NREL's S818 Airfoil (s818-nr) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NREL's S818 Airfoil (s818-nr) Reynolds number: 500,000 Max Cl/Cd: 81.95 at α=9° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s818-nr-500000-n5.txt Download as CSV file: xf-s818-nr-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NREL's S818 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
------ -------- --------- --------- -------- -------- --------
-14.250 -0.6674 0.09069 0.08584 -0.0464 0.9964 0.0653
-14.000 -0.6587 0.08870 0.08389 -0.0472 0.9959 0.0719
-13.750 -0.6505 0.08643 0.08166 -0.0484 0.9952 0.0794
-13.500 -0.6422 0.08387 0.07915 -0.0501 0.9943 0.0887
-13.250 -0.6354 0.08043 0.07580 -0.0530 0.9931 0.1035
-13.000 -0.6412 0.07574 0.07129 -0.0559 0.9911 0.1301
-12.750 -0.6672 0.06881 0.06456 -0.0594 0.9880 0.1659
-12.500 -0.7118 0.05958 0.05552 -0.0644 0.9847 0.2008
-11.750 -0.8054 0.03824 0.03436 -0.0773 0.9709 0.2801
-11.500 -0.8569 0.03122 0.02714 -0.0787 0.9640 0.2774
-11.250 -0.8851 0.02646 0.02228 -0.0798 0.9561 0.2841
-11.000 -0.9176 0.02306 0.01878 -0.0770 0.9448 0.2876
-10.750 -0.8983 0.02043 0.01601 -0.0816 0.9408 0.2958
-10.500 -0.8916 0.01858 0.01410 -0.0825 0.9315 0.3010
-10.000 -0.8348 0.01666 0.01195 -0.0877 0.9209 0.3100
-9.750 -0.8073 0.01634 0.01161 -0.0885 0.9139 0.3131
-9.500 -0.7822 0.01606 0.01128 -0.0888 0.9054 0.3164
-9.250 -0.7534 0.01572 0.01085 -0.0898 0.8977 0.3194
-9.000 -0.7246 0.01538 0.01038 -0.0909 0.8891 0.3218
-8.750 -0.6895 0.01502 0.00995 -0.0929 0.8821 0.3237
-8.500 -0.6532 0.01475 0.00967 -0.0948 0.8742 0.3253
-8.250 -0.6085 0.01454 0.00942 -0.0982 0.8665 0.3270
-8.000 -0.5563 0.01434 0.00915 -0.1032 0.8555 0.3287
-7.750 -0.4906 0.01407 0.00874 -0.1110 0.8392 0.3297
-7.500 -0.4278 0.01382 0.00827 -0.1185 0.8110 0.3300
-7.250 -0.3935 0.01368 0.00792 -0.1203 0.7797 0.3304
-7.000 -0.3675 0.01357 0.00764 -0.1205 0.7516 0.3307
-6.750 -0.3433 0.01348 0.00738 -0.1202 0.7267 0.3310
-6.500 -0.3193 0.01339 0.00715 -0.1199 0.7040 0.3314
-6.250 -0.2951 0.01331 0.00693 -0.1196 0.6835 0.3318
-6.000 -0.2705 0.01323 0.00672 -0.1194 0.6647 0.3323
-5.750 -0.2454 0.01314 0.00652 -0.1193 0.6473 0.3327
-5.500 -0.2199 0.01306 0.00632 -0.1192 0.6310 0.3331
-5.250 -0.1941 0.01299 0.00614 -0.1192 0.6151 0.3336
-5.000 -0.1679 0.01292 0.00596 -0.1192 0.6002 0.3339
-4.750 -0.1415 0.01285 0.00580 -0.1193 0.5861 0.3343
-4.500 -0.1149 0.01280 0.00564 -0.1194 0.5731 0.3347
-4.250 -0.0874 0.01273 0.00550 -0.1196 0.5612 0.3351
-4.000 -0.0599 0.01267 0.00536 -0.1199 0.5507 0.3355
-3.500 -0.0043 0.01258 0.00512 -0.1204 0.5310 0.3363
-3.250 0.0232 0.01256 0.00501 -0.1206 0.5219 0.3367
-3.000 0.0517 0.01251 0.00492 -0.1210 0.5136 0.3370
-2.500 0.1081 0.01244 0.00474 -0.1216 0.4984 0.3379
-2.250 0.1361 0.01239 0.00466 -0.1219 0.4911 0.3386
-2.000 0.1643 0.01236 0.00461 -0.1222 0.4850 0.3393
-1.750 0.1928 0.01234 0.00456 -0.1226 0.4784 0.3400
-1.500 0.2206 0.01234 0.00453 -0.1228 0.4721 0.3407
-1.250 0.2491 0.01233 0.00450 -0.1231 0.4666 0.3413
-1.000 0.2775 0.01233 0.00449 -0.1234 0.4609 0.3420
-0.750 0.3054 0.01236 0.00448 -0.1236 0.4559 0.3427
-0.500 0.3337 0.01237 0.00448 -0.1239 0.4517 0.3434
-0.250 0.3624 0.01237 0.00448 -0.1242 0.4475 0.3442
0.000 0.3907 0.01239 0.00449 -0.1245 0.4433 0.3450
0.250 0.4187 0.01243 0.00451 -0.1247 0.4395 0.3458
0.500 0.4466 0.01248 0.00454 -0.1249 0.4360 0.3466
