NREL's S834 Airfoil (s834-nr) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: NREL's S834 Airfoil (s834-nr) Reynolds number: 100,000 Max Cl/Cd: 47.4 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s834-nr-100000.txt Download as CSV file: xf-s834-nr-100000.csv |
XFOIL Version 6.96
Calculated polar for: NREL's S834 Airfoil
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.000 -0.3913 0.13311 0.12838 -0.0412 1.0000 0.1599
-12.750 -0.8070 0.06644 0.06074 -0.0783 1.0000 0.0534
-12.500 -0.8325 0.06326 0.05743 -0.0760 1.0000 0.0533
-12.250 -0.8586 0.06057 0.05459 -0.0726 1.0000 0.0533
-12.000 -0.8852 0.05835 0.05222 -0.0682 1.0000 0.0533
-11.750 -0.9121 0.05662 0.05034 -0.0627 1.0000 0.0533
-11.500 -0.9383 0.05509 0.04865 -0.0565 1.0000 0.0534
-11.250 -0.9583 0.05214 0.04554 -0.0516 1.0000 0.0539
-11.000 -0.9591 0.04977 0.04325 -0.0489 1.0000 0.0565
-10.750 -0.9633 0.04865 0.04210 -0.0451 1.0000 0.0592
-10.500 -0.9721 0.04679 0.04002 -0.0408 1.0000 0.0611
-10.250 -0.9806 0.04475 0.03765 -0.0363 1.0000 0.0632
-10.000 -0.9866 0.04270 0.03516 -0.0319 1.0000 0.0651
-9.750 -0.9803 0.04008 0.03250 -0.0295 1.0000 0.0686
-9.500 -0.9747 0.03892 0.03126 -0.0267 1.0000 0.0733
-9.250 -0.9717 0.03748 0.02939 -0.0232 1.0000 0.0780
-9.000 -0.9586 0.03549 0.02751 -0.0216 1.0000 0.0833
-8.750 -0.9501 0.03432 0.02606 -0.0189 1.0000 0.0900
-8.500 -0.9377 0.03289 0.02470 -0.0170 1.0000 0.0975
-8.250 -0.9263 0.03162 0.02315 -0.0146 1.0000 0.1060
-8.000 -0.9132 0.03062 0.02217 -0.0128 1.0000 0.1159
-7.750 -0.8994 0.02950 0.02108 -0.0109 1.0000 0.1264
-7.500 -0.8852 0.02844 0.02000 -0.0091 1.0000 0.1388
-7.250 -0.8712 0.02758 0.01913 -0.0073 1.0000 0.1529
-7.000 -0.8564 0.02674 0.01830 -0.0056 1.0000 0.1687
-6.750 -0.8412 0.02600 0.01752 -0.0040 1.0000 0.1869
-6.500 -0.8256 0.02528 0.01687 -0.0025 1.0000 0.2061
-6.250 -0.8094 0.02464 0.01631 -0.0010 1.0000 0.2264
-6.000 -0.7928 0.02406 0.01573 0.0004 1.0000 0.2492
-5.750 -0.7759 0.02357 0.01527 0.0017 1.0000 0.2736
-5.500 -0.7587 0.02310 0.01493 0.0030 1.0000 0.2985
-5.250 -0.7411 0.02268 0.01460 0.0042 1.0000 0.3250
-5.000 -0.7233 0.02232 0.01433 0.0054 1.0000 0.3531
-4.750 -0.7051 0.02201 0.01410 0.0066 1.0000 0.3821
-4.500 -0.6869 0.02175 0.01391 0.0078 1.0000 0.4123
-4.250 -0.6685 0.02153 0.01380 0.0090 1.0000 0.4434
-4.000 -0.6501 0.02136 0.01373 0.0102 1.0000 0.4759
-3.750 -0.6316 0.02123 0.01371 0.0114 1.0000 0.5091
-3.500 -0.6067 0.02135 0.01397 0.0115 0.9976 0.5449
-3.250 -0.5695 0.02190 0.01463 0.0094 0.9900 0.5868
-3.000 -0.5343 0.02250 0.01535 0.0078 0.9833 0.6278
-2.750 -0.5059 0.02283 0.01578 0.0077 0.9757 0.6656
-2.250 -0.4505 0.02388 0.01699 0.0082 0.9621 0.7346
-2.000 -0.4180 0.02481 0.01793 0.0077 0.9560 0.7673
-1.750 -0.4011 0.02515 0.01830 0.0103 0.9483 0.7938
-1.250 -0.3558 0.02650 0.01958 0.0134 0.9345 0.8447
-1.000 -0.3237 0.02744 0.02045 0.0132 0.9289 0.8695
-0.750 -0.3054 0.02775 0.02073 0.0154 0.9208 0.8909
-0.500 -0.2637 0.02858 0.02146 0.0131 0.9156 0.9124
-0.250 -0.2247 0.02910 0.02192 0.0108 0.9085 0.9293
0.000 -0.1618 0.02996 0.02267 0.0038 0.9038 0.9423
0.250 -0.0872 0.03083 0.02347 -0.0058 0.8994 0.9503
0.500 -0.0252 0.03135 0.02393 -0.0132 0.8933 0.9601
