NREL's S804 Airfoil (s804-nr) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: NREL's S804 Airfoil (s804-nr) Reynolds number: 1,000,000 Max Cl/Cd: 125.53 at α=9° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s804-nr-1000000-n5.txt Download as CSV file: xf-s804-nr-1000000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-18.750 -0.7122 0.12829 0.12568 -0.0419 1.0000 0.0115
-18.500 -0.7387 0.11943 0.11671 -0.0466 1.0000 0.0116
-18.250 -0.7654 0.11086 0.10802 -0.0511 1.0000 0.0116
-18.000 -0.7913 0.10262 0.09966 -0.0556 1.0000 0.0116
-17.750 -0.8169 0.09473 0.09166 -0.0599 1.0000 0.0116
-17.500 -0.8428 0.08692 0.08373 -0.0641 1.0000 0.0117
-17.250 -0.8639 0.08013 0.07682 -0.0678 1.0000 0.0117
-17.000 -0.8826 0.07382 0.07040 -0.0713 1.0000 0.0117
-16.750 -0.8999 0.06792 0.06439 -0.0744 1.0000 0.0117
-16.500 -0.9096 0.06329 0.05967 -0.0768 1.0000 0.0118
-16.250 -0.9202 0.05874 0.05503 -0.0790 1.0000 0.0118
-16.000 -0.9314 0.05433 0.05051 -0.0811 1.0000 0.0119
-15.750 -0.9384 0.05067 0.04677 -0.0826 1.0000 0.0119
-15.500 -0.9452 0.04730 0.04333 -0.0837 1.0000 0.0119
-15.250 -0.9501 0.04436 0.04032 -0.0845 1.0000 0.0120
-15.000 -0.9533 0.04175 0.03764 -0.0849 1.0000 0.0120
-14.750 -0.9576 0.03878 0.03459 -0.0859 0.9998 0.0121
-14.500 -0.9461 0.03583 0.03157 -0.0896 0.9984 0.0122
-14.250 -0.9308 0.03329 0.02897 -0.0931 0.9964 0.0125
-14.000 -0.9112 0.03108 0.02671 -0.0967 0.9940 0.0126
-13.750 -0.8944 0.02911 0.02469 -0.0991 0.9913 0.0128
-13.500 -0.8771 0.02733 0.02286 -0.1013 0.9874 0.0129
-13.250 -0.8558 0.02569 0.02118 -0.1039 0.9837 0.0131
-13.000 -0.8462 0.02419 0.01962 -0.1041 0.9756 0.0133
-12.500 -0.8134 0.02140 0.01673 -0.1063 0.9395 0.0137
-12.250 -0.7387 0.01993 0.01516 -0.1174 0.9253 0.0141
-12.000 -0.6539 0.01876 0.01379 -0.1302 0.8904 0.0146
-11.750 -0.6388 0.01815 0.01284 -0.1300 0.8190 0.0147
-11.500 -0.6279 0.01735 0.01187 -0.1292 0.7841 0.0150
-11.250 -0.6118 0.01680 0.01117 -0.1285 0.7562 0.0153
-11.000 -0.5929 0.01635 0.01061 -0.1278 0.7329 0.0156
-10.750 -0.5722 0.01594 0.01011 -0.1273 0.7132 0.0159
-10.500 -0.5503 0.01556 0.00963 -0.1268 0.6946 0.0162
-10.250 -0.5274 0.01523 0.00920 -0.1265 0.6769 0.0166
-10.000 -0.5035 0.01493 0.00881 -0.1262 0.6597 0.0171
-9.750 -0.4789 0.01462 0.00842 -0.1260 0.6448 0.0175
-9.500 -0.4541 0.01429 0.00801 -0.1258 0.6308 0.0179
-9.000 -0.4029 0.01368 0.00728 -0.1257 0.6051 0.0189
-8.750 -0.3766 0.01343 0.00696 -0.1256 0.5940 0.0195
-8.500 -0.3498 0.01318 0.00665 -0.1256 0.5822 0.0200
-8.250 -0.3228 0.01296 0.00636 -0.1256 0.5714 0.0205
