NREL's S815 Airfoil (s815-nr) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NREL's S815 Airfoil (s815-nr) Reynolds number: 500,000 Max Cl/Cd: 75.89 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s815-nr-500000-n5.txt Download as CSV file: xf-s815-nr-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.500 -0.6116 0.12842 0.12469 -0.0329 0.9995 0.2127
-14.500 -0.5907 0.11709 0.11325 -0.0383 0.9978 0.2239
-14.250 -0.5598 0.11707 0.11322 -0.0400 0.9967 0.2233
-14.000 -0.5180 0.11689 0.11302 -0.0438 0.9946 0.2222
-12.500 -0.4325 0.09732 0.09322 -0.0642 0.9833 0.2373
-12.250 -0.4047 0.09599 0.09187 -0.0671 0.9819 0.2376
-12.000 -0.3773 0.09471 0.09058 -0.0698 0.9807 0.2380
-11.750 -0.3513 0.09346 0.08932 -0.0723 0.9798 0.2383
-11.500 -0.3222 0.09231 0.08815 -0.0752 0.9789 0.2387
-11.250 -0.3051 0.09137 0.08722 -0.0754 0.9768 0.2392
-11.000 -0.2882 0.09059 0.08644 -0.0754 0.9740 0.2397
-10.750 -0.2676 0.08947 0.08532 -0.0766 0.9717 0.2403
-10.250 -0.2942 0.07766 0.07340 -0.0825 0.9675 0.2510
-9.750 -0.7336 0.02938 0.02426 -0.0902 0.9410 0.2780
-9.500 -0.7316 0.02679 0.02155 -0.0922 0.9350 0.2784
-9.250 -0.7449 0.02551 0.02025 -0.0881 0.9207 0.2791
-9.000 -0.7526 0.02433 0.01903 -0.0849 0.9056 0.2797
-8.750 -0.7490 0.02320 0.01787 -0.0833 0.8921 0.2803
-8.500 -0.7269 0.02208 0.01669 -0.0848 0.8821 0.2809
-8.250 -0.6886 0.02106 0.01562 -0.0887 0.8723 0.2814
-8.000 -0.6337 0.02017 0.01467 -0.0953 0.8621 0.2819
-7.750 -0.5544 0.01952 0.01392 -0.1059 0.8481 0.2825
-7.500 -0.4963 0.01890 0.01314 -0.1132 0.8194 0.2830
-7.250 -0.4737 0.01828 0.01232 -0.1144 0.7866 0.2836
-7.000 -0.4601 0.01767 0.01156 -0.1141 0.7588 0.2842
-6.750 -0.4455 0.01711 0.01085 -0.1138 0.7351 0.2848
-6.500 -0.4279 0.01662 0.01024 -0.1139 0.7143 0.2854
-6.000 -0.3874 0.01595 0.00935 -0.1137 0.6784 0.2864
-5.750 -0.3653 0.01569 0.00900 -0.1136 0.6628 0.2869
-5.500 -0.3425 0.01546 0.00868 -0.1135 0.6485 0.2874
-5.250 -0.3193 0.01526 0.00838 -0.1134 0.6349 0.2879
-5.000 -0.2945 0.01505 0.00811 -0.1136 0.6220 0.2884
-4.750 -0.2697 0.01487 0.00785 -0.1136 0.6099 0.2889
-4.500 -0.2447 0.01472 0.00761 -0.1137 0.5975 0.2894
-4.250 -0.2184 0.01455 0.00738 -0.1140 0.5865 0.2899
-4.000 -0.1927 0.01442 0.00718 -0.1141 0.5760 0.2904
-3.750 -0.1652 0.01427 0.00698 -0.1145 0.5668 0.2909
-3.500 -0.1386 0.01415 0.00679 -0.1147 0.5579 0.2913
-3.250 -0.1107 0.01402 0.00662 -0.1151 0.5503 0.2918
-3.000 -0.0830 0.01392 0.00646 -0.1154 0.5423 0.2922
-2.750 -0.0554 0.01383 0.00632 -0.1157 0.5353 0.2926
-2.500 -0.0268 0.01372 0.00618 -0.1162 0.5286 0.2930
-2.250 0.0013 0.01365 0.00606 -0.1166 0.5219 0.2933
-2.000 0.0292 0.01355 0.00593 -0.1169 0.5161 0.2939
-1.750 0.0582 0.01342 0.00580 -0.1174 0.5107 0.2948
-1.500 0.0868 0.01333 0.00570 -0.1178 0.5051 0.2956
-1.250 0.1150 0.01326 0.00562 -0.1181 0.4997 0.2964
-1.000 0.1440 0.01319 0.00554 -0.1186 0.4949 0.2972
-0.750 0.1731 0.01312 0.00548 -0.1190 0.4900 0.2979
-0.500 0.2019 0.01308 0.00543 -0.1194 0.4853 0.2987
-0.250 0.2305 0.01305 0.00539 -0.1197 0.4812 0.2995
0.000 0.2593 0.01303 0.00536 -0.1201 0.4776 0.3003
0.250 0.2890 0.01299 0.00533 -0.1206 0.4744 0.3012
0.500 0.3183 0.01296 0.00531 -0.1210 0.4710 0.3021
0.750 0.3474 0.01294 0.00530 -0.1213 0.4676 0.3029
1.000 0.3763 0.01294 0.00529 -0.1216 0.4643 0.3038
1.250 0.4050 0.01296 0.00530 -0.1219 0.4613 0.3048
1.500 0.4340 0.01298 0.00532 -0.1222 0.4586 0.3058
1.750 0.4636 0.01298 0.00533 -0.1226 0.4562 0.3068
2.000 0.4929 0.01299 0.00535 -0.1229 0.4535 0.3077