0.750 0.0456 0.03186 0.02440 -0.0221 0.8892 0.9699
1.000 0.1056 0.03217 0.02470 -0.0294 0.8827 0.9794
1.250 0.1735 0.03234 0.02487 -0.0381 0.8772 0.9877
1.500 0.2488 0.03241 0.02495 -0.0479 0.8739 0.9954
1.750 0.2766 0.03238 0.02493 -0.0495 0.8636 1.0000
2.000 0.2927 0.03230 0.02486 -0.0485 0.8539 1.0000
2.250 0.3277 0.03208 0.02466 -0.0504 0.8468 1.0000
2.500 0.3368 0.03203 0.02461 -0.0480 0.8352 1.0000
2.750 0.3537 0.03196 0.02456 -0.0467 0.8250 1.0000
3.000 0.3950 0.03159 0.02424 -0.0491 0.8183 1.0000
3.250 0.4053 0.03154 0.02422 -0.0465 0.8064 1.0000
3.500 0.4228 0.03140 0.02412 -0.0450 0.7953 1.0000
3.750 0.4748 0.03066 0.02348 -0.0485 0.7896 1.0000
4.000 0.4885 0.03047 0.02334 -0.0461 0.7773 1.0000
4.250 0.5074 0.03018 0.02310 -0.0444 0.7656 1.0000
4.500 0.5718 0.02879 0.02186 -0.0492 0.7611 1.0000
4.750 0.5901 0.02832 0.02149 -0.0470 0.7487 1.0000
5.000 0.6174 0.02754 0.02080 -0.0460 0.7374 1.0000
5.250 0.7060 0.02507 0.01858 -0.0541 0.7334 1.0000
5.500 0.7482 0.02383 0.01751 -0.0552 0.7206 1.0000
5.750 0.8098 0.02215 0.01603 -0.0594 0.7058 1.0000
6.000 0.8511 0.02094 0.01493 -0.0603 0.6860 1.0000
6.250 0.8795 0.02008 0.01418 -0.0591 0.6614 1.0000
6.500 0.8949 0.01960 0.01372 -0.0558 0.6331 1.0000
6.750 0.9067 0.01928 0.01337 -0.0520 0.6000 1.0000
7.000 0.9092 0.01918 0.01318 -0.0466 0.5637 1.0000
7.250 0.9064 0.01920 0.01306 -0.0404 0.5260 1.0000
7.500 0.9020 0.01936 0.01302 -0.0340 0.4858 1.0000
7.750 0.8975 0.01973 0.01313 -0.0280 0.4425 1.0000
8.000 0.8954 0.02036 0.01347 -0.0227 0.3978 1.0000
8.250 0.8949 0.02120 0.01402 -0.0180 0.3538 1.0000
8.500 0.8951 0.02219 0.01472 -0.0138 0.3123 1.0000
8.750 0.8967 0.02328 0.01562 -0.0101 0.2733 1.0000
9.000 0.8993 0.02449 0.01658 -0.0066 0.2376 1.0000
9.250 0.9026 0.02580 0.01768 -0.0035 0.2044 1.0000
9.500 0.9072 0.02719 0.01886 -0.0007 0.1751 1.0000
9.750 0.9132 0.02865 0.02016 0.0018 0.1496 1.0000
10.000 0.9211 0.03022 0.02149 0.0039 0.1289 1.0000
10.250 0.9310 0.03175 0.02301 0.0058 0.1101 1.0000
10.500 0.9428 0.03334 0.02455 0.0075 0.0951 1.0000
10.750 0.9597 0.03512 0.02630 0.0086 0.0828 1.0000
11.000 0.9805 0.03704 0.02815 0.0091 0.0728 1.0000
11.250 0.9944 0.03870 0.02988 0.0104 0.0647 1.0000
11.500 1.0168 0.04114 0.03254 0.0108 0.0581 1.0000
11.750 1.0280 0.04286 0.03430 0.0122 0.0531 1.0000
12.000 1.0534 0.04650 0.03816 0.0120 0.0494 1.0000
12.250 1.0555 0.04892 0.04096 0.0145 0.0472 1.0000
12.500 1.0562 0.05130 0.04361 0.0166 0.0448 1.0000
12.750 1.0580 0.05366 0.04612 0.0184 0.0428 1.0000
13.000 1.0624 0.05641 0.04892 0.0195 0.0408 1.0000
13.250 1.0590 0.06101 0.05378 0.0209 0.0399 1.0000
13.500 1.0478 0.06476 0.05782 0.0227 0.0399 1.0000
13.750 1.0319 0.06898 0.06233 0.0243 0.0397 1.0000
14.000 1.0145 0.07303 0.06664 0.0254 0.0397 1.0000
14.250 0.9932 0.07761 0.07149 0.0259 0.0397 1.0000
14.500 0.9744 0.08164 0.07575 0.0258 0.0400 1.0000
14.750 0.9506 0.08670 0.08106 0.0247 0.0402 1.0000
15.000 0.9199 0.09302 0.08766 0.0221 0.0407 1.0000
15.250 0.8120 0.11523 0.11046 0.0075 0.0469 1.0000
15.500 0.7851 0.12655 0.12180 0.0010 0.0492 1.0000
15.750 0.7690 0.13611 0.13135 -0.0040 0.0502 1.0000
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