NREL's S805A Airfoil (s805a-nr) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: NREL's S805A Airfoil (s805a-nr) Reynolds number: 50,000 Max Cl/Cd: 30.09 at α=9.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s805a-nr-50000.txt Download as CSV file: xf-s805a-nr-50000.csv |
XFOIL Version 6.96
Calculated polar for: NREL's S805A 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.3917 0.12527 0.11821 -0.0264 1.0000 0.2521
-10.750 -0.4091 0.12441 0.11746 -0.0275 1.0000 0.2627
-10.500 -0.3916 0.11996 0.11299 -0.0266 1.0000 0.2763
-10.250 -0.3793 0.11607 0.10913 -0.0260 1.0000 0.2888
-10.000 -0.3732 0.11280 0.10591 -0.0255 1.0000 0.3021
-9.750 -0.3685 0.10975 0.10290 -0.0250 1.0000 0.3161
-9.500 -0.3654 0.10695 0.10016 -0.0242 1.0000 0.3331
-9.250 -0.3709 0.10491 0.09822 -0.0232 1.0000 0.3514
-9.000 -0.3561 0.10125 0.09459 -0.0218 1.0000 0.3716
-8.750 -0.3500 0.09871 0.09210 -0.0203 1.0000 0.3943
-7.000 -0.4245 0.07959 0.07395 -0.0124 1.0000 0.4123
-6.250 -0.6319 0.06748 0.06215 -0.0133 1.0000 0.2609
-6.000 -0.6430 0.05863 0.05225 -0.0176 1.0000 0.1688
-5.750 -0.6402 0.05420 0.04697 -0.0164 1.0000 0.1422
-5.500 -0.6315 0.05090 0.04291 -0.0146 1.0000 0.1289
-5.250 -0.6184 0.04783 0.03970 -0.0135 1.0000 0.1262
-5.000 -0.6045 0.04521 0.03671 -0.0122 1.0000 0.1244
-4.750 -0.5884 0.04282 0.03387 -0.0110 1.0000 0.1225
-4.500 -0.5699 0.04055 0.03112 -0.0098 1.0000 0.1200
-4.250 -0.5496 0.03858 0.02861 -0.0085 1.0000 0.1177
-4.000 -0.5291 0.03692 0.02658 -0.0074 1.0000 0.1174
-3.750 -0.5081 0.03539 0.02483 -0.0063 1.0000 0.1187
-3.500 -0.4878 0.03420 0.02352 -0.0053 1.0000 0.1237
-3.250 -0.4665 0.03335 0.02231 -0.0040 1.0000 0.1295
-3.000 -0.1485 0.03343 0.02546 -0.0299 1.0000 1.0000
-2.750 -0.1499 0.03341 0.02527 -0.0274 1.0000 1.0000
-2.500 -0.1449 0.03340 0.02504 -0.0259 0.9988 1.0000
-2.250 -0.1146 0.03347 0.02478 -0.0289 0.9912 1.0000
-2.000 -0.0872 0.03364 0.02468 -0.0313 0.9844 1.0000
-1.750 -0.0670 0.03376 0.02459 -0.0322 0.9778 1.0000
-1.500 -0.0414 0.03407 0.02468 -0.0340 0.9717 1.0000
-1.250 -0.0284 0.03423 0.02468 -0.0334 0.9657 1.0000
-1.000 -0.0101 0.03453 0.02481 -0.0339 0.9602 1.0000
-0.750 0.0054 0.03487 0.02500 -0.0337 0.9551 1.0000
-0.500 0.0141 0.03512 0.02514 -0.0322 0.9501 1.0000
-0.250 0.0288 0.03552 0.02542 -0.0318 0.9457 1.0000
0.000 0.0413 0.03593 0.02572 -0.0310 0.9414 1.0000
0.250 0.0439 0.03619 0.02590 -0.0284 0.9375 1.0000
0.500 0.0509 0.03656 0.02619 -0.0266 0.9339 1.0000
