NREL's S804 Airfoil (s804-nr) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NREL's S804 Airfoil (s804-nr) Reynolds number: 200,000 Max Cl/Cd: 67.87 at α=9.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s804-nr-200000-n5.txt Download as CSV file: xf-s804-nr-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.000 -0.5420 0.07183 0.06728 -0.0723 1.0000 0.0235
-12.750 -0.5779 0.06370 0.05893 -0.0773 1.0000 0.0235
-12.500 -0.6035 0.05793 0.05297 -0.0803 1.0000 0.0236
-12.250 -0.6233 0.05345 0.04834 -0.0820 1.0000 0.0236
-12.000 -0.6421 0.04960 0.04432 -0.0828 1.0000 0.0237
-11.750 -0.6595 0.04637 0.04094 -0.0827 1.0000 0.0239
-11.500 -0.6745 0.04374 0.03818 -0.0820 0.9998 0.0240
-11.250 -0.6614 0.03976 0.03384 -0.0882 0.9915 0.0243
-11.000 -0.6393 0.03756 0.03160 -0.0916 0.9830 0.0247
-10.750 -0.6240 0.03563 0.02959 -0.0935 0.9683 0.0250
-10.500 -0.6092 0.03377 0.02765 -0.0949 0.9484 0.0254
-10.250 -0.5851 0.03188 0.02564 -0.0975 0.9326 0.0259
-10.000 -0.5551 0.03004 0.02362 -0.1006 0.9183 0.0266
-9.750 -0.5188 0.02829 0.02162 -0.1045 0.9040 0.0276
-9.500 -0.4761 0.02673 0.01993 -0.1091 0.8877 0.0286
-9.250 -0.4307 0.02545 0.01856 -0.1140 0.8648 0.0298
-9.000 -0.3843 0.02417 0.01706 -0.1188 0.8404 0.0311
-8.750 -0.3495 0.02315 0.01577 -0.1211 0.8153 0.0322
-8.500 -0.3236 0.02233 0.01487 -0.1218 0.7906 0.0330
-8.250 -0.3002 0.02167 0.01409 -0.1219 0.7683 0.0340
-8.000 -0.2774 0.02108 0.01335 -0.1217 0.7481 0.0353
-7.750 -0.2550 0.02052 0.01262 -0.1214 0.7298 0.0368
-7.500 -0.2329 0.01994 0.01196 -0.1211 0.7126 0.0380
-7.250 -0.2100 0.01942 0.01133 -0.1208 0.6967 0.0395
-7.000 -0.1866 0.01893 0.01069 -0.1205 0.6814 0.0411
-6.750 -0.1629 0.01840 0.01011 -0.1204 0.6670 0.0429
-6.500 -0.1382 0.01798 0.00958 -0.1203 0.6536 0.0453
-6.250 -0.1132 0.01753 0.00904 -0.1203 0.6403 0.0478
-6.000 -0.0875 0.01712 0.00855 -0.1203 0.6281 0.0509
-5.500 -0.0347 0.01634 0.00764 -0.1205 0.6056 0.0607
-5.250 -0.0079 0.01598 0.00722 -0.1207 0.5951 0.0692
-5.000 0.0195 0.01560 0.00683 -0.1209 0.5841 0.0825
-4.750 0.0469 0.01523 0.00647 -0.1212 0.5741 0.1036
-4.500 0.0749 0.01484 0.00615 -0.1217 0.5639 0.1323
-4.250 0.1029 0.01449 0.00585 -0.1221 0.5550 0.1680
-4.000 0.1318 0.01409 0.00559 -0.1228 0.5460 0.2130
-3.750 0.1605 0.01372 0.00535 -0.1234 0.5377 0.2687
-3.500 0.1897 0.01339 0.00527 -0.1241 0.5298 0.3411
-3.250 0.2182 0.01335 0.00537 -0.1242 0.5217 0.4042
-3.000 0.2465 0.01346 0.00543 -0.1242 0.5145 0.4372
-2.750 0.2752 0.01354 0.00545 -0.1241 0.5067 0.4555
-2.500 0.3035 0.01366 0.00545 -0.1241 0.4994 0.4703
-2.250 0.3314 0.01377 0.00552 -0.1239 0.4928 0.4823
-2.000 0.3601 0.01387 0.00552 -0.1239 0.4860 0.4940
-1.750 0.3878 0.01399 0.00559 -0.1236 0.4800 0.5030
-1.500 0.4164 0.01412 0.00558 -0.1237 0.4747 0.5126
-1.250 0.4443 0.01419 0.00566 -0.1235 0.4690 0.5196
-1.000 0.4724 0.01431 0.00571 -0.1234 0.4636 0.5274
-0.750 0.5007 0.01445 0.00570 -0.1234 0.4589 0.5349
-0.500 0.5284 0.01453 0.00580 -0.1232 0.4543 0.5404
-0.250 0.5565 0.01462 0.00586 -0.1232 0.4493 0.5461
0.000 0.5847 0.01473 0.00589 -0.1232 0.4445 0.5518
0.250 0.6128 0.01486 0.00591 -0.1232 0.4402 0.5568
0.500 0.6404 0.01496 0.00600 -0.1230 0.4362 0.5605
0.750 0.6684 0.01505 0.00609 -0.1230 0.4322 0.5648
1.000 0.6965 0.01516 0.00618 -0.1230 0.4283 0.5695
