NREL's S819 Airfoil (s819-nr) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: NREL's S819 Airfoil (s819-nr) Reynolds number: 50,000 Max Cl/Cd: 22.62 at α=9.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s819-nr-50000-n5.txt Download as CSV file: xf-s819-nr-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NREL's S819 Airfoil
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.250 -0.7393 0.12818 0.11934 -0.0456 1.0000 0.0363
-17.000 -0.7646 0.12261 0.11350 -0.0490 1.0000 0.0358
-16.750 -0.7916 0.11792 0.10855 -0.0520 1.0000 0.0354
-16.500 -0.7829 0.11489 0.10535 -0.0523 1.0000 0.0347
-16.250 -0.7592 0.11236 0.10277 -0.0515 1.0000 0.0341
-16.000 -0.7469 0.10957 0.09983 -0.0514 1.0000 0.0336
-15.750 -0.7354 0.10703 0.09715 -0.0513 1.0000 0.0332
-15.500 -0.7228 0.10474 0.09469 -0.0512 1.0000 0.0331
-15.250 -0.7047 0.10308 0.09288 -0.0505 1.0000 0.0330
-15.000 -0.6808 0.10212 0.09176 -0.0493 1.0000 0.0330
-14.750 -0.6535 0.10177 0.09127 -0.0478 1.0000 0.0333
-14.500 -0.6216 0.10224 0.09159 -0.0458 1.0000 0.0335
-14.250 -0.5875 0.10335 0.09258 -0.0433 1.0000 0.0337
-14.000 -0.5511 0.10521 0.09436 -0.0405 1.0000 0.0337
-13.750 -0.5204 0.10670 0.09579 -0.0381 1.0000 0.0335
-13.500 -0.4933 0.10789 0.09693 -0.0360 1.0000 0.0334
-13.250 -0.4681 0.10896 0.09796 -0.0340 1.0000 0.0334
-13.000 -0.4471 0.10945 0.09843 -0.0325 1.0000 0.0334
-12.750 -0.4276 0.10979 0.09875 -0.0311 1.0000 0.0336
-12.500 -0.4111 0.10964 0.09856 -0.0301 1.0000 0.0337
-12.250 -0.3963 0.10920 0.09810 -0.0292 1.0000 0.0340
-12.000 -0.3835 0.10844 0.09733 -0.0284 1.0000 0.0341
-11.750 -0.3720 0.10745 0.09633 -0.0278 1.0000 0.0345
-11.500 -0.3619 0.10622 0.09507 -0.0273 1.0000 0.0347
-11.250 -0.3533 0.10476 0.09362 -0.0268 1.0000 0.0353
-11.000 -0.3475 0.10297 0.09183 -0.0265 1.0000 0.0362
-10.750 -0.3426 0.10101 0.08989 -0.0262 1.0000 0.0371
-10.500 -0.3382 0.09894 0.08783 -0.0259 1.0000 0.0385
-10.250 -0.3341 0.09685 0.08573 -0.0256 1.0000 0.0398
-10.000 -0.3302 0.09475 0.08361 -0.0253 1.0000 0.0411
-9.750 -0.3258 0.09272 0.08156 -0.0249 1.0000 0.0417
-9.500 -0.3227 0.09057 0.07938 -0.0245 1.0000 0.0431
-9.250 -0.3202 0.08839 0.07719 -0.0240 1.0000 0.0442
-9.000 -0.3192 0.08610 0.07490 -0.0235 1.0000 0.0455
-8.750 -0.2772 0.09099 0.08094 -0.0200 1.0000 0.1769
-8.500 -0.2867 0.08720 0.07706 -0.0201 1.0000 0.2322
-8.250 -0.2968 0.08363 0.07342 -0.0200 1.0000 0.2427
-8.000 -0.3083 0.08014 0.06987 -0.0197 1.0000 0.2510
-7.750 -0.3171 0.07733 0.06702 -0.0191 1.0000 0.2596