-8.000 -0.2956 0.01274 0.00607 -0.1257 0.5599 0.0210
-7.750 -0.2683 0.01247 0.00575 -0.1258 0.5498 0.0217
-7.500 -0.2407 0.01226 0.00550 -0.1258 0.5402 0.0224
-7.250 -0.2127 0.01207 0.00526 -0.1259 0.5319 0.0232
-7.000 -0.1846 0.01190 0.00503 -0.1261 0.5230 0.0240
-6.750 -0.1565 0.01172 0.00480 -0.1262 0.5147 0.0248
-6.500 -0.1280 0.01151 0.00457 -0.1264 0.5071 0.0257
-6.250 -0.0996 0.01136 0.00436 -0.1265 0.4985 0.0267
-6.000 -0.0709 0.01122 0.00417 -0.1267 0.4910 0.0276
-5.750 -0.0423 0.01107 0.00398 -0.1268 0.4825 0.0288
-5.500 -0.0136 0.01093 0.00381 -0.1270 0.4747 0.0305
-5.250 0.0154 0.01080 0.00365 -0.1272 0.4678 0.0321
-5.000 0.0442 0.01067 0.00349 -0.1274 0.4607 0.0344
-4.750 0.0733 0.01055 0.00334 -0.1276 0.4549 0.0377
-4.500 0.1025 0.01040 0.00320 -0.1279 0.4491 0.0435
-4.250 0.1316 0.01025 0.00306 -0.1281 0.4427 0.0535
-4.000 0.1608 0.01011 0.00293 -0.1284 0.4372 0.0667
-3.750 0.1904 0.00994 0.00281 -0.1288 0.4324 0.0830
-3.250 0.2492 0.00965 0.00260 -0.1295 0.4214 0.1248
-3.000 0.2788 0.00949 0.00251 -0.1299 0.4171 0.1503
-2.750 0.3086 0.00931 0.00242 -0.1303 0.4124 0.1829
-2.500 0.3383 0.00915 0.00234 -0.1308 0.4070 0.2209
-2.000 0.3983 0.00868 0.00219 -0.1320 0.3984 0.3380
-1.750 0.4281 0.00855 0.00218 -0.1324 0.3948 0.3853
-1.500 0.4574 0.00854 0.00220 -0.1326 0.3910 0.4107
-1.250 0.4865 0.00857 0.00224 -0.1327 0.3870 0.4286
-0.750 0.5447 0.00865 0.00230 -0.1329 0.3807 0.4492
-0.500 0.5738 0.00869 0.00234 -0.1330 0.3779 0.4558
-0.250 0.6029 0.00874 0.00238 -0.1331 0.3749 0.4629
0.000 0.6317 0.00881 0.00242 -0.1331 0.3716 0.4689
0.250 0.6603 0.00889 0.00247 -0.1332 0.3682 0.4742
0.500 0.6889 0.00896 0.00253 -0.1332 0.3648 0.4803
0.750 0.7179 0.00902 0.00259 -0.1333 0.3628 0.4861
1.000 0.7466 0.00908 0.00264 -0.1333 0.3605 0.4906
1.250 0.7753 0.00915 0.00270 -0.1334 0.3582 0.4941
1.500 0.8039 0.00922 0.00276 -0.1334 0.3558 0.4979
1.750 0.8323 0.00930 0.00284 -0.1334 0.3534 0.5017
2.000 0.8605 0.00939 0.00292 -0.1334 0.3510 0.5052
2.250 0.8885 0.00950 0.00301 -0.1334 0.3484 0.5083
2.500 0.9169 0.00958 0.00309 -0.1334 0.3469 0.5111
3.000 0.9737 0.00973 0.00326 -0.1334 0.3439 0.5181
3.250 1.0019 0.00981 0.00335 -0.1334 0.3420 0.5222
3.500 1.0298 0.00990 0.00345 -0.1334 0.3399 0.5260
3.750 1.0576 0.01000 0.00356 -0.1333 0.3379 0.5296
4.000 1.0852 0.01012 0.00367 -0.1332 0.3361 0.5328
4.250 1.1126 0.01024 0.00379 -0.1331 0.3342 0.5363
4.500 1.1399 0.01036 0.00393 -0.1330 0.3322 0.5409
4.750 1.1671 0.01049 0.00407 -0.1329 0.3305 0.5459
