NREL's S804 Airfoil (s804-nr) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: NREL's S804 Airfoil (s804-nr) Reynolds number: 1,000,000 Max Cl/Cd: 128.03 at α=10.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s804-nr-1000000.txt Download as CSV file: xf-s804-nr-1000000.csv |
XFOIL Version 6.96
Calculated polar for: NREL's S804 Airfoil
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.500 -0.6965 0.11039 0.10784 -0.0507 1.0000 0.0146
-17.250 -0.7275 0.10068 0.09798 -0.0562 1.0000 0.0147
-17.000 -0.7480 0.09319 0.09037 -0.0605 1.0000 0.0147
-16.750 -0.7698 0.08576 0.08280 -0.0647 1.0000 0.0147
-16.500 -0.7893 0.07907 0.07598 -0.0685 1.0000 0.0147
-16.250 -0.8113 0.07227 0.06904 -0.0723 1.0000 0.0148
-16.000 -0.8293 0.06645 0.06310 -0.0753 1.0000 0.0149
-15.750 -0.8404 0.06181 0.05837 -0.0776 1.0000 0.0151
-15.500 -0.8478 0.05783 0.05430 -0.0795 1.0000 0.0151
-15.250 -0.8563 0.05394 0.05034 -0.0811 1.0000 0.0152
-15.000 -0.8613 0.05066 0.04700 -0.0823 1.0000 0.0153
-14.750 -0.8658 0.04767 0.04395 -0.0831 1.0000 0.0154
-14.500 -0.8713 0.04478 0.04100 -0.0837 1.0000 0.0154
-14.250 -0.8727 0.04238 0.03856 -0.0841 1.0000 0.0156
-14.000 -0.8765 0.03991 0.03603 -0.0841 1.0000 0.0157
-13.750 -0.8782 0.03777 0.03384 -0.0839 1.0000 0.0158
-13.500 -0.8816 0.03566 0.03168 -0.0834 1.0000 0.0159
-13.250 -0.8848 0.03378 0.02975 -0.0825 1.0000 0.0160
-13.000 -0.8775 0.03177 0.02769 -0.0836 0.9992 0.0161
-12.750 -0.8502 0.02994 0.02579 -0.0878 0.9967 0.0164
-12.500 -0.8212 0.02814 0.02393 -0.0921 0.9940 0.0167
-12.250 -0.7970 0.02635 0.02206 -0.0955 0.9903 0.0169
-12.000 -0.7701 0.02482 0.02046 -0.0987 0.9857 0.0172
-11.750 -0.7365 0.02350 0.01907 -0.1027 0.9827 0.0175
-11.500 -0.7130 0.02224 0.01774 -0.1045 0.9745 0.0177
-11.250 -0.6950 0.02010 0.01553 -0.1070 0.9617 0.0181
-11.000 -0.6698 0.01888 0.01427 -0.1088 0.9464 0.0185
-10.750 -0.6278 0.01795 0.01330 -0.1128 0.9347 0.0189
-10.500 -0.5614 0.01700 0.01230 -0.1214 0.9239 0.0196
-10.250 -0.4927 0.01620 0.01132 -0.1304 0.8934 0.0203
-10.000 -0.4655 0.01594 0.01077 -0.1309 0.8344 0.0207
-9.750 -0.4487 0.01534 0.00998 -0.1299 0.8030 0.0212
-9.500 -0.4290 0.01483 0.00937 -0.1292 0.7764 0.0218
-9.250 -0.4065 0.01455 0.00899 -0.1287 0.7530 0.0224
-9.000 -0.3830 0.01428 0.00861 -0.1282 0.7330 0.0230
-8.750 -0.3588 0.01400 0.00823 -0.1278 0.7149 0.0237
-8.500 -0.3340 0.01377 0.00788 -0.1275 0.6970 0.0242
-8.250 -0.3102 0.01322 0.00724 -0.1274 0.6803 0.0250
-8.000 -0.2845 0.01288 0.00684 -0.1273 0.6649 0.0258
-7.750 -0.2582 0.01262 0.00651 -0.1272 0.6506 0.0266
-7.500 -0.2316 0.01241 0.00621 -0.1271 0.6368 0.0275