-7.500 -0.3275 0.07456 0.06423 -0.0182 1.0000 0.2666
-7.250 -0.3399 0.07196 0.06162 -0.0170 1.0000 0.2745
-7.000 -0.3493 0.07032 0.06002 -0.0154 1.0000 0.2861
-6.750 -0.3660 0.06750 0.05721 -0.0137 1.0000 0.2897
-6.500 -0.3621 0.06778 0.05753 -0.0112 1.0000 0.2995
-6.250 -0.2435 0.08710 0.07701 -0.0026 1.0000 0.3896
-6.000 -0.2480 0.08590 0.07584 -0.0005 1.0000 0.3903
-5.750 -0.2544 0.08469 0.07468 0.0019 1.0000 0.3896
-5.500 -0.2648 0.08361 0.07366 0.0047 1.0000 0.3894
-5.250 -0.2602 0.08199 0.07202 0.0043 0.9958 0.3897
-5.000 -0.2334 0.07947 0.06939 -0.0005 0.9851 0.3905
-4.750 -0.2088 0.07694 0.06675 -0.0049 0.9734 0.3911
-4.500 -0.1860 0.07444 0.06417 -0.0088 0.9605 0.3912
-4.000 -0.1495 0.06940 0.05899 -0.0151 0.9315 0.3917
-3.750 -0.1358 0.06680 0.05633 -0.0177 0.9162 0.3923
-3.500 -0.1305 0.06376 0.05323 -0.0199 0.9003 0.3935
-3.250 -0.1362 0.05983 0.04921 -0.0222 0.8838 0.3960
-3.000 -0.1069 0.05856 0.04792 -0.0238 0.8709 0.3971
-2.750 -0.0787 0.05714 0.04646 -0.0257 0.8583 0.3984
-2.500 -0.0552 0.05535 0.04463 -0.0275 0.8456 0.3999
-2.250 -0.0361 0.05305 0.04226 -0.0297 0.8332 0.4014
-2.000 -0.0241 0.05026 0.03938 -0.0319 0.8202 0.4036
-1.750 -0.0306 0.04624 0.03517 -0.0336 0.8049 0.4073
-1.500 -0.0339 0.04245 0.03114 -0.0354 0.7902 0.4119
-1.250 -0.0064 0.04205 0.03075 -0.0355 0.7777 0.4134
-1.000 0.0219 0.04143 0.03011 -0.0362 0.7659 0.4154
-0.750 0.0511 0.04047 0.02910 -0.0375 0.7552 0.4181
-0.500 0.0674 0.03913 0.02767 -0.0380 0.7417 0.4216
-0.250 0.0818 0.03679 0.02507 -0.0400 0.7290 0.4267
0.000 0.1100 0.03649 0.02480 -0.0401 0.7176 0.4283
0.250 0.1397 0.03608 0.02439 -0.0407 0.7070 0.4303
0.500 0.1616 0.03571 0.02403 -0.0404 0.6942 0.4328
0.750 0.1856 0.03515 0.02345 -0.0408 0.6826 0.4360
1.000 0.2151 0.03405 0.02217 -0.0428 0.6729 0.4414
1.250 0.2376 0.03393 0.02212 -0.0424 0.6609 0.4442
1.500 0.2612 0.03392 0.02221 -0.0419 0.6496 0.4470
1.750 0.2912 0.03362 0.02190 -0.0425 0.6405 0.4510
2.000 0.3139 0.03323 0.02148 -0.0430 0.6291 0.4561
2.250 0.3385 0.03308 0.02137 -0.0431 0.6187 0.4598
2.500 0.3671 0.03301 0.02140 -0.0432 0.6099 0.4631
2.750 0.3882 0.03306 0.02153 -0.0427 0.5991 0.4670
3.000 0.4183 0.03270 0.02110 -0.0441 0.5906 0.4730
3.250 0.4405 0.03285 0.02141 -0.0435 0.5807 0.4765
3.500 0.4643 0.03303 0.02171 -0.0430 0.5718 0.4809
3.750 0.4914 0.03299 0.02171 -0.0435 0.5632 0.4871
4.000 0.5135 0.03321 0.02207 -0.0432 0.5542 0.4922
4.250 0.5401 0.03334 0.02232 -0.0430 0.5464 0.4972
4.500 0.5610 0.03363 0.02270 -0.0428 0.5375 0.5036
