NREL's S801 Airfoil (s801-nr) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NREL's S801 Airfoil (s801-nr) Reynolds number: 200,000 Max Cl/Cd: 80.22 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s801-nr-200000-n5.txt Download as CSV file: xf-s801-nr-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NREL's S801 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
------ -------- --------- --------- -------- -------- --------
-10.250 -0.3608 0.07544 0.07185 -0.0823 0.9761 0.0190
-9.750 -0.4110 0.05164 0.04772 -0.1048 0.9418 0.0184
-9.500 -0.4255 0.04536 0.04109 -0.1107 0.9248 0.0184
-9.250 -0.4275 0.03872 0.03382 -0.1162 0.9113 0.0186
-9.000 -0.4142 0.03396 0.02841 -0.1197 0.9016 0.0188
-8.750 -0.3939 0.03083 0.02482 -0.1219 0.8920 0.0194
-8.500 -0.3667 0.02921 0.02305 -0.1238 0.8836 0.0201
-8.250 -0.3385 0.02761 0.02121 -0.1257 0.8754 0.0209
-8.000 -0.3134 0.02582 0.01909 -0.1266 0.8667 0.0216
-7.750 -0.2861 0.02404 0.01696 -0.1277 0.8591 0.0221
-7.500 -0.2612 0.02263 0.01526 -0.1279 0.8510 0.0227
-7.250 -0.2338 0.02139 0.01374 -0.1283 0.8440 0.0234
-7.000 -0.2082 0.02047 0.01259 -0.1283 0.8368 0.0240
-6.750 -0.1831 0.01944 0.01151 -0.1285 0.8300 0.0250
-6.500 -0.1572 0.01878 0.01078 -0.1286 0.8237 0.0263
-6.250 -0.1324 0.01809 0.01000 -0.1284 0.8170 0.0272
-6.000 -0.1061 0.01741 0.00920 -0.1284 0.8118 0.0281
-5.750 -0.0818 0.01683 0.00853 -0.1281 0.8060 0.0290
-5.500 -0.0567 0.01626 0.00788 -0.1280 0.8008 0.0301
-5.250 -0.0303 0.01573 0.00730 -0.1282 0.7965 0.0318
-5.000 -0.0046 0.01536 0.00687 -0.1281 0.7919 0.0345
-4.750 0.0213 0.01498 0.00642 -0.1280 0.7872 0.0371
-4.500 0.0482 0.01457 0.00598 -0.1282 0.7830 0.0410
-4.250 0.0760 0.01419 0.00555 -0.1285 0.7795 0.0489
-4.000 0.1017 0.01380 0.00524 -0.1285 0.7749 0.0691
-3.750 0.1281 0.01338 0.00499 -0.1287 0.7709 0.1108
-3.500 0.1556 0.01298 0.00476 -0.1292 0.7676 0.1630
-3.250 0.1839 0.01253 0.00455 -0.1299 0.7648 0.2387
-3.000 0.2106 0.01185 0.00441 -0.1307 0.7615 0.3728
-2.750 0.2359 0.01126 0.00447 -0.1307 0.7579 0.5283
-2.500 0.2590 0.01133 0.00488 -0.1292 0.7546 0.6264
-2.250 0.2862 0.01152 0.00504 -0.1288 0.7515 0.6711
-2.000 0.3147 0.01171 0.00514 -0.1287 0.7490 0.6954
-1.750 0.3415 0.01189 0.00526 -0.1284 0.7461 0.7117
-1.500 0.3681 0.01206 0.00539 -0.1281 0.7431 0.7253
-1.250 0.3957 0.01221 0.00547 -0.1280 0.7402 0.7374
-1.000 0.4213 0.01238 0.00561 -0.1273 0.7375 0.7454
-0.750 0.4495 0.01251 0.00567 -0.1273 0.7350 0.7549
-0.500 0.4762 0.01266 0.00578 -0.1268 0.7328 0.7621
-0.250 0.5026 0.01278 0.00589 -0.1266 0.7299 0.7701
0.000 0.5269 0.01291 0.00604 -0.1258 0.7269 0.7759
0.250 0.5546 0.01302 0.00612 -0.1259 0.7240 0.7831
0.500 0.5810 0.01311 0.00620 -0.1255 0.7215 0.7876
0.750 0.6085 0.01319 0.00626 -0.1255 0.7192 0.7917
1.000 0.6373 0.01328 0.00632 -0.1258 0.7168 0.7959
1.250 0.6641 0.01337 0.00644 -0.1259 0.7133 0.8000
1.500 0.6895 0.01345 0.00654 -0.1254 0.7099 0.8025
1.750 0.7166 0.01351 0.00662 -0.1254 0.7067 0.8052
2.000 0.7454 0.01357 0.00667 -0.1257 0.7037 0.8078
2.250 0.7735 0.01365 0.00675 -0.1259 0.7004 0.8105
2.500 0.7996 0.01374 0.00689 -0.1258 0.6958 0.8133
2.750 0.8274 0.01379 0.00696 -0.1259 0.6911 0.8155
3.000 0.8562 0.01379 0.00695 -0.1261 0.6867 0.8173
3.250 0.8791 0.01385 0.00709 -0.1252 0.6800 0.8194
3.500 0.9062 0.01384 0.00711 -0.1251 0.6736 0.8213
