SOMERS S102 AIRFOIL (BLUNT) (s102b-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: SOMERS S102 AIRFOIL (BLUNT) (s102b-il) Reynolds number: 100,000 Max Cl/Cd: 42.63 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s102b-il-100000.txt Download as CSV file: xf-s102b-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: SOMERS S102 AIRFOIL (BLUNT)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.4189 0.10861 0.10376 -0.0411 1.0000 0.1194
-10.250 -0.4794 0.10072 0.09603 -0.0540 1.0000 0.1231
-10.000 -0.5220 0.09596 0.09132 -0.0586 1.0000 0.1234
-9.500 -0.4964 0.08872 0.08422 -0.0563 1.0000 0.1379
-9.250 -0.5374 0.08590 0.08150 -0.0556 1.0000 0.1380
-9.000 -0.5735 0.08438 0.08009 -0.0520 1.0000 0.1380
-8.750 -0.6081 0.08348 0.07925 -0.0472 1.0000 0.1380
-8.500 -0.6428 0.08266 0.07845 -0.0427 1.0000 0.1381
-8.250 -0.6797 0.08185 0.07754 -0.0392 1.0000 0.1384
-7.250 -0.6010 0.06368 0.05954 -0.0479 0.9814 0.1916
-6.750 -0.5540 0.04503 0.03801 -0.0569 0.9654 0.0657
-6.500 -0.5234 0.04059 0.03287 -0.0576 0.9603 0.0547
-6.250 -0.4888 0.03708 0.02902 -0.0595 0.9568 0.0518
-6.000 -0.4584 0.03480 0.02639 -0.0603 0.9521 0.0516
-5.750 -0.4299 0.03308 0.02438 -0.0606 0.9467 0.0530
-5.500 -0.3954 0.03135 0.02240 -0.0616 0.9432 0.0543
-5.250 -0.3579 0.02975 0.02059 -0.0628 0.9407 0.0555
-5.000 -0.3349 0.02836 0.01925 -0.0616 0.9360 0.0577
-4.750 -0.3105 0.02740 0.01841 -0.0613 0.9310 0.0640
-4.500 -0.2806 0.02622 0.01738 -0.0618 0.9273 0.0737
-4.250 -0.2462 0.02496 0.01626 -0.0636 0.9245 0.0975
-4.000 -0.2364 0.02335 0.01727 -0.0618 0.9186 0.6039
-3.750 -0.2347 0.02679 0.02080 -0.0511 0.9130 0.6584
-3.500 -0.2224 0.02919 0.02318 -0.0431 0.9095 0.6941
-3.250 -0.2211 0.03072 0.02470 -0.0345 0.9043 0.7188
-3.000 -0.2203 0.03207 0.02603 -0.0256 0.8995 0.7485
-2.750 -0.2104 0.03339 0.02732 -0.0166 0.8968 0.7849
-2.500 -0.1882 0.03366 0.02744 -0.0146 0.8941 0.8071
-2.250 -0.1582 0.03337 0.02696 -0.0157 0.8915 0.8108
-2.000 -0.1615 0.03318 0.02672 -0.0119 0.8856 0.8138
-1.750 -0.1432 0.03299 0.02640 -0.0119 0.8822 0.8165
-1.500 -0.1157 0.03280 0.02608 -0.0136 0.8792 0.8187
-1.250 -0.0798 0.03266 0.02578 -0.0167 0.8766 0.8204
-1.000 -0.0707 0.03269 0.02573 -0.0159 0.8725 0.8221
-0.750 -0.0492 0.03271 0.02566 -0.0170 0.8686 0.8233
-0.500 -0.0223 0.03269 0.02555 -0.0182 0.8652 0.8243
-0.250 0.0099 0.03270 0.02548 -0.0202 0.8624 0.8255
0.000 0.0417 0.03281 0.02551 -0.0224 0.8594 0.8261
0.250 0.0548 0.03306 0.02573 -0.0219 0.8547 0.8274
0.500 0.0815 0.03324 0.02586 -0.0232 0.8504 0.8286
0.750 0.1175 0.03338 0.02596 -0.0260 0.8469 0.8292
1.000 0.1501 0.03363 0.02617 -0.0282 0.8429 0.8299
1.250 0.1673 0.03401 0.02655 -0.0283 0.8368 0.8313
1.500 0.2024 0.03421 0.02673 -0.0308 0.8319 0.8325
1.750 0.2417 0.03441 0.02691 -0.0337 0.8272 0.8333
