NREL's S815 Airfoil (s815-nr) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NREL's S815 Airfoil (s815-nr) Reynolds number: 200,000 Max Cl/Cd: 54.79 at α=9° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s815-nr-200000-n5.txt Download as CSV file: xf-s815-nr-200000-n5.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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.1475 0.10475 0.09877 -0.0582 0.9714 0.2543
-9.000 -0.1244 0.10284 0.09685 -0.0607 0.9681 0.2555
-8.500 -0.1370 0.09401 0.08790 -0.0656 0.9588 0.2645
-8.250 -0.1118 0.09273 0.08663 -0.0670 0.9536 0.2649
-8.000 -0.0832 0.09122 0.08513 -0.0695 0.9500 0.2653
-7.750 -0.0708 0.09034 0.08429 -0.0680 0.9384 0.2658
-7.250 -0.0463 0.08843 0.08244 -0.0656 0.9073 0.2669
-7.000 -0.0266 0.08704 0.08105 -0.0662 0.8911 0.2677
-6.750 0.0038 0.08528 0.07927 -0.0692 0.8759 0.2689
-6.500 0.0418 0.08274 0.07667 -0.0746 0.8619 0.2703
-6.000 0.0778 0.07032 0.06387 -0.0935 0.8321 0.2787
-5.750 0.1557 0.06760 0.06095 -0.1067 0.8045 0.2792
-5.500 0.2057 0.06584 0.05895 -0.1137 0.7693 0.2796
-5.250 0.2333 0.06489 0.05781 -0.1156 0.7379 0.2801
-3.750 -0.1298 0.02434 0.01594 -0.1086 0.6579 0.3092
-3.500 -0.1098 0.02386 0.01541 -0.1083 0.6454 0.3099
-3.250 -0.0886 0.02347 0.01495 -0.1082 0.6340 0.3105
-3.000 -0.0670 0.02312 0.01455 -0.1080 0.6225 0.3111
-2.750 -0.0446 0.02280 0.01417 -0.1079 0.6121 0.3117
-2.500 -0.0218 0.02248 0.01381 -0.1078 0.6018 0.3124
-2.250 0.0019 0.02218 0.01344 -0.1080 0.5929 0.3131
-2.000 0.0261 0.02187 0.01310 -0.1081 0.5841 0.3139
-1.500 0.0768 0.02127 0.01240 -0.1088 0.5692 0.3155
-1.250 0.1029 0.02099 0.01207 -0.1093 0.5622 0.3164
-1.000 0.1300 0.02074 0.01173 -0.1099 0.5562 0.3174
-0.750 0.1573 0.02044 0.01142 -0.1105 0.5501 0.3184
-0.500 0.1850 0.02018 0.01111 -0.1112 0.5442 0.3194
-0.250 0.2134 0.01996 0.01081 -0.1119 0.5390 0.3205
0.000 0.2424 0.01974 0.01054 -0.1127 0.5341 0.3216
0.250 0.2712 0.01952 0.01028 -0.1135 0.5287 0.3228
0.500 0.3005 0.01935 0.01004 -0.1143 0.5236 0.3239
0.750 0.3300 0.01923 0.00986 -0.1150 0.5193 0.3251
1.000 0.3584 0.01917 0.00984 -0.1154 0.5156 0.3262
1.250 0.3866 0.01911 0.00986 -0.1157 0.5117 0.3272
1.500 0.4152 0.01909 0.00988 -0.1160 0.5078 0.3283
1.750 0.4442 0.01907 0.00989 -0.1164 0.5043 0.3293
2.000 0.4737 0.01907 0.00989 -0.1170 0.5010 0.3305
2.250 0.5043 0.01910 0.00990 -0.1177 0.4982 0.3317
2.500 0.5333 0.01908 0.00994 -0.1182 0.4950 0.3330
2.750 0.5623 0.01906 0.00997 -0.1186 0.4915 0.3344
3.000 0.5914 0.01905 0.00998 -0.1190 0.4881 0.3359
3.250 0.6213 0.01906 0.01000 -0.1196 0.4851 0.3374
3.500 0.6519 0.01909 0.01002 -0.1203 0.4825 0.3389
3.750 0.6834 0.01914 0.01004 -0.1212 0.4801 0.3405
4.000 0.7142 0.01921 0.01014 -0.1219 0.4778 0.3419
