SOMERS S102 AIRFOIL (BLUNT) (s102b-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: SOMERS S102 AIRFOIL (BLUNT) (s102b-il) Reynolds number: 50,000 Max Cl/Cd: 28.11 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s102b-il-50000-n5.txt Download as CSV file: xf-s102b-il-50000-n5.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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.4430 0.10428 0.09711 -0.0483 1.0000 0.0424
-10.750 -0.4518 0.09728 0.09017 -0.0525 1.0000 0.0411
-10.250 -0.5146 0.08141 0.07413 -0.0632 1.0000 0.0381
-10.000 -0.5276 0.07761 0.07032 -0.0639 1.0000 0.0378
-9.750 -0.5436 0.07430 0.06701 -0.0636 1.0000 0.0376
-9.500 -0.5630 0.07170 0.06441 -0.0619 1.0000 0.0375
-9.250 -0.5827 0.06940 0.06210 -0.0594 1.0000 0.0373
-9.000 -0.6004 0.06720 0.05985 -0.0566 1.0000 0.0371
-8.750 -0.6173 0.06516 0.05774 -0.0533 1.0000 0.0370
-8.500 -0.6326 0.06318 0.05566 -0.0498 1.0000 0.0369
-8.250 -0.6453 0.06115 0.05349 -0.0465 1.0000 0.0367
-8.000 -0.6479 0.05841 0.05050 -0.0451 0.9977 0.0366
-7.750 -0.6289 0.05433 0.04595 -0.0475 0.9895 0.0365
-7.500 -0.6059 0.05056 0.04167 -0.0497 0.9824 0.0366
-7.250 -0.5821 0.04731 0.03794 -0.0510 0.9747 0.0368
-7.000 -0.5523 0.04428 0.03440 -0.0526 0.9691 0.0374
-6.750 -0.5256 0.04186 0.03159 -0.0531 0.9619 0.0386
-6.500 -0.4943 0.03995 0.02961 -0.0546 0.9569 0.0413
-6.250 -0.4641 0.03828 0.02767 -0.0549 0.9514 0.0441
-6.000 -0.4316 0.03689 0.02598 -0.0544 0.9465 0.0464
-5.750 -0.3983 0.03576 0.02494 -0.0543 0.9428 0.0507
-5.500 -0.3650 0.03487 0.02388 -0.0542 0.9390 0.0569
-5.250 -0.3454 0.03397 0.02301 -0.0529 0.9315 0.0627
-5.000 -0.3196 0.03286 0.02188 -0.0533 0.9261 0.0730
-4.750 -0.3012 0.03174 0.02078 -0.0529 0.9192 0.0870
-4.500 -0.2825 0.03019 0.01946 -0.0533 0.9127 0.1166
-4.250 -0.2775 0.02915 0.02134 -0.0479 0.9080 0.5169
-4.000 -0.2625 0.03060 0.02233 -0.0454 0.8992 0.6271
-3.750 -0.2473 0.03370 0.02537 -0.0358 0.8949 0.6878
-3.500 -0.2236 0.03565 0.02715 -0.0286 0.8924 0.7339
-3.250 -0.2124 0.03549 0.02676 -0.0266 0.8851 0.7442
-3.000 -0.1862 0.03518 0.02617 -0.0269 0.8806 0.7481
-2.750 -0.1557 0.03485 0.02556 -0.0281 0.8771 0.7518
-2.500 -0.1404 0.03461 0.02515 -0.0272 0.8706 0.7561
-2.250 -0.1177 0.03431 0.02461 -0.0280 0.8656 0.7602
-2.000 -0.0890 0.03407 0.02418 -0.0291 0.8622 0.7626
-1.750 -0.0665 0.03394 0.02389 -0.0291 0.8579 0.7652
-1.500 -0.0482 0.03385 0.02367 -0.0286 0.8522 0.7679
-1.250 -0.0208 0.03372 0.02338 -0.0297 0.8483 0.7704
-1.000 0.0100 0.03359 0.02310 -0.0315 0.8454 0.7729
-0.750 0.0279 0.03364 0.02304 -0.0314 0.8401 0.7754
-0.500 0.0504 0.03366 0.02298 -0.0318 0.8352 0.7774
-0.250 0.0786 0.03367 0.02290 -0.0327 0.8318 0.7793
0.000 0.1106 0.03367 0.02281 -0.0343 0.8291 0.7810
0.250 0.1242 0.03392 0.02302 -0.0333 0.8230 0.7830
0.500 0.1485 0.03408 0.02313 -0.0339 0.8183 0.7851
