NREL's S834 Airfoil (s834-nr) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NREL's S834 Airfoil (s834-nr) Reynolds number: 200,000 Max Cl/Cd: 70.59 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s834-nr-200000.txt Download as CSV file: xf-s834-nr-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.000 -0.4955 0.15770 0.15391 -0.0431 1.0000 0.0434
-15.750 -0.6803 0.10053 0.09656 -0.0669 1.0000 0.0229
-15.500 -0.7112 0.09158 0.08748 -0.0715 1.0000 0.0226
-15.250 -0.7383 0.08400 0.07974 -0.0751 1.0000 0.0225
-15.000 -0.7622 0.07752 0.07312 -0.0778 1.0000 0.0222
-14.750 -0.7833 0.07195 0.06740 -0.0798 1.0000 0.0221
-14.500 -0.8051 0.06674 0.06201 -0.0813 1.0000 0.0223
-14.250 -0.8223 0.06265 0.05776 -0.0821 1.0000 0.0226
-14.000 -0.8412 0.05848 0.05341 -0.0821 1.0000 0.0226
-13.750 -0.8559 0.05516 0.04992 -0.0814 1.0000 0.0227
-13.500 -0.8702 0.05274 0.04734 -0.0804 1.0000 0.0232
-13.000 -0.9055 0.04602 0.04030 -0.0762 1.0000 0.0245
-12.750 -0.9154 0.04394 0.03816 -0.0736 1.0000 0.0252
-12.500 -0.9242 0.04235 0.03652 -0.0708 1.0000 0.0259
-12.250 -0.9335 0.04097 0.03508 -0.0675 1.0000 0.0268
-12.000 -0.9437 0.03961 0.03362 -0.0638 1.0000 0.0277
-11.750 -0.9546 0.03847 0.03238 -0.0596 1.0000 0.0288
-11.500 -0.9651 0.03728 0.03106 -0.0552 1.0000 0.0298
-11.250 -0.9756 0.03621 0.02985 -0.0504 1.0000 0.0306
-11.000 -0.9894 0.03553 0.02903 -0.0447 1.0000 0.0314
-10.750 -1.0009 0.03406 0.02740 -0.0394 1.0000 0.0327
-10.500 -1.0069 0.03269 0.02601 -0.0350 1.0000 0.0345
-10.250 -1.0086 0.03193 0.02522 -0.0311 1.0000 0.0366
-10.000 -1.0068 0.03105 0.02424 -0.0275 1.0000 0.0389
-9.750 -0.9973 0.03022 0.02320 -0.0252 0.9993 0.0416
-9.500 -0.9759 0.02855 0.02154 -0.0258 0.9957 0.0466
-9.250 -0.9495 0.02782 0.02065 -0.0266 0.9923 0.0523
-9.000 -0.9307 0.02646 0.01928 -0.0263 0.9882 0.0578
-8.750 -0.9029 0.02595 0.01861 -0.0272 0.9846 0.0653
-8.500 -0.8788 0.02495 0.01767 -0.0278 0.9811 0.0743
-8.250 -0.8601 0.02411 0.01679 -0.0270 0.9762 0.0836
-8.000 -0.8339 0.02343 0.01609 -0.0276 0.9724 0.0956
-7.750 -0.8027 0.02291 0.01559 -0.0293 0.9698 0.1108
-7.500 -0.7873 0.02225 0.01495 -0.0276 0.9639 0.1241
-7.250 -0.7606 0.02175 0.01446 -0.0282 0.9600 0.1413
-7.000 -0.7286 0.02135 0.01407 -0.0297 0.9572 0.1624
-6.750 -0.7105 0.02086 0.01363 -0.0285 0.9518 0.1802
-6.500 -0.6845 0.02051 0.01329 -0.0288 0.9474 0.2032
-6.250 -0.6536 0.02013 0.01301 -0.0301 0.9445 0.2276
-6.000 -0.6269 0.01982 0.01276 -0.0305 0.9406 0.2518
