NREL's S815 Airfoil (s815-nr) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: NREL's S815 Airfoil (s815-nr) Reynolds number: 1,000,000 Max Cl/Cd: 99.35 at α=8.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s815-nr-1000000.txt Download as CSV file: xf-s815-nr-1000000.csv |
XFOIL Version 6.96
Calculated polar for: NREL's S815 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
------ -------- --------- --------- -------- -------- --------
-11.750 -0.3672 0.09591 0.09305 -0.0656 0.9838 0.2400
-11.500 -0.9351 0.03043 0.02678 -0.0844 0.9705 0.2781
-11.250 -0.9199 0.02809 0.02435 -0.0883 0.9680 0.2784
-11.000 -0.9191 0.02421 0.02031 -0.0931 0.9655 0.2798
-10.750 -0.9295 0.02257 0.01861 -0.0904 0.9574 0.2807
-10.500 -0.9088 0.02148 0.01748 -0.0920 0.9542 0.2813
-10.250 -0.8818 0.02054 0.01651 -0.0942 0.9524 0.2819
-10.000 -0.8512 0.01966 0.01560 -0.0970 0.9510 0.2823
-9.750 -0.8510 0.01863 0.01454 -0.0946 0.9423 0.2828
-9.500 -0.8218 0.01781 0.01369 -0.0968 0.9392 0.2832
-9.250 -0.7869 0.01707 0.01293 -0.0999 0.9373 0.2837
-9.000 -0.7502 0.01636 0.01219 -0.1032 0.9359 0.2840
-8.750 -0.7423 0.01563 0.01143 -0.1015 0.9252 0.2845
-8.500 -0.7119 0.01503 0.01079 -0.1032 0.9209 0.2848
-8.250 -0.6971 0.01457 0.01030 -0.1018 0.9094 0.2852
-8.000 -0.6618 0.01408 0.00978 -0.1040 0.9036 0.2856
-7.750 -0.6273 0.01365 0.00931 -0.1060 0.8932 0.2860
-7.500 -0.5722 0.01321 0.00882 -0.1120 0.8858 0.2865
-7.250 -0.5078 0.01286 0.00841 -0.1197 0.8722 0.2870
-7.000 -0.4585 0.01261 0.00802 -0.1246 0.8458 0.2875
-6.750 -0.4303 0.01249 0.00771 -0.1253 0.8124 0.2879
-6.500 -0.4081 0.01238 0.00747 -0.1248 0.7824 0.2883
-6.000 -0.3653 0.01220 0.00703 -0.1234 0.7320 0.2891
-5.750 -0.3425 0.01211 0.00683 -0.1229 0.7101 0.2895
-5.500 -0.3188 0.01202 0.00664 -0.1226 0.6906 0.2899
-5.250 -0.2944 0.01194 0.00647 -0.1224 0.6726 0.2904
-4.750 -0.2429 0.01178 0.00616 -0.1224 0.6410 0.2913
-4.500 -0.2163 0.01170 0.00601 -0.1225 0.6272 0.2917
-4.250 -0.1899 0.01164 0.00587 -0.1225 0.6138 0.2920
-4.000 -0.1625 0.01156 0.00573 -0.1227 0.6012 0.2923
-3.750 -0.1349 0.01150 0.00561 -0.1230 0.5899 0.2926
-3.500 -0.1076 0.01146 0.00550 -0.1232 0.5784 0.2929
-3.250 -0.0791 0.01140 0.00539 -0.1235 0.5687 0.2931
-3.000 -0.0515 0.01137 0.00531 -0.1237 0.5584 0.2933
-2.750 -0.0227 0.01121 0.00512 -0.1242 0.5500 0.2940
-2.500 0.0055 0.01105 0.00490 -0.1246 0.5409 0.2951
-2.250 0.0345 0.01092 0.00475 -0.1251 0.5330 0.2962
-2.000 0.0636 0.01083 0.00464 -0.1256 0.5252 0.2971
-1.750 0.0920 0.01080 0.00456 -0.1259 0.5172 0.2980
-1.500 0.1220 0.01072 0.00449 -0.1265 0.5119 0.2988
-1.250 0.1513 0.01067 0.00443 -0.1269 0.5059 0.2995
-1.000 0.1798 0.01067 0.00439 -0.1272 0.4997 0.3003
-0.750 0.2094 0.01063 0.00435 -0.1276 0.4952 0.3010
-0.500 0.2390 0.01060 0.00432 -0.1281 0.4907 0.3017
-0.250 0.2681 0.01058 0.00429 -0.1284 0.4862 0.3025
0.000 0.2966 0.01060 0.00428 -0.1286 0.4814 0.3032
0.250 0.3257 0.01060 0.00427 -0.1289 0.4774 0.3040
0.500 0.3556 0.01057 0.00425 -0.1293 0.4747 0.3047
0.750 0.3851 0.01056 0.00424 -0.1297 0.4714 0.3055
1.000 0.4142 0.01056 0.00424 -0.1300 0.4679 0.3062
1.250 0.4428 0.01059 0.00425 -0.1301 0.4643 0.3069
1.500 0.4713 0.01066 0.00429 -0.1303 0.4602 0.3076
1.750 0.5008 0.01068 0.00431 -0.1306 0.4581 0.3081
2.000 0.5303 0.01068 0.00434 -0.1309 0.4561 0.3086
2.250 0.5598 0.01068 0.00435 -0.1312 0.4540 0.3092