5.000 1.1947 0.01058 0.00419 -0.1328 0.3296 0.5508
5.250 1.2222 0.01068 0.00432 -0.1327 0.3285 0.5550
5.500 1.2496 0.01078 0.00445 -0.1326 0.3271 0.5597
5.750 1.2768 0.01088 0.00459 -0.1325 0.3255 0.5650
6.000 1.3038 0.01100 0.00474 -0.1323 0.3240 0.5704
6.250 1.3304 0.01113 0.00489 -0.1321 0.3223 0.5754
6.500 1.3568 0.01127 0.00505 -0.1319 0.3202 0.5809
6.750 1.3828 0.01143 0.00524 -0.1316 0.3178 0.5879
7.000 1.4080 0.01162 0.00544 -0.1312 0.3148 0.5948
7.250 1.4345 0.01174 0.00560 -0.1310 0.3128 0.6011
7.500 1.4610 0.01184 0.00576 -0.1308 0.3103 0.6084
7.750 1.4869 0.01198 0.00593 -0.1305 0.3074 0.6157
8.000 1.5121 0.01214 0.00611 -0.1301 0.3045 0.6226
8.250 1.5365 0.01233 0.00633 -0.1296 0.3009 0.6310
8.500 1.5606 0.01254 0.00655 -0.1290 0.2974 0.6389
8.750 1.5860 0.01266 0.00674 -0.1286 0.2947 0.6481
9.000 1.6105 0.01283 0.00695 -0.1281 0.2914 0.6585
9.250 1.6340 0.01302 0.00719 -0.1275 0.2873 0.6690
9.500 1.6558 0.01328 0.00746 -0.1266 0.2829 0.6797
9.750 1.6786 0.01345 0.00769 -0.1258 0.2797 0.6906
10.250 1.7179 0.01396 0.00825 -0.1231 0.2682 0.7141
10.500 1.7374 0.01422 0.00856 -0.1218 0.2620 0.7268
10.750 1.7535 0.01463 0.00896 -0.1200 0.2530 0.7416
11.250 1.7818 0.01560 0.00996 -0.1158 0.2301 0.7801
11.500 1.7902 0.01634 0.01067 -0.1130 0.2155 0.8018
11.750 1.7956 0.01720 0.01153 -0.1098 0.2009 0.8283
12.000 1.7985 0.01809 0.01247 -0.1063 0.1882 0.8853
12.250 1.7984 0.01901 0.01346 -0.1025 0.1770 0.9302
12.500 1.8012 0.02022 0.01465 -0.0997 0.1665 1.0000
12.750 1.8012 0.02165 0.01606 -0.0968 0.1561 1.0000
13.000 1.8017 0.02319 0.01758 -0.0942 0.1463 1.0000
13.250 1.8025 0.02483 0.01923 -0.0920 0.1392 1.0000
13.500 1.8001 0.02684 0.02124 -0.0899 0.1317 1.0000
13.750 1.7995 0.02889 0.02331 -0.0882 0.1251 1.0000
14.000 1.7951 0.03140 0.02584 -0.0866 0.1192 1.0000
14.250 1.7932 0.03387 0.02835 -0.0855 0.1138 1.0000
14.500 1.7857 0.03701 0.03153 -0.0845 0.1086 1.0000
14.750 1.7820 0.03996 0.03453 -0.0838 0.1043 1.0000
15.000 1.7715 0.04376 0.03837 -0.0833 0.0995 1.0000
15.250 1.7637 0.04743 0.04211 -0.0831 0.0959 1.0000
15.500 1.7542 0.05144 0.04619 -0.0830 0.0922 1.0000
15.750 1.7397 0.05622 0.05103 -0.0833 0.0886 1.0000
16.000 1.7306 0.06048 0.05537 -0.0837 0.0859 1.0000
16.250 1.7183 0.06530 0.06027 -0.0844 0.0827 1.0000
16.500 1.7040 0.07050 0.06553 -0.0852 0.0798 1.0000
16.750 1.6939 0.07530 0.07041 -0.0862 0.0773 1.0000
17.000 1.6824 0.08038 0.07557 -0.0873 0.0745 1.0000
17.250 1.6695 0.08577 0.08102 -0.0887 0.0718 1.0000
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