-5.750 -0.6068 0.01951 0.01247 -0.0295 0.9350 0.2754
-5.500 -0.5763 0.01923 0.01224 -0.0306 0.9317 0.3040
-5.250 -0.5414 0.01900 0.01209 -0.0324 0.9294 0.3339
-5.000 -0.5265 0.01873 0.01190 -0.0304 0.9229 0.3569
-4.750 -0.4975 0.01850 0.01174 -0.0310 0.9190 0.3858
-4.500 -0.4634 0.01830 0.01161 -0.0326 0.9165 0.4175
-4.250 -0.4425 0.01814 0.01152 -0.0316 0.9112 0.4440
-4.000 -0.4170 0.01796 0.01142 -0.0315 0.9065 0.4731
-3.750 -0.3840 0.01779 0.01132 -0.0327 0.9037 0.5044
-3.500 -0.3478 0.01763 0.01125 -0.0345 0.9018 0.5374
-3.250 -0.3351 0.01756 0.01126 -0.0318 0.8940 0.5622
-3.000 -0.3034 0.01743 0.01122 -0.0327 0.8908 0.5929
-2.750 -0.2681 0.01730 0.01117 -0.0341 0.8887 0.6247
-2.500 -0.2520 0.01733 0.01130 -0.0320 0.8817 0.6500
-2.250 -0.2221 0.01727 0.01132 -0.0323 0.8779 0.6782
-2.000 -0.1877 0.01721 0.01133 -0.0334 0.8755 0.7056
-1.750 -0.1651 0.01730 0.01149 -0.0323 0.8702 0.7300
-1.500 -0.1409 0.01738 0.01161 -0.0314 0.8648 0.7535
-1.250 -0.1075 0.01739 0.01167 -0.0321 0.8621 0.7744
-1.000 -0.0712 0.01740 0.01171 -0.0332 0.8604 0.7932
-0.750 -0.0612 0.01775 0.01207 -0.0297 0.8513 0.8107
-0.500 -0.0288 0.01779 0.01212 -0.0301 0.8484 0.8263
-0.250 0.0071 0.01780 0.01213 -0.0310 0.8466 0.8398
0.000 0.0161 0.01817 0.01251 -0.0271 0.8373 0.8545
0.250 0.0480 0.01816 0.01251 -0.0273 0.8345 0.8659
0.500 0.0845 0.01803 0.01237 -0.0282 0.8327 0.8765
0.750 0.1200 0.01786 0.01220 -0.0290 0.8309 0.8875
1.000 0.1270 0.01811 0.01247 -0.0247 0.8206 0.9012
1.250 0.1674 0.01784 0.01220 -0.0263 0.8191 0.9096
1.500 0.2125 0.01749 0.01186 -0.0290 0.8181 0.9170
1.750 0.2653 0.01717 0.01156 -0.0333 0.8173 0.9224
2.000 0.2809 0.01732 0.01174 -0.0308 0.8071 0.9334
2.250 0.3408 0.01692 0.01136 -0.0366 0.8059 0.9370
2.500 0.3967 0.01645 0.01092 -0.0417 0.8043 0.9416
2.750 0.4470 0.01630 0.01082 -0.0460 0.7976 0.9446
3.000 0.5082 0.01589 0.01046 -0.0524 0.7930 0.9462
3.250 0.5760 0.01533 0.00996 -0.0600 0.7892 0.9468
3.500 0.6040 0.01519 0.00986 -0.0599 0.7784 0.9553
3.750 0.6570 0.01486 0.00961 -0.0648 0.7689 0.9576
4.000 0.7092 0.01448 0.00926 -0.0694 0.7586 0.9603
4.250 0.7496 0.01421 0.00903 -0.0718 0.7458 0.9656
4.500 0.7848 0.01402 0.00890 -0.0732 0.7296 0.9713
4.750 0.8216 0.01384 0.00879 -0.0750 0.7104 0.9767
5.000 0.8560 0.01366 0.00862 -0.0762 0.6894 0.9824
5.250 0.8935 0.01351 0.00847 -0.0783 0.6617 0.9871
5.500 0.9239 0.01349 0.00840 -0.0788 0.6274 0.9931