-7.250 -0.2041 0.01220 0.00593 -0.1271 0.6244 0.0281
-7.000 -0.1773 0.01178 0.00545 -0.1273 0.6125 0.0295
-6.750 -0.1496 0.01158 0.00519 -0.1273 0.6004 0.0307
-6.500 -0.1216 0.01140 0.00495 -0.1274 0.5896 0.0318
-6.250 -0.0938 0.01113 0.00461 -0.1276 0.5780 0.0333
-6.000 -0.0653 0.01092 0.00436 -0.1278 0.5677 0.0348
-5.500 -0.0083 0.01055 0.00390 -0.1281 0.5469 0.0390
-5.250 0.0201 0.01042 0.00370 -0.1282 0.5365 0.0418
-5.000 0.0493 0.01022 0.00349 -0.1285 0.5283 0.0466
-4.750 0.0782 0.00999 0.00329 -0.1288 0.5190 0.0589
-4.500 0.1076 0.00970 0.00308 -0.1292 0.5111 0.0842
-4.250 0.1369 0.00944 0.00290 -0.1297 0.5026 0.1132
-4.000 0.1662 0.00921 0.00275 -0.1301 0.4945 0.1452
-3.750 0.1960 0.00894 0.00260 -0.1307 0.4873 0.1856
-3.500 0.2255 0.00870 0.00247 -0.1312 0.4793 0.2324
-3.250 0.2555 0.00842 0.00234 -0.1318 0.4728 0.2863
-3.000 0.2854 0.00816 0.00225 -0.1323 0.4658 0.3485
-2.750 0.3145 0.00810 0.00224 -0.1326 0.4579 0.3927
-2.500 0.3442 0.00807 0.00225 -0.1328 0.4524 0.4167
-2.250 0.3734 0.00810 0.00227 -0.1329 0.4461 0.4345
-2.000 0.4021 0.00818 0.00230 -0.1330 0.4394 0.4482
-1.750 0.4315 0.00820 0.00233 -0.1331 0.4349 0.4585
-1.500 0.4607 0.00826 0.00236 -0.1332 0.4299 0.4679
-1.250 0.4895 0.00834 0.00240 -0.1332 0.4246 0.4762
-1.000 0.5181 0.00843 0.00246 -0.1332 0.4191 0.4840
-0.750 0.5474 0.00848 0.00249 -0.1333 0.4157 0.4895
-0.500 0.5764 0.00855 0.00252 -0.1334 0.4115 0.4942
-0.250 0.6051 0.00861 0.00256 -0.1334 0.4072 0.5003
0.000 0.6332 0.00873 0.00264 -0.1333 0.4020 0.5054
0.250 0.6623 0.00879 0.00269 -0.1334 0.3991 0.5102
0.500 0.6913 0.00886 0.00273 -0.1335 0.3959 0.5139
0.750 0.7200 0.00890 0.00278 -0.1335 0.3924 0.5200
1.000 0.7483 0.00899 0.00285 -0.1335 0.3890 0.5247
1.250 0.7763 0.00912 0.00294 -0.1334 0.3851 0.5288
1.500 0.8046 0.00922 0.00303 -0.1334 0.3821 0.5322
1.750 0.8334 0.00929 0.00308 -0.1335 0.3802 0.5347
2.000 0.8621 0.00932 0.00314 -0.1336 0.3780 0.5399
2.250 0.8905 0.00939 0.00323 -0.1336 0.3755 0.5439
2.500 0.9187 0.00949 0.00331 -0.1336 0.3730 0.5477
2.750 0.9465 0.00961 0.00341 -0.1335 0.3703 0.5514
3.000 0.9738 0.00977 0.00354 -0.1333 0.3670 0.5548
3.250 1.0015 0.00988 0.00366 -0.1333 0.3646 0.5596
3.500 1.0299 0.00994 0.00375 -0.1333 0.3631 0.5645
3.750 1.0581 0.01001 0.00386 -0.1333 0.3615 0.5691
4.000 1.0861 0.01011 0.00397 -0.1333 0.3598 0.5736
4.250 1.1139 0.01022 0.00408 -0.1333 0.3580 0.5774
4.500 1.1414 0.01031 0.00421 -0.1332 0.3562 0.5834
4.750 1.1687 0.01044 0.00435 -0.1331 0.3543 0.5893
5.000 1.1955 0.01059 0.00450 -0.1329 0.3521 0.5951
5.250 1.2218 0.01080 0.00470 -0.1326 0.3494 0.6009
