NREL's S823 Airfoil (s823-nr) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NREL's S823 Airfoil (s823-nr) Reynolds number: 500,000 Max Cl/Cd: 86.15 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s823-nr-500000.txt Download as CSV file: xf-s823-nr-500000.csv |
XFOIL Version 6.96
Calculated polar for: NREL's S823 Airfoil
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.250 -0.9106 0.08781 0.08334 -0.0593 1.0000 0.1153
-16.000 -0.9270 0.08265 0.07807 -0.0614 1.0000 0.1159
-15.750 -0.9276 0.08006 0.07547 -0.0621 1.0000 0.1178
-15.500 -0.9277 0.07732 0.07272 -0.0629 1.0000 0.1187
-15.250 -0.9263 0.07471 0.07012 -0.0639 1.0000 0.1202
-15.000 -0.9289 0.07161 0.06700 -0.0650 1.0000 0.1212
-14.750 -0.9329 0.06840 0.06374 -0.0661 1.0000 0.1221
-14.500 -0.9366 0.06533 0.06062 -0.0670 1.0000 0.1229
-14.250 -0.9419 0.06213 0.05736 -0.0680 1.0000 0.1239
-14.000 -0.9466 0.05907 0.05425 -0.0689 1.0000 0.1247
-13.750 -0.9507 0.05621 0.05133 -0.0695 1.0000 0.1253
-13.500 -0.9545 0.05351 0.04855 -0.0700 1.0000 0.1259
-13.250 -0.9598 0.05070 0.04568 -0.0705 1.0000 0.1267
-13.000 -0.9642 0.04818 0.04309 -0.0707 1.0000 0.1272
-12.750 -0.9691 0.04583 0.04069 -0.0708 1.0000 0.1277
-12.500 -0.9735 0.04373 0.03853 -0.0704 1.0000 0.1281
-12.250 -0.9804 0.04178 0.03653 -0.0693 1.0000 0.1287
-12.000 -0.9879 0.04016 0.03489 -0.0674 1.0000 0.1299
-11.750 -0.9979 0.03861 0.03334 -0.0651 1.0000 0.1305
-11.500 -0.9790 0.03674 0.03146 -0.0682 0.9977 0.1319
-11.250 -0.9540 0.03485 0.02955 -0.0725 0.9945 0.1332
-11.000 -0.9278 0.03308 0.02775 -0.0768 0.9916 0.1345
-10.750 -0.9038 0.03142 0.02605 -0.0801 0.9870 0.1353
-10.500 -0.8761 0.02989 0.02448 -0.0839 0.9834 0.1360
-10.250 -0.8454 0.02844 0.02297 -0.0880 0.9809 0.1368
-10.000 -0.8257 0.02699 0.02147 -0.0899 0.9732 0.1374
-9.750 -0.7963 0.02564 0.02007 -0.0935 0.9693 0.1381
-9.500 -0.7764 0.02430 0.01868 -0.0952 0.9608 0.1389
-9.250 -0.7483 0.02304 0.01736 -0.0981 0.9558 0.1396
-9.000 -0.7274 0.02184 0.01611 -0.0996 0.9470 0.1401
-8.750 -0.6961 0.02069 0.01490 -0.1027 0.9421 0.1407
-8.500 -0.6606 0.01970 0.01384 -0.1062 0.9384 0.1413
-8.250 -0.6333 0.01843 0.01254 -0.1088 0.9294 0.1431
-8.000 -0.5920 0.01741 0.01152 -0.1134 0.9257 0.1453
-7.750 -0.5567 0.01668 0.01078 -0.1163 0.9179 0.1470
-7.500 -0.5171 0.01606 0.01012 -0.1198 0.9108 0.1488
-7.250 -0.4825 0.01557 0.00958 -0.1220 0.9010 0.1508
-7.000 -0.4461 0.01514 0.00908 -0.1244 0.8918 0.1526
-6.750 -0.4179 0.01483 0.00870 -0.1251 0.8794 0.1541