0.750 0.0647 0.03708 0.02662 -0.0259 0.9301 1.0000
1.000 0.0692 0.03747 0.02695 -0.0237 0.9271 1.0000
1.250 0.0679 0.03772 0.02714 -0.0204 0.9247 1.0000
1.500 0.0692 0.03803 0.02739 -0.0176 0.9223 1.0000
1.750 0.0716 0.03840 0.02770 -0.0150 0.9206 1.0000
2.000 0.0765 0.03884 0.02809 -0.0128 0.9188 1.0000
2.250 0.0839 0.03940 0.02859 -0.0111 0.9173 1.0000
2.500 0.1013 0.04030 0.02942 -0.0111 0.9139 1.0000
2.750 0.1091 0.04094 0.03000 -0.0097 0.9131 1.0000
3.000 0.1195 0.04168 0.03071 -0.0087 0.9123 1.0000
3.250 0.1314 0.04254 0.03153 -0.0081 0.9118 1.0000
3.500 0.1450 0.04357 0.03253 -0.0079 0.9125 1.0000
3.750 0.1599 0.04473 0.03368 -0.0080 0.9135 1.0000
5.500 0.3215 0.05458 0.04378 -0.0162 0.8389 1.0000
5.750 0.3295 0.05603 0.04531 -0.0158 0.8354 1.0000
6.000 0.3419 0.05779 0.04715 -0.0161 0.8321 1.0000
6.250 0.4374 0.05815 0.04771 -0.0216 0.7480 1.0000
6.500 0.4643 0.05924 0.04895 -0.0220 0.7253 1.0000
6.750 0.4962 0.06027 0.05013 -0.0227 0.7016 1.0000
7.000 0.5425 0.06083 0.05091 -0.0241 0.6766 1.0000
7.250 0.5559 0.06186 0.05209 -0.0229 0.6535 1.0000
7.500 0.6000 0.06195 0.05241 -0.0234 0.6290 1.0000
7.750 0.6310 0.06205 0.05273 -0.0228 0.6041 1.0000
8.000 0.6581 0.06210 0.05302 -0.0216 0.5786 1.0000
8.250 0.7028 0.06060 0.05183 -0.0205 0.5522 1.0000
8.500 0.7615 0.05693 0.04857 -0.0186 0.5244 1.0000
8.750 0.8384 0.04935 0.04158 -0.0148 0.4935 1.0000
9.000 0.9725 0.03323 0.02590 -0.0093 0.4089 1.0000
9.250 0.9885 0.03285 0.02449 -0.0047 0.3253 1.0000
9.500 0.9926 0.03487 0.02600 -0.0014 0.2749 1.0000
9.750 1.0110 0.03708 0.02780 -0.0001 0.2331 1.0000
10.000 1.0441 0.03959 0.03011 -0.0006 0.1994 1.0000
10.250 1.0758 0.04233 0.03281 -0.0012 0.1759 1.0000
10.500 1.1057 0.04541 0.03602 -0.0016 0.1603 1.0000
10.750 1.1242 0.04836 0.03913 -0.0009 0.1483 1.0000
11.000 1.1498 0.05197 0.04282 -0.0012 0.1380 1.0000
11.250 1.1432 0.05479 0.04618 0.0022 0.1332 1.0000
11.500 1.1625 0.05861 0.05001 0.0023 0.1245 1.0000
11.750 1.1464 0.06173 0.05359 0.0061 0.1227 1.0000
12.000 1.1278 0.06491 0.05711 0.0096 0.1213 1.0000
12.250 1.1070 0.06845 0.06095 0.0124 0.1203 1.0000
12.500 1.0839 0.07249 0.06524 0.0142 0.1200 1.0000
12.750 1.0571 0.07719 0.07019 0.0150 0.1206 1.0000
13.000 1.0295 0.08260 0.07579 0.0147 0.1217 1.0000
13.250 1.0018 0.08879 0.08212 0.0133 0.1232 1.0000
13.500 0.9753 0.09563 0.08903 0.0111 0.1243 1.0000
13.750 0.9540 0.10290 0.09637 0.0085 0.1252 1.0000
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