0.750 0.1797 0.03419 0.02319 -0.0356 0.8149 0.7873
1.000 0.2122 0.03432 0.02328 -0.0374 0.8116 0.7894
1.250 0.2276 0.03474 0.02370 -0.0371 0.8047 0.7916
1.500 0.2570 0.03494 0.02389 -0.0383 0.8003 0.7931
1.750 0.2911 0.03506 0.02402 -0.0400 0.7970 0.7948
2.000 0.3048 0.03555 0.02455 -0.0390 0.7893 0.7971
2.250 0.3342 0.03578 0.02482 -0.0401 0.7841 0.7995
2.500 0.3722 0.03585 0.02493 -0.0422 0.7804 0.8017
2.750 0.3867 0.03642 0.02556 -0.0415 0.7707 0.8043
3.000 0.4260 0.03641 0.02561 -0.0438 0.7655 0.8063
3.250 0.4500 0.03654 0.02581 -0.0437 0.7536 0.8084
3.500 0.4864 0.03582 0.02517 -0.0440 0.7391 0.8104
3.750 0.5255 0.03464 0.02405 -0.0439 0.7222 0.8128
4.000 0.5615 0.03355 0.02306 -0.0436 0.7055 0.8155
4.250 0.5925 0.03292 0.02252 -0.0433 0.6908 0.8186
4.500 0.6234 0.03238 0.02208 -0.0432 0.6765 0.8218
4.750 0.6518 0.03184 0.02170 -0.0426 0.6615 0.8248
5.000 0.6770 0.03137 0.02137 -0.0416 0.6449 0.8277
5.250 0.7011 0.03090 0.02105 -0.0404 0.6257 0.8310
5.500 0.7267 0.03032 0.02063 -0.0394 0.6043 0.8347
5.750 0.7392 0.03046 0.02096 -0.0375 0.5743 0.8391
6.000 0.7421 0.03101 0.02171 -0.0345 0.5353 0.8437
6.250 0.7678 0.03017 0.02088 -0.0329 0.4773 0.8487
6.500 0.8081 0.02875 0.01869 -0.0316 0.3909 0.8533
6.750 0.8182 0.02963 0.01911 -0.0291 0.3408 0.8585
7.000 0.8289 0.03078 0.02001 -0.0274 0.3087 0.8645
7.250 0.8431 0.03188 0.02097 -0.0262 0.2861 0.8708
7.500 0.8586 0.03283 0.02185 -0.0250 0.2697 0.8777
7.750 0.8770 0.03373 0.02272 -0.0243 0.2559 0.8858
8.000 0.8961 0.03451 0.02351 -0.0234 0.2444 0.8956
8.250 0.9173 0.03522 0.02424 -0.0227 0.2342 0.9079
8.500 0.9426 0.03587 0.02503 -0.0225 0.2252 0.9250
9.000 1.0036 0.03733 0.02671 -0.0242 0.2086 1.0000
9.250 1.0421 0.03835 0.02769 -0.0264 0.2008 1.0000
9.500 1.0756 0.03961 0.02921 -0.0280 0.1939 1.0000
9.750 1.1140 0.04089 0.03047 -0.0303 0.1873 1.0000
10.000 1.1392 0.04241 0.03228 -0.0310 0.1811 1.0000
10.250 1.1666 0.04391 0.03395 -0.0320 0.1753 1.0000
10.500 1.1966 0.04550 0.03558 -0.0331 0.1701 1.0000
10.750 1.2105 0.04737 0.03783 -0.0325 0.1648 1.0000
11.000 1.2308 0.04904 0.03964 -0.0325 0.1597 1.0000
11.250 1.2531 0.05086 0.04155 -0.0328 0.1551 1.0000
11.500 1.2542 0.05311 0.04424 -0.0308 0.1509 1.0000
11.750 1.2619 0.05514 0.04649 -0.0296 0.1464 1.0000
12.000 1.2862 0.05673 0.04806 -0.0299 0.1418 1.0000
12.250 1.2746 0.05966 0.05140 -0.0272 0.1388 1.0000
12.500 1.2627 0.06276 0.05486 -0.0251 0.1356 1.0000
12.750 1.2558 0.06569 0.05803 -0.0236 0.1323 1.0000
13.000 1.2686 0.06746 0.05984 -0.0231 0.1283 1.0000
13.250 1.2570 0.07102 0.06363 -0.0219 0.1258 1.0000
13.500 1.2242 0.07644 0.06940 -0.0210 0.1246 1.0000
13.750 1.1862 0.08309 0.07636 -0.0215 0.1237 1.0000
14.000 1.1379 0.09197 0.08549 -0.0238 0.1235 1.0000
14.250 1.0682 0.10590 0.09960 -0.0303 0.1243 1.0000
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