-6.500 -0.3902 0.01446 0.00826 -0.1257 0.8678 0.1561
-6.250 -0.3636 0.01396 0.00775 -0.1264 0.8568 0.1596
-6.000 -0.3382 0.01365 0.00741 -0.1265 0.8453 0.1624
-5.750 -0.3116 0.01341 0.00714 -0.1267 0.8348 0.1655
-5.250 -0.2584 0.01295 0.00657 -0.1269 0.8141 0.1717
-5.000 -0.2316 0.01268 0.00629 -0.1271 0.8050 0.1760
-4.750 -0.2047 0.01250 0.00609 -0.1271 0.7952 0.1800
-4.500 -0.1771 0.01239 0.00592 -0.1272 0.7860 0.1834
-4.250 -0.1501 0.01214 0.00567 -0.1273 0.7767 0.1881
-4.000 -0.1228 0.01196 0.00550 -0.1274 0.7678 0.1927
-3.750 -0.0947 0.01187 0.00536 -0.1276 0.7593 0.1970
-3.500 -0.0671 0.01172 0.00520 -0.1276 0.7506 0.2015
-3.250 -0.0391 0.01157 0.00505 -0.1278 0.7421 0.2066
-3.000 -0.0111 0.01148 0.00495 -0.1279 0.7335 0.2114
-2.750 0.0173 0.01141 0.00483 -0.1280 0.7255 0.2155
-2.500 0.0453 0.01125 0.00471 -0.1281 0.7173 0.2207
-2.250 0.0737 0.01119 0.00462 -0.1282 0.7092 0.2256
-2.000 0.1022 0.01116 0.00455 -0.1282 0.7012 0.2296
-1.750 0.1305 0.01102 0.00445 -0.1284 0.6933 0.2352
-1.500 0.1591 0.01096 0.00439 -0.1285 0.6857 0.2404
-1.250 0.1876 0.01095 0.00434 -0.1285 0.6777 0.2449
-1.000 0.2163 0.01086 0.00427 -0.1287 0.6705 0.2505
-0.750 0.2448 0.01080 0.00424 -0.1287 0.6626 0.2560
-0.500 0.2736 0.01083 0.00420 -0.1288 0.6556 0.2609
-0.250 0.3021 0.01073 0.00417 -0.1288 0.6480 0.2667
0.000 0.3309 0.01073 0.00416 -0.1289 0.6410 0.2726
0.250 0.3595 0.01073 0.00415 -0.1289 0.6337 0.2777
0.500 0.3882 0.01067 0.00414 -0.1290 0.6266 0.2839
0.750 0.4169 0.01070 0.00416 -0.1290 0.6199 0.2904
1.000 0.4455 0.01067 0.00417 -0.1290 0.6127 0.2966
1.250 0.4744 0.01072 0.00420 -0.1290 0.6063 0.3039
1.500 0.5028 0.01072 0.00424 -0.1290 0.5994 0.3110
1.750 0.5314 0.01072 0.00429 -0.1290 0.5928 0.3185
2.000 0.5600 0.01080 0.00434 -0.1289 0.5864 0.3256
2.250 0.5884 0.01077 0.00440 -0.1288 0.5795 0.3327
2.500 0.6169 0.01086 0.00445 -0.1287 0.5729 0.3396
2.750 0.6448 0.01084 0.00451 -0.1286 0.5656 0.3460
3.000 0.6726 0.01089 0.00457 -0.1283 0.5580 0.3529
3.250 0.7003 0.01095 0.00464 -0.1281 0.5504 0.3600
3.500 0.7279 0.01098 0.00472 -0.1278 0.5428 0.3673
3.750 0.7554 0.01106 0.00481 -0.1275 0.5353 0.3746
4.000 0.7826 0.01109 0.00489 -0.1271 0.5272 0.3815
4.250 0.8096 0.01118 0.00499 -0.1267 0.5193 0.3891
4.500 0.8365 0.01123 0.00509 -0.1263 0.5108 0.3967
4.750 0.8631 0.01133 0.00521 -0.1258 0.5028 0.4047
5.000 0.8894 0.01140 0.00532 -0.1252 0.4937 0.4121
5.250 0.9155 0.01150 0.00546 -0.1246 0.4849 0.4203
5.500 0.9407 0.01161 0.00558 -0.1239 0.4749 0.4283