5.500 1.2486 0.01096 0.00489 -0.1324 0.3474 0.6076
5.750 1.2761 0.01105 0.00503 -0.1323 0.3464 0.6144
6.000 1.3033 0.01115 0.00517 -0.1322 0.3451 0.6207
6.250 1.3305 0.01124 0.00532 -0.1321 0.3436 0.6287
6.500 1.3574 0.01135 0.00547 -0.1320 0.3417 0.6367
6.750 1.3841 0.01147 0.00562 -0.1318 0.3398 0.6451
7.000 1.4103 0.01160 0.00579 -0.1315 0.3375 0.6548
7.250 1.4356 0.01178 0.00598 -0.1311 0.3346 0.6640
7.500 1.4597 0.01208 0.00628 -0.1306 0.3307 0.6743
7.750 1.4865 0.01213 0.00641 -0.1304 0.3294 0.6846
8.000 1.5128 0.01222 0.00657 -0.1302 0.3276 0.6962
8.250 1.5387 0.01231 0.00673 -0.1299 0.3252 0.7078
8.750 1.5885 0.01259 0.00709 -0.1290 0.3197 0.7345
9.000 1.6115 0.01282 0.00736 -0.1283 0.3166 0.7500
9.250 1.6345 0.01304 0.00763 -0.1275 0.3137 0.7669
9.500 1.6595 0.01312 0.00781 -0.1271 0.3118 0.7853
9.750 1.6836 0.01322 0.00801 -0.1265 0.3095 0.8052
10.000 1.7059 0.01334 0.00821 -0.1256 0.3066 0.8288
10.250 1.7245 0.01347 0.00845 -0.1239 0.3033 0.8696
10.500 1.7410 0.01371 0.00873 -0.1220 0.2995 0.9059
10.750 1.7577 0.01378 0.00893 -0.1200 0.2967 1.0000
11.000 1.7805 0.01394 0.00914 -0.1192 0.2937 1.0000
11.250 1.8013 0.01418 0.00940 -0.1182 0.2895 1.0000
11.500 1.8189 0.01452 0.00973 -0.1167 0.2847 1.0000
11.750 1.8383 0.01482 0.01006 -0.1155 0.2804 1.0000
12.000 1.8579 0.01511 0.01038 -0.1143 0.2744 1.0000
12.250 1.8719 0.01561 0.01085 -0.1124 0.2674 1.0000
12.500 1.8896 0.01600 0.01126 -0.1110 0.2596 1.0000
12.750 1.9012 0.01663 0.01187 -0.1089 0.2499 1.0000
13.000 1.9093 0.01746 0.01264 -0.1063 0.2375 1.0000
13.250 1.9134 0.01851 0.01364 -0.1034 0.2236 1.0000
13.500 1.9134 0.01985 0.01492 -0.1002 0.2096 1.0000
13.750 1.9103 0.02146 0.01648 -0.0970 0.1964 1.0000
14.000 1.9072 0.02322 0.01822 -0.0942 0.1846 1.0000
14.250 1.9031 0.02520 0.02020 -0.0917 0.1740 1.0000
14.500 1.8969 0.02753 0.02252 -0.0894 0.1643 1.0000
14.750 1.8877 0.03030 0.02530 -0.0873 0.1555 1.0000
15.000 1.8812 0.03308 0.02810 -0.0859 0.1474 1.0000
15.250 1.8716 0.03633 0.03138 -0.0846 0.1406 1.0000
15.500 1.8597 0.04002 0.03510 -0.0837 0.1337 1.0000
15.750 1.8482 0.04387 0.03901 -0.0832 0.1280 1.0000
16.000 1.8337 0.04823 0.04341 -0.0829 0.1222 1.0000
16.250 1.8186 0.05289 0.04814 -0.0829 0.1175 1.0000
16.500 1.8041 0.05765 0.05296 -0.0832 0.1128 1.0000
16.750 1.7841 0.06329 0.05867 -0.0838 0.1082 1.0000
17.000 1.7713 0.06819 0.06364 -0.0845 0.1044 1.0000
17.250 1.7526 0.07403 0.06955 -0.0856 0.1004 1.0000
17.500 1.7366 0.07968 0.07527 -0.0868 0.0967 1.0000
17.750 1.7243 0.08488 0.08054 -0.0881 0.0931 1.0000
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