1.250 0.7245 0.01530 0.00625 -0.1230 0.4248 0.5740
1.500 0.7524 0.01545 0.00633 -0.1230 0.4216 0.5781
1.750 0.7798 0.01560 0.00646 -0.1229 0.4187 0.5821
2.000 0.8076 0.01573 0.00662 -0.1228 0.4155 0.5867
2.250 0.8354 0.01587 0.00677 -0.1228 0.4122 0.5915
2.500 0.8631 0.01602 0.00690 -0.1228 0.4090 0.5962
2.750 0.8904 0.01618 0.00704 -0.1227 0.4059 0.6005
3.000 0.9174 0.01636 0.00721 -0.1225 0.4031 0.6051
3.250 0.9448 0.01658 0.00740 -0.1225 0.4007 0.6105
3.500 0.9723 0.01676 0.00762 -0.1225 0.3982 0.6165
3.750 0.9995 0.01693 0.00784 -0.1224 0.3957 0.6215
4.000 1.0263 0.01712 0.00809 -0.1222 0.3932 0.6265
4.250 1.0530 0.01732 0.00832 -0.1220 0.3908 0.6324
4.500 1.0800 0.01754 0.00854 -0.1219 0.3885 0.6390
4.750 1.1064 0.01776 0.00879 -0.1217 0.3863 0.6450
5.000 1.1331 0.01802 0.00904 -0.1216 0.3841 0.6521
5.250 1.1599 0.01829 0.00932 -0.1215 0.3819 0.6599
5.500 1.1856 0.01851 0.00966 -0.1212 0.3798 0.6664
5.750 1.2115 0.01876 0.01000 -0.1209 0.3777 0.6742
6.000 1.2375 0.01902 0.01033 -0.1207 0.3756 0.6823
6.250 1.2628 0.01928 0.01067 -0.1203 0.3735 0.6906
6.750 1.3134 0.01980 0.01131 -0.1196 0.3693 0.7104
7.000 1.3391 0.02010 0.01164 -0.1194 0.3673 0.7215
7.250 1.3652 0.02043 0.01200 -0.1192 0.3656 0.7326
7.500 1.3892 0.02075 0.01244 -0.1187 0.3637 0.7443
7.750 1.4121 0.02106 0.01289 -0.1180 0.3614 0.7575
8.000 1.4345 0.02136 0.01332 -0.1172 0.3589 0.7718
8.250 1.4568 0.02166 0.01373 -0.1163 0.3565 0.7883
8.500 1.4785 0.02193 0.01411 -0.1154 0.3540 0.8070
8.750 1.4995 0.02218 0.01445 -0.1143 0.3517 0.8287
9.000 1.5199 0.02240 0.01473 -0.1130 0.3493 0.8582
9.250 1.5393 0.02268 0.01509 -0.1117 0.3467 0.9021
9.500 1.5542 0.02292 0.01552 -0.1096 0.3435 1.0000
9.750 1.5734 0.02331 0.01600 -0.1086 0.3399 1.0000
10.000 1.5927 0.02368 0.01641 -0.1075 0.3365 1.0000
10.250 1.6121 0.02401 0.01676 -0.1064 0.3334 1.0000
10.500 1.6319 0.02440 0.01713 -0.1054 0.3302 1.0000
10.750 1.6418 0.02493 0.01782 -0.1028 0.3264 1.0000
11.000 1.6534 0.02544 0.01844 -0.1007 0.3225 1.0000
11.250 1.6661 0.02594 0.01900 -0.0987 0.3187 1.0000
11.500 1.6814 0.02641 0.01946 -0.0972 0.3152 1.0000
11.750 1.6910 0.02713 0.02030 -0.0951 0.3115 1.0000
12.000 1.6981 0.02796 0.02129 -0.0929 0.3070 1.0000
12.250 1.7062 0.02879 0.02220 -0.0909 0.3027 1.0000
12.500 1.7160 0.02958 0.02299 -0.0891 0.2987 1.0000
12.750 1.7199 0.03082 0.02439 -0.0871 0.2938 1.0000
13.000 1.7233 0.03214 0.02585 -0.0853 0.2885 1.0000
13.250 1.7275 0.03347 0.02721 -0.0836 0.2834 1.0000
13.500 1.7277 0.03530 0.02919 -0.0821 0.2776 1.0000
13.750 1.7264 0.03732 0.03131 -0.0807 0.2711 1.0000
14.000 1.7241 0.03959 0.03366 -0.0796 0.2646 1.0000
14.250 1.7184 0.04235 0.03653 -0.0787 0.2569 1.0000
14.500 1.7110 0.04546 0.03972 -0.0780 0.2491 1.0000
14.750 1.6995 0.04917 0.04349 -0.0777 0.2402 1.0000
15.000 1.6858 0.05338 0.04779 -0.0776 0.2309 1.0000
15.250 1.6684 0.05822 0.05266 -0.0779 0.2216 1.0000
15.500 1.6488 0.06361 0.05808 -0.0785 0.2120 1.0000
15.750 1.6289 0.06928 0.06381 -0.0794 0.2026 1.0000
16.000 1.6090 0.07516 0.06971 -0.0806 0.1938 1.0000
16.250 1.5896 0.08119 0.07576 -0.0820 0.1848 1.0000
16.500 1.5736 0.08688 0.08150 -0.0835 0.1765 1.0000
16.750 1.5588 0.09251 0.08712 -0.0850 0.1685 1.0000
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