5.750 0.9662 0.01171 0.00574 -0.1232 0.4646 0.4363
6.000 0.9905 0.01186 0.00588 -0.1223 0.4540 0.4445
6.250 1.0146 0.01199 0.00605 -0.1213 0.4418 0.4529
6.500 1.0382 0.01215 0.00622 -0.1203 0.4287 0.4612
6.750 1.0608 0.01233 0.00643 -0.1191 0.4145 0.4695
7.000 1.0820 0.01256 0.00664 -0.1176 0.3981 0.4781
7.250 1.1002 0.01281 0.00688 -0.1156 0.3791 0.4865
7.500 1.1154 0.01316 0.00715 -0.1131 0.3583 0.4947
7.750 1.1312 0.01354 0.00750 -0.1108 0.3357 0.5031
8.000 1.1448 0.01407 0.00792 -0.1082 0.3106 0.5117
8.250 1.1573 0.01466 0.00843 -0.1056 0.2831 0.5202
8.500 1.1677 0.01538 0.00901 -0.1027 0.2546 0.5288
8.750 1.1766 0.01617 0.00969 -0.0996 0.2277 0.5372
9.000 1.1866 0.01695 0.01036 -0.0969 0.2036 0.5464
9.250 1.1960 0.01776 0.01111 -0.0941 0.1833 0.5558
9.500 1.2055 0.01861 0.01189 -0.0915 0.1655 0.5649
9.750 1.2153 0.01946 0.01271 -0.0890 0.1497 0.5751
10.000 1.2245 0.02038 0.01360 -0.0866 0.1350 0.5849
10.500 1.2428 0.02236 0.01555 -0.0822 0.1105 0.6063
10.750 1.2518 0.02342 0.01662 -0.0801 0.1001 0.6175
11.000 1.2599 0.02460 0.01779 -0.0781 0.0908 0.6296
11.250 1.2667 0.02591 0.01910 -0.0761 0.0820 0.6418
11.500 1.2757 0.02713 0.02037 -0.0744 0.0746 0.6547
11.750 1.2827 0.02854 0.02181 -0.0727 0.0680 0.6684
12.000 1.2899 0.03000 0.02331 -0.0711 0.0620 0.6831
12.250 1.2970 0.03152 0.02489 -0.0697 0.0568 0.6991
12.500 1.3030 0.03318 0.02660 -0.0683 0.0520 0.7165
12.750 1.3094 0.03487 0.02837 -0.0671 0.0478 0.7361
13.000 1.3150 0.03665 0.03023 -0.0659 0.0440 0.7589
13.250 1.3192 0.03857 0.03226 -0.0647 0.0407 0.7863
13.500 1.3240 0.04037 0.03421 -0.0634 0.0378 0.8265
13.750 1.3192 0.04220 0.03627 -0.0610 0.0353 1.0000
14.000 1.3257 0.04431 0.03842 -0.0605 0.0329 1.0000
14.250 1.3301 0.04669 0.04081 -0.0601 0.0306 1.0000
14.500 1.3316 0.04943 0.04357 -0.0597 0.0286 1.0000
14.750 1.3371 0.05181 0.04600 -0.0595 0.0268 1.0000
15.000 1.3395 0.05459 0.04880 -0.0594 0.0252 1.0000
15.250 1.3388 0.05782 0.05206 -0.0594 0.0238 1.0000
15.500 1.3432 0.06054 0.05485 -0.0595 0.0224 1.0000
15.750 1.3451 0.06360 0.05796 -0.0597 0.0213 1.0000
16.000 1.3430 0.06724 0.06164 -0.0602 0.0203 1.0000
16.250 1.3421 0.07084 0.06531 -0.0608 0.0194 1.0000
16.500 1.3446 0.07406 0.06860 -0.0613 0.0186 1.0000
16.750 1.3457 0.07751 0.07212 -0.0620 0.0178 1.0000
17.000 1.3442 0.08141 0.07607 -0.0630 0.0171 1.0000
17.250 1.3390 0.08592 0.08065 -0.0642 0.0165 1.0000
17.500 1.3353 0.09030 0.08511 -0.0655 0.0159 1.0000
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