3.750 0.9314 0.01386 0.00717 -0.1246 0.6662 0.8237
4.000 0.9576 0.01385 0.00718 -0.1243 0.6580 0.8261
4.250 0.9825 0.01388 0.00726 -0.1238 0.6490 0.8284
4.500 1.0098 0.01386 0.00724 -0.1237 0.6400 0.8303
4.750 1.0310 0.01389 0.00738 -0.1225 0.6293 0.8322
5.000 1.0540 0.01392 0.00747 -0.1215 0.6186 0.8344
5.250 1.0769 0.01395 0.00757 -0.1206 0.6063 0.8368
5.500 1.0985 0.01401 0.00768 -0.1194 0.5910 0.8391
5.750 1.1193 0.01408 0.00779 -0.1181 0.5706 0.8415
6.000 1.1391 0.01420 0.00787 -0.1165 0.5414 0.8440
6.250 1.1530 0.01444 0.00794 -0.1138 0.4966 0.8465
6.500 1.1589 0.01501 0.00822 -0.1097 0.4464 0.8496
6.750 1.1602 0.01575 0.00871 -0.1050 0.4000 0.8533
7.000 1.1625 0.01663 0.00937 -0.1007 0.3568 0.8569
7.250 1.1657 0.01758 0.01014 -0.0968 0.3175 0.8604
7.500 1.1691 0.01854 0.01095 -0.0931 0.2822 0.8639
7.750 1.1738 0.01954 0.01183 -0.0898 0.2506 0.8677
8.000 1.1798 0.02058 0.01275 -0.0869 0.2223 0.8720
8.250 1.1862 0.02163 0.01371 -0.0842 0.1979 0.8765
8.500 1.1935 0.02266 0.01468 -0.0817 0.1767 0.8814
8.750 1.2016 0.02376 0.01572 -0.0796 0.1584 0.8869
9.000 1.2099 0.02486 0.01680 -0.0775 0.1423 0.8924
9.250 1.2186 0.02596 0.01789 -0.0755 0.1283 0.8992
9.500 1.2279 0.02705 0.01898 -0.0737 0.1164 0.9076
9.750 1.2372 0.02811 0.02009 -0.0719 0.1061 0.9203
10.000 1.2435 0.02912 0.02116 -0.0697 0.0981 1.0000
10.250 1.2550 0.03045 0.02249 -0.0687 0.0898 1.0000
10.500 1.2674 0.03173 0.02382 -0.0678 0.0831 1.0000
10.750 1.2774 0.03320 0.02528 -0.0668 0.0769 1.0000
11.000 1.2895 0.03454 0.02668 -0.0659 0.0717 1.0000
11.250 1.2999 0.03602 0.02819 -0.0650 0.0671 1.0000
11.500 1.3087 0.03765 0.02985 -0.0640 0.0634 1.0000
11.750 1.3199 0.03910 0.03141 -0.0631 0.0599 1.0000
12.000 1.3294 0.04072 0.03309 -0.0623 0.0566 1.0000
12.250 1.3354 0.04268 0.03506 -0.0613 0.0537 1.0000
12.500 1.3459 0.04426 0.03676 -0.0606 0.0514 1.0000
12.750 1.3552 0.04599 0.03858 -0.0599 0.0490 1.0000
13.000 1.3632 0.04786 0.04053 -0.0592 0.0467 1.0000
13.250 1.3686 0.05003 0.04273 -0.0585 0.0448 1.0000
13.500 1.3756 0.05208 0.04489 -0.0578 0.0430 1.0000
13.750 1.3839 0.05403 0.04697 -0.0573 0.0413 1.0000
14.000 1.3911 0.05613 0.04918 -0.0568 0.0396 1.0000
14.250 1.3971 0.05840 0.05154 -0.0565 0.0380 1.0000
14.500 1.4006 0.06097 0.05416 -0.0561 0.0366 1.0000
14.750 1.4048 0.06354 0.05682 -0.0558 0.0353 1.0000
15.000 1.4111 0.06592 0.05937 -0.0556 0.0339 1.0000
15.250 1.4160 0.06850 0.06210 -0.0556 0.0324 1.0000
15.500 1.4197 0.07127 0.06498 -0.0557 0.0310 1.0000
15.750 1.4211 0.07437 0.06815 -0.0560 0.0298 1.0000
16.000 1.4212 0.07772 0.07159 -0.0563 0.0287 1.0000
16.250 1.4243 0.08078 0.07484 -0.0567 0.0275 1.0000
16.500 1.4257 0.08412 0.07834 -0.0573 0.0262 1.0000
16.750 1.4259 0.08770 0.08206 -0.0582 0.0252 1.0000
17.000 1.4245 0.09157 0.08605 -0.0592 0.0243 1.0000
17.250 1.4210 0.09587 0.09043 -0.0606 0.0235 1.0000
17.500 1.4177 0.10021 0.09492 -0.0619 0.0227 1.0000
17.750 1.4151 0.10457 0.09948 -0.0635 0.0218 1.0000
18.000 1.4113 0.10921 0.10431 -0.0653 0.0210 1.0000
18.250 1.4066 0.11409 0.10936 -0.0675 0.0203 1.0000
18.500 1.4010 0.11923 0.11463 -0.0700 0.0196 1.0000
18.750 1.3944 0.12464 0.12017 -0.0728 0.0191 1.0000
19.000 1.3869 0.13029 0.12593 -0.0759 0.0186 1.0000
19.250 1.3787 0.13619 0.13195 -0.0792 0.0181 1.0000
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