0.750 0.4754 0.01250 0.00456 -0.1252 0.4330 0.3474
1.000 0.5039 0.01252 0.00459 -0.1255 0.4298 0.3483
1.250 0.5320 0.01257 0.00463 -0.1257 0.4266 0.3491
1.500 0.5599 0.01263 0.00468 -0.1258 0.4237 0.3500
1.750 0.5876 0.01270 0.00474 -0.1259 0.4209 0.3508
2.000 0.6157 0.01276 0.00480 -0.1261 0.4185 0.3515
2.250 0.6442 0.01281 0.00486 -0.1264 0.4160 0.3522
2.500 0.6725 0.01285 0.00493 -0.1266 0.4134 0.3531
2.750 0.7008 0.01290 0.00501 -0.1269 0.4109 0.3543
3.000 0.7289 0.01297 0.00511 -0.1270 0.4087 0.3554
3.250 0.7567 0.01306 0.00521 -0.1272 0.4066 0.3566
3.500 0.7843 0.01316 0.00534 -0.1273 0.4046 0.3577
3.750 0.8120 0.01328 0.00547 -0.1274 0.4027 0.3589
4.000 0.8404 0.01335 0.00560 -0.1276 0.4012 0.3601
4.250 0.8685 0.01344 0.00573 -0.1278 0.3997 0.3615
4.500 0.8965 0.01354 0.00588 -0.1279 0.3980 0.3629
4.750 0.9242 0.01365 0.00603 -0.1280 0.3963 0.3643
5.000 0.9518 0.01377 0.00619 -0.1281 0.3946 0.3657
5.250 0.9790 0.01390 0.00635 -0.1281 0.3928 0.3669
5.500 1.0059 0.01405 0.00651 -0.1281 0.3909 0.3679
5.750 1.0332 0.01419 0.00669 -0.1281 0.3893 0.3694
6.000 1.0607 0.01434 0.00690 -0.1282 0.3877 0.3710
6.250 1.0883 0.01453 0.00712 -0.1283 0.3862 0.3725
6.500 1.1158 0.01466 0.00733 -0.1284 0.3850 0.3741
6.750 1.1427 0.01479 0.00755 -0.1283 0.3834 0.3757
7.000 1.1676 0.01490 0.00773 -0.1279 0.3793 0.3774
7.250 1.1883 0.01509 0.00790 -0.1267 0.3712 0.3790
7.500 1.2110 0.01522 0.00809 -0.1259 0.3630 0.3805
7.750 1.2341 0.01541 0.00830 -0.1252 0.3575 0.3821
8.000 1.2564 0.01566 0.00856 -0.1244 0.3532 0.3834
8.250 1.2815 0.01580 0.00879 -0.1240 0.3481 0.3850
8.500 1.3047 0.01600 0.00906 -0.1234 0.3414 0.3870
8.750 1.3264 0.01626 0.00936 -0.1225 0.3354 0.3889
9.000 1.3497 0.01647 0.00965 -0.1219 0.3277 0.3909
9.250 1.3696 0.01679 0.00999 -0.1207 0.3177 0.3931
9.500 1.3879 0.01719 0.01038 -0.1193 0.3017 0.3953
9.750 1.3985 0.01793 0.01099 -0.1169 0.2719 0.3972
10.000 1.3993 0.01923 0.01206 -0.1132 0.2335 0.3989
10.250 1.3993 0.02065 0.01333 -0.1096 0.2024 0.4002
10.500 1.4006 0.02207 0.01464 -0.1064 0.1772 0.4020
10.750 1.4025 0.02351 0.01602 -0.1035 0.1560 0.4039
11.000 1.4037 0.02506 0.01751 -0.1007 0.1384 0.4057
11.250 1.4055 0.02665 0.01907 -0.0982 0.1238 0.4075
11.500 1.4075 0.02831 0.02074 -0.0960 0.1115 0.4095
11.750 1.4096 0.03008 0.02251 -0.0940 0.1014 0.4114
12.000 1.4104 0.03205 0.02449 -0.0922 0.0927 0.4133
12.250 1.4103 0.03424 0.02670 -0.0906 0.0850 0.4150
12.500 1.4123 0.03640 0.02891 -0.0894 0.0791 0.4166
12.750 1.4113 0.03899 0.03154 -0.0884 0.0733 0.4186
13.000 1.4121 0.04154 0.03416 -0.0877 0.0686 0.4209
13.250 1.4107 0.04445 0.03713 -0.0871 0.0639 0.4231
13.500 1.4087 0.04756 0.04031 -0.0868 0.0601 0.4256
13.750 1.4074 0.05069 0.04351 -0.0866 0.0563 0.4280
14.000 1.4037 0.05420 0.04709 -0.0866 0.0529 0.4304
14.250 1.4014 0.05766 0.05061 -0.0868 0.0501 0.4326
14.500 1.3992 0.06121 0.05425 -0.0871 0.0473 0.4350
14.750 1.3951 0.06506 0.05816 -0.0876 0.0447 0.4376
15.000 1.3926 0.06879 0.06198 -0.0881 0.0425 0.4402
15.250 1.3911 0.07246 0.06573 -0.0887 0.0404 0.4430
15.500 1.3885 0.07633 0.06966 -0.0894 0.0383 0.4457
15.750 1.3854 0.08028 0.07368 -0.0902 0.0363 0.4482
16.000 1.3856 0.08389 0.07736 -0.0910 0.0348 0.4508
16.250 1.3852 0.08764 0.08119 -0.0919 0.0331 0.4539
16.500 1.3843 0.09146 0.08508 -0.0929 0.0314 0.4571
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