2.500 0.5904 0.01062 0.00433 -0.1318 0.4517 0.3112
2.750 0.6202 0.01062 0.00434 -0.1322 0.4495 0.3130
3.000 0.6495 0.01065 0.00439 -0.1325 0.4471 0.3147
3.250 0.6784 0.01071 0.00447 -0.1327 0.4445 0.3162
3.500 0.7076 0.01082 0.00458 -0.1329 0.4411 0.3177
3.750 0.7368 0.01086 0.00465 -0.1331 0.4392 0.3191
4.000 0.7655 0.01088 0.00470 -0.1332 0.4372 0.3204
4.250 0.7941 0.01090 0.00476 -0.1333 0.4345 0.3216
4.500 0.8223 0.01094 0.00482 -0.1332 0.4316 0.3228
4.750 0.8498 0.01101 0.00489 -0.1331 0.4281 0.3238
5.000 0.8767 0.01115 0.00500 -0.1328 0.4238 0.3246
5.250 0.9059 0.01120 0.00508 -0.1331 0.4202 0.3271
5.500 0.9348 0.01119 0.00514 -0.1332 0.4173 0.3298
5.750 0.9631 0.01122 0.00522 -0.1332 0.4136 0.3321
6.000 0.9898 0.01131 0.00533 -0.1329 0.4090 0.3341
6.250 1.0155 0.01148 0.00548 -0.1324 0.4038 0.3362
6.500 1.0431 0.01155 0.00560 -0.1323 0.4007 0.3381
6.750 1.0708 0.01161 0.00570 -0.1321 0.3969 0.3398
7.000 1.0973 0.01171 0.00582 -0.1317 0.3922 0.3410
7.250 1.1230 0.01185 0.00595 -0.1313 0.3862 0.3449
7.500 1.1506 0.01192 0.00609 -0.1312 0.3808 0.3480
7.750 1.1774 0.01202 0.00623 -0.1309 0.3744 0.3508
8.000 1.2010 0.01223 0.00642 -0.1300 0.3665 0.3534
8.250 1.2270 0.01235 0.00657 -0.1296 0.3571 0.3558
8.500 1.2490 0.01261 0.00679 -0.1284 0.3426 0.3575
8.750 1.2681 0.01302 0.00709 -0.1270 0.3169 0.3609
9.000 1.2807 0.01376 0.00764 -0.1246 0.2806 0.3643
9.250 1.2911 0.01460 0.00832 -0.1219 0.2486 0.3669
9.500 1.3017 0.01542 0.00900 -0.1192 0.2218 0.3694
9.750 1.3112 0.01631 0.00975 -0.1165 0.1968 0.3717
10.000 1.3208 0.01715 0.01050 -0.1139 0.1763 0.3736
10.250 1.3306 0.01802 0.01127 -0.1113 0.1577 0.3751
10.500 1.3393 0.01895 0.01212 -0.1088 0.1410 0.3780
10.750 1.3481 0.01991 0.01304 -0.1063 0.1265 0.3812
11.000 1.3559 0.02094 0.01403 -0.1039 0.1139 0.3839
11.250 1.3635 0.02202 0.01508 -0.1015 0.1034 0.3865
11.500 1.3698 0.02321 0.01625 -0.0992 0.0939 0.3889
11.750 1.3759 0.02448 0.01750 -0.0970 0.0859 0.3909
12.000 1.3832 0.02576 0.01877 -0.0950 0.0791 0.3927
12.250 1.3892 0.02720 0.02021 -0.0932 0.0731 0.3951
12.500 1.3940 0.02882 0.02185 -0.0915 0.0674 0.3985
12.750 1.4005 0.03041 0.02347 -0.0901 0.0627 0.4016
13.000 1.4036 0.03234 0.02542 -0.0886 0.0582 0.4042
13.250 1.4088 0.03421 0.02733 -0.0875 0.0543 0.4068
13.500 1.4116 0.03637 0.02951 -0.0864 0.0508 0.4091
13.750 1.4153 0.03856 0.03172 -0.0855 0.0475 0.4109
14.000 1.4176 0.04099 0.03420 -0.0848 0.0446 0.4139
14.250 1.4209 0.04342 0.03668 -0.0843 0.0419 0.4177
14.500 1.4217 0.04617 0.03948 -0.0839 0.0395 0.4208
14.750 1.4247 0.04878 0.04215 -0.0836 0.0374 0.4241
15.000 1.4243 0.05182 0.04522 -0.0834 0.0352 0.4268
15.250 1.4260 0.05467 0.04813 -0.0833 0.0334 0.4291
15.500 1.4267 0.05774 0.05125 -0.0834 0.0317 0.4319
15.750 1.4264 0.06101 0.05458 -0.0836 0.0301 0.4357
16.000 1.4293 0.06395 0.05759 -0.0838 0.0287 0.4394
16.250 1.4292 0.06729 0.06099 -0.0842 0.0274 0.4427
16.500 1.4281 0.07081 0.06456 -0.0847 0.0261 0.4457
16.750 1.4311 0.07385 0.06765 -0.0850 0.0250 0.4484
17.000 1.4315 0.07733 0.07119 -0.0857 0.0239 0.4522
17.250 1.4308 0.08099 0.07491 -0.0864 0.0229 0.4563
17.500 1.4330 0.08429 0.07829 -0.0871 0.0221 0.4604
17.750 1.4346 0.08772 0.08178 -0.0879 0.0213 0.4642
18.000 1.4356 0.09122 0.08533 -0.0887 0.0205 0.4675
18.250 1.4349 0.09506 0.08924 -0.0898 0.0197 0.4720
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