2.250 0.5219 0.01300 0.00538 -0.1231 0.4506 0.3084
2.500 0.5508 0.01302 0.00542 -0.1234 0.4479 0.3093
2.750 0.5802 0.01303 0.00546 -0.1238 0.4456 0.3107
3.000 0.6092 0.01307 0.00551 -0.1241 0.4433 0.3120
3.500 0.6679 0.01318 0.00568 -0.1247 0.4392 0.3146
3.750 0.6974 0.01321 0.00577 -0.1250 0.4375 0.3160
4.000 0.7266 0.01325 0.00586 -0.1253 0.4355 0.3175
4.250 0.7555 0.01330 0.00595 -0.1255 0.4331 0.3189
4.500 0.7841 0.01337 0.00605 -0.1256 0.4307 0.3204
4.750 0.8119 0.01345 0.00615 -0.1255 0.4278 0.3219
5.000 0.8388 0.01355 0.00626 -0.1253 0.4243 0.3232
5.250 0.8660 0.01369 0.00639 -0.1252 0.4208 0.3244
5.500 0.8940 0.01372 0.00650 -0.1252 0.4176 0.3261
5.750 0.9213 0.01378 0.00663 -0.1251 0.4132 0.3281
6.000 0.9473 0.01389 0.00677 -0.1247 0.4083 0.3300
6.250 0.9721 0.01406 0.00694 -0.1241 0.4032 0.3320
6.500 0.9989 0.01414 0.00710 -0.1239 0.3985 0.3342
6.750 1.0244 0.01426 0.00726 -0.1234 0.3924 0.3363
7.000 1.0482 0.01444 0.00744 -0.1227 0.3861 0.3384
7.250 1.0737 0.01458 0.00762 -0.1222 0.3806 0.3404
7.500 1.0988 0.01472 0.00781 -0.1217 0.3734 0.3428
7.750 1.1211 0.01494 0.00805 -0.1207 0.3657 0.3454
8.000 1.1459 0.01510 0.00827 -0.1202 0.3559 0.3481
8.250 1.1668 0.01538 0.00854 -0.1190 0.3421 0.3506
8.500 1.1845 0.01578 0.00888 -0.1173 0.3205 0.3529
8.750 1.1953 0.01647 0.00942 -0.1147 0.2896 0.3549
9.000 1.2033 0.01738 0.01016 -0.1119 0.2591 0.3567
9.250 1.2110 0.01834 0.01098 -0.1090 0.2323 0.3584
9.500 1.2190 0.01934 0.01188 -0.1064 0.2080 0.3606
9.750 1.2253 0.02042 0.01287 -0.1037 0.1848 0.3628
10.000 1.2310 0.02157 0.01394 -0.1010 0.1648 0.3651
10.250 1.2368 0.02276 0.01507 -0.0985 0.1474 0.3674
10.500 1.2423 0.02401 0.01627 -0.0961 0.1322 0.3695
10.750 1.2476 0.02534 0.01756 -0.0939 0.1196 0.3717
11.000 1.2531 0.02673 0.01893 -0.0919 0.1087 0.3736
11.250 1.2589 0.02818 0.02037 -0.0901 0.0994 0.3753
11.500 1.2641 0.02977 0.02198 -0.0885 0.0916 0.3777
11.750 1.2679 0.03156 0.02378 -0.0869 0.0841 0.3800
12.000 1.2729 0.03337 0.02563 -0.0857 0.0778 0.3824
12.250 1.2771 0.03534 0.02763 -0.0846 0.0723 0.3849
12.500 1.2803 0.03749 0.02981 -0.0837 0.0674 0.3875
12.750 1.2847 0.03964 0.03200 -0.0829 0.0632 0.3901
13.000 1.2868 0.04209 0.03448 -0.0823 0.0592 0.3922
13.250 1.2906 0.04447 0.03692 -0.0818 0.0558 0.3946
13.500 1.2924 0.04715 0.03965 -0.0815 0.0522 0.3973
13.750 1.2955 0.04978 0.04235 -0.0814 0.0493 0.4000
14.000 1.2971 0.05262 0.04524 -0.0813 0.0463 0.4027
14.250 1.2992 0.05547 0.04814 -0.0813 0.0438 0.4052
14.500 1.3011 0.05841 0.05114 -0.0814 0.0414 0.4077
14.750 1.3022 0.06150 0.05428 -0.0816 0.0394 0.4099
15.000 1.3053 0.06442 0.05726 -0.0819 0.0374 0.4121
15.250 1.3071 0.06756 0.06046 -0.0823 0.0355 0.4148
15.500 1.3090 0.07074 0.06372 -0.0828 0.0340 0.4177
15.750 1.3121 0.07381 0.06685 -0.0832 0.0323 0.4207
16.000 1.3136 0.07715 0.07024 -0.0839 0.0308 0.4235
16.250 1.3162 0.08036 0.07351 -0.0845 0.0295 0.4265
16.500 1.3189 0.08358 0.07679 -0.0851 0.0281 0.4292
16.750 1.3208 0.08699 0.08026 -0.0860 0.0268 0.4322
17.000 1.3236 0.09032 0.08367 -0.0868 0.0258 0.4360
17.250 1.3269 0.09359 0.08702 -0.0877 0.0247 0.4398
17.500 1.3291 0.09702 0.09051 -0.0886 0.0237 0.4437
17.750 1.3311 0.10049 0.09403 -0.0896 0.0228 0.4472
18.000 1.3338 0.10394 0.09756 -0.0907 0.0220 0.4506
18.250 1.3377 0.10720 0.10091 -0.0918 0.0213 0.4549
18.500 1.3399 0.11075 0.10453 -0.0930 0.0205 0.4592
18.750 1.3419 0.11431 0.10815 -0.0943 0.0198 0.4636
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