2.000 0.2605 0.03484 0.02736 -0.0341 0.8190 0.8342
2.250 0.3095 0.03472 0.02724 -0.0379 0.8133 0.8351
2.500 0.3515 0.03409 0.02662 -0.0398 0.7982 0.8364
2.750 0.4320 0.03157 0.02410 -0.0447 0.7809 0.8376
3.000 0.4701 0.03074 0.02330 -0.0458 0.7672 0.8388
3.250 0.5007 0.03038 0.02300 -0.0461 0.7574 0.8398
3.500 0.5480 0.02912 0.02179 -0.0477 0.7504 0.8410
3.750 0.5758 0.02880 0.02156 -0.0476 0.7394 0.8424
4.000 0.6269 0.02713 0.01993 -0.0493 0.7329 0.8437
4.250 0.6543 0.02668 0.01959 -0.0489 0.7203 0.8458
4.500 0.6884 0.02582 0.01881 -0.0491 0.7085 0.8481
4.750 0.7280 0.02456 0.01761 -0.0496 0.6959 0.8503
5.000 0.7633 0.02345 0.01659 -0.0497 0.6794 0.8524
5.250 0.7957 0.02240 0.01561 -0.0495 0.6586 0.8544
5.500 0.8234 0.02127 0.01457 -0.0481 0.6318 0.8565
5.750 0.8426 0.02037 0.01376 -0.0455 0.5816 0.8591
6.000 0.8530 0.02001 0.01246 -0.0411 0.4202 0.8619
6.250 0.8565 0.02157 0.01320 -0.0378 0.3373 0.8650
6.500 0.8733 0.02271 0.01398 -0.0368 0.3020 0.8686
6.750 0.8935 0.02358 0.01461 -0.0360 0.2817 0.8721
7.000 0.9172 0.02436 0.01526 -0.0357 0.2662 0.8760
7.250 0.9436 0.02516 0.01599 -0.0360 0.2532 0.8801
7.500 0.9729 0.02604 0.01684 -0.0369 0.2426 0.8843
7.750 1.0010 0.02689 0.01759 -0.0373 0.2343 0.8885
8.000 1.0276 0.02771 0.01854 -0.0376 0.2266 0.8937
8.250 1.0583 0.02869 0.01945 -0.0387 0.2190 0.8994
8.500 1.0829 0.02958 0.02051 -0.0385 0.2129 0.9057
8.750 1.1093 0.03051 0.02155 -0.0388 0.2068 0.9137
9.000 1.1372 0.03171 0.02271 -0.0392 0.2011 0.9229
9.250 1.1563 0.03254 0.02388 -0.0382 0.1957 0.9352
9.500 1.1807 0.03353 0.02501 -0.0382 0.1903 0.9528
9.750 1.2123 0.03510 0.02670 -0.0400 0.1846 1.0000
10.000 1.2388 0.03657 0.02847 -0.0412 0.1786 1.0000
10.250 1.2717 0.03822 0.03011 -0.0434 0.1727 1.0000
10.500 1.2929 0.04018 0.03243 -0.0440 0.1673 1.0000
10.750 1.3168 0.04180 0.03427 -0.0447 0.1614 1.0000
11.000 1.3453 0.04396 0.03638 -0.0464 0.1556 1.0000
11.250 1.3519 0.04588 0.03880 -0.0446 0.1506 1.0000
11.500 1.3735 0.04733 0.04029 -0.0449 0.1447 1.0000
11.750 1.3873 0.04973 0.04284 -0.0443 0.1398 1.0000
12.000 1.3832 0.05205 0.04560 -0.0413 0.1355 1.0000
12.250 1.4029 0.05315 0.04668 -0.0411 0.1297 1.0000
12.500 1.4071 0.05577 0.04946 -0.0395 0.1255 1.0000
12.750 1.3860 0.05851 0.05262 -0.0349 0.1230 1.0000
13.000 1.3700 0.06120 0.05558 -0.0314 0.1201 1.0000
13.250 1.4128 0.06155 0.05560 -0.0333 0.1127 1.0000
13.500 1.3811 0.06493 0.05938 -0.0290 0.1117 1.0000
13.750 1.3481 0.06920 0.06400 -0.0259 0.1107 1.0000
14.000 1.3127 0.07438 0.06949 -0.0241 0.1102 1.0000
14.250 1.2733 0.08073 0.07612 -0.0237 0.1101 1.0000
14.500 1.2296 0.08848 0.08411 -0.0247 0.1107 1.0000
14.750 1.1825 0.09786 0.09367 -0.0276 0.1116 1.0000
15.000 1.1336 0.10917 0.10508 -0.0324 0.1125 1.0000
|
Polar data table (+)
Polar graphs
<< Back to SOMERS S102 AIRFOIL (BLUNT) (s102b-il)