.000 1.4282 0.11435 0.10861 -0.0970 0.0084 0.6439
18.250 1.4320 0.11743 0.11182 -0.0979 0.0077 0.6459
18.500 1.4343 0.12070 0.11520 -0.0989 0.0069 0.6478
18.750 1.4308 0.12486 0.11943 -0.1001 0.0063 0.6494
19.000 1.4313 0.12845 0.12314 -0.1013 0.0058 0.6513
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