4.750 0.5883 0.03373 0.02294 -0.0428 0.5302 0.5091
5.000 0.6063 0.03423 0.02363 -0.0418 0.5215 0.5144
5.250 0.6357 0.03432 0.02378 -0.0426 0.5144 0.5225
5.500 0.6520 0.03494 0.02464 -0.0412 0.5061 0.5274
5.750 0.6788 0.03516 0.02497 -0.0414 0.4989 0.5353
6.000 0.6967 0.03576 0.02577 -0.0405 0.4909 0.5415
6.250 0.7202 0.03613 0.02632 -0.0401 0.4835 0.5491
6.500 0.7393 0.03671 0.02707 -0.0394 0.4754 0.5568
6.750 0.7616 0.03710 0.02764 -0.0387 0.4675 0.5644
7.000 0.7789 0.03773 0.02846 -0.0379 0.4588 0.5725
7.250 0.8035 0.03796 0.02887 -0.0373 0.4508 0.5809
7.500 0.8152 0.03881 0.02993 -0.0358 0.4414 0.5892
7.750 0.8478 0.03861 0.02987 -0.0359 0.4333 0.5995
8.000 0.8508 0.03976 0.03128 -0.0334 0.4230 0.6068
8.250 0.8749 0.03989 0.03158 -0.0329 0.4136 0.6175
8.500 0.8917 0.04021 0.03211 -0.0313 0.4034 0.6266
8.750 0.8978 0.04116 0.03326 -0.0292 0.3927 0.6363
9.000 0.9192 0.04115 0.03342 -0.0280 0.3822 0.6470
9.250 0.9346 0.04131 0.03377 -0.0262 0.3711 0.6577
9.500 0.9298 0.04262 0.03528 -0.0231 0.3599 0.6678
9.750 0.9387 0.04320 0.03607 -0.0210 0.3485 0.6788
10.000 0.9534 0.04333 0.03636 -0.0192 0.3362 0.6912
10.250 0.9625 0.04385 0.03705 -0.0173 0.3237 0.7042
10.500 0.9540 0.04581 0.03922 -0.0151 0.3111 0.7159
10.750 0.9497 0.04756 0.04115 -0.0133 0.2984 0.7286
11.000 0.9478 0.04918 0.04296 -0.0117 0.2853 0.7421
11.250 0.9468 0.05084 0.04479 -0.0104 0.2720 0.7576
11.500 0.9452 0.05266 0.04676 -0.0092 0.2583 0.7748
11.750 0.9425 0.05460 0.04885 -0.0082 0.2446 0.7942
12.000 0.9401 0.05637 0.05075 -0.0068 0.2313 0.8181
12.250 0.9339 0.05854 0.05311 -0.0056 0.2186 0.8499
12.500 0.9208 0.06132 0.05607 -0.0045 0.2070 0.9145
12.750 0.9211 0.06392 0.05865 -0.0056 0.1938 1.0000
13.000 0.9256 0.06671 0.06136 -0.0068 0.1807 1.0000
13.250 0.9285 0.06967 0.06425 -0.0080 0.1687 1.0000
13.500 0.9335 0.07233 0.06680 -0.0089 0.1578 1.0000
13.750 0.9362 0.07536 0.06976 -0.0099 0.1477 1.0000
14.000 0.9302 0.07990 0.07440 -0.0117 0.1392 1.0000
14.250 0.9360 0.08256 0.07696 -0.0125 0.1306 1.0000
14.500 0.9288 0.08749 0.08204 -0.0146 0.1236 1.0000
14.750 0.9322 0.09063 0.08512 -0.0157 0.1164 1.0000
15.000 0.9222 0.09632 0.09099 -0.0184 0.1109 1.0000
15.250 0.9311 0.09854 0.09310 -0.0190 0.1042 1.0000
15.500 0.9108 0.10645 0.10129 -0.0230 0.1005 1.0000
15.750 0.9054 0.11158 0.10649 -0.0256 0.0956 1.0000
16.000 0.9079 0.11524 0.11014 -0.0272 0.0910 1.0000
16.250 0.8676 0.12829 0.12346 -0.0346 0.0896 1.0000
16.500 0.8029 0.14897 0.14421 -0.0464 0.0882 1.0000
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