4.250 0.7420 0.01927 0.01033 -0.1220 0.4752 0.3434
4.500 0.7699 0.01935 0.01052 -0.1221 0.4722 0.3449
4.750 0.7981 0.01944 0.01070 -0.1222 0.4692 0.3465
5.000 0.8269 0.01955 0.01088 -0.1225 0.4666 0.3483
5.250 0.8558 0.01967 0.01104 -0.1228 0.4638 0.3504
5.500 0.8861 0.01981 0.01117 -0.1233 0.4605 0.3527
5.750 0.9138 0.01993 0.01135 -0.1234 0.4571 0.3551
6.000 0.9396 0.02004 0.01153 -0.1231 0.4534 0.3574
6.250 0.9650 0.02013 0.01174 -0.1227 0.4493 0.3594
6.500 0.9904 0.02022 0.01192 -0.1222 0.4450 0.3615
6.750 1.0189 0.02037 0.01206 -0.1223 0.4405 0.3636
7.000 1.0387 0.02047 0.01232 -0.1209 0.4351 0.3658
7.250 1.0592 0.02055 0.01249 -0.1196 0.4291 0.3682
7.500 1.0816 0.02064 0.01258 -0.1186 0.4234 0.3707
7.750 1.1007 0.02076 0.01276 -0.1170 0.4174 0.3732
8.000 1.1179 0.02087 0.01296 -0.1152 0.4105 0.3755
8.250 1.1378 0.02102 0.01315 -0.1138 0.4041 0.3778
8.500 1.1559 0.02124 0.01352 -0.1122 0.3972 0.3801
8.750 1.1735 0.02147 0.01386 -0.1105 0.3894 0.3826
9.000 1.1911 0.02174 0.01417 -0.1088 0.3818 0.3854
9.250 1.2071 0.02204 0.01458 -0.1070 0.3721 0.3884
9.500 1.2223 0.02239 0.01497 -0.1051 0.3619 0.3915
9.750 1.2352 0.02280 0.01542 -0.1029 0.3488 0.3942
10.000 1.2463 0.02331 0.01601 -0.1006 0.3319 0.3968
10.250 1.2536 0.02401 0.01671 -0.0978 0.3098 0.3995
10.500 1.2539 0.02509 0.01768 -0.0945 0.2841 0.4021
10.750 1.2498 0.02654 0.01902 -0.0909 0.2605 0.4045
11.000 1.2461 0.02820 0.02059 -0.0878 0.2386 0.4070
11.250 1.2415 0.03009 0.02241 -0.0850 0.2188 0.4094
11.500 1.2367 0.03219 0.02445 -0.0826 0.2011 0.4115
11.750 1.2319 0.03448 0.02675 -0.0806 0.1850 0.4134
12.000 1.2270 0.03698 0.02925 -0.0790 0.1704 0.4155
12.250 1.2224 0.03966 0.03194 -0.0778 0.1575 0.4176
12.500 1.2173 0.04256 0.03485 -0.0768 0.1458 0.4199
12.750 1.2125 0.04560 0.03790 -0.0761 0.1350 0.4223
13.000 1.2098 0.04860 0.04093 -0.0758 0.1251 0.4248
13.250 1.2062 0.05182 0.04416 -0.0756 0.1164 0.4273
13.500 1.2024 0.05518 0.04752 -0.0756 0.1083 0.4298
13.750 1.2013 0.05835 0.05076 -0.0757 0.1007 0.4322
14.000 1.1987 0.06178 0.05424 -0.0760 0.0942 0.4347
14.250 1.1980 0.06507 0.05758 -0.0763 0.0879 0.4376
14.500 1.1973 0.06844 0.06100 -0.0768 0.0824 0.4406
14.750 1.1973 0.07181 0.06440 -0.0773 0.0772 0.4439
15.000 1.1980 0.07516 0.06779 -0.0780 0.0726 0.4473
15.250 1.1986 0.07858 0.07125 -0.0787 0.0682 0.4502
15.500 1.2001 0.08192 0.07468 -0.0795 0.0644 0.4532
15.750 1.2018 0.08533 0.07815 -0.0803 0.0607 0.4564
16.000 1.2031 0.08879 0.08168 -0.0812 0.0575 0.4599
16.250 1.2059 0.09213 0.08507 -0.0821 0.0543 0.4638
16.750 1.2103 0.09902 0.09210 -0.0842 0.0490 0.4711
17.000 1.2126 0.10250 0.09565 -0.0854 0.0466 0.4748
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