5.750 0.9565 0.01355 0.00837 -0.0800 0.5840 0.9982
6.000 0.9667 0.01381 0.00846 -0.0768 0.5413 1.0000
6.250 0.9618 0.01414 0.00862 -0.0706 0.5001 1.0000
6.500 0.9520 0.01451 0.00879 -0.0635 0.4606 1.0000
6.750 0.9361 0.01481 0.00893 -0.0553 0.4294 1.0000
7.000 0.9177 0.01510 0.00907 -0.0466 0.4009 1.0000
7.250 0.9025 0.01540 0.00924 -0.0388 0.3735 1.0000
7.500 0.8895 0.01575 0.00946 -0.0314 0.3461 1.0000
7.750 0.8805 0.01617 0.00974 -0.0250 0.3175 1.0000
8.000 0.8792 0.01679 0.01020 -0.0203 0.2858 1.0000
8.250 0.8831 0.01755 0.01079 -0.0167 0.2514 1.0000
8.500 0.8891 0.01841 0.01147 -0.0137 0.2174 1.0000
8.750 0.8967 0.01932 0.01225 -0.0112 0.1868 1.0000
9.000 0.9049 0.02030 0.01307 -0.0088 0.1579 1.0000
9.250 0.9136 0.02133 0.01397 -0.0065 0.1317 1.0000
9.500 0.9225 0.02243 0.01496 -0.0044 0.1096 1.0000
9.750 0.9306 0.02362 0.01604 -0.0023 0.0914 1.0000
10.000 0.9381 0.02490 0.01724 -0.0001 0.0773 1.0000
10.250 0.9464 0.02619 0.01850 0.0019 0.0654 1.0000
10.500 0.9550 0.02751 0.01984 0.0038 0.0561 1.0000
10.750 0.9606 0.02913 0.02144 0.0059 0.0492 1.0000
11.000 0.9720 0.03030 0.02270 0.0073 0.0435 1.0000
11.250 0.9773 0.03215 0.02454 0.0092 0.0384 1.0000
11.500 0.9888 0.03333 0.02582 0.0104 0.0339 1.0000
11.750 0.9945 0.03522 0.02768 0.0120 0.0304 1.0000
12.000 1.0063 0.03698 0.02957 0.0133 0.0284 1.0000
12.250 1.0178 0.03858 0.03130 0.0145 0.0262 1.0000
12.500 1.0267 0.04022 0.03302 0.0157 0.0242 1.0000
12.750 1.0352 0.04219 0.03500 0.0167 0.0224 1.0000
13.000 1.0454 0.04485 0.03785 0.0178 0.0210 1.0000
13.250 1.0499 0.04667 0.03987 0.0189 0.0197 1.0000
13.500 1.0571 0.04910 0.04250 0.0199 0.0194 1.0000
13.750 1.0602 0.05161 0.04521 0.0209 0.0186 1.0000
14.000 1.0610 0.05454 0.04839 0.0218 0.0184 1.0000
14.250 1.0588 0.05750 0.05153 0.0225 0.0177 1.0000
14.500 1.0542 0.06097 0.05522 0.0230 0.0176 1.0000
14.750 1.0473 0.06456 0.05901 0.0231 0.0173 1.0000
15.000 1.0359 0.06899 0.06370 0.0229 0.0173 1.0000
15.250 1.0223 0.07390 0.06885 0.0222 0.0174 1.0000
15.500 1.0044 0.07956 0.07477 0.0208 0.0175 1.0000
15.750 0.9822 0.08625 0.08174 0.0183 0.0176 1.0000
16.000 0.9576 0.09385 0.08959 0.0148 0.0178 1.0000
16.250 0.9270 0.10328 0.09929 0.0096 0.0182 1.0000
16.500 0.8965 0.11373 0.10997 0.0031 0.0188 1.0000
16.750 0.8579 0.12740 0.12383 -0.0057 0.0192 1.0000
17.000 0.8080 0.14623 0.14281 -0.0171 0.0203 1.0000
17.250 0.7759 0.16152 0.15808 -0.0247 0.0213 1.0000
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