SOMERS S102 AIRFOIL (SHARP) (s102s-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: SOMERS S102 AIRFOIL (SHARP) (s102s-il) Reynolds number: 100,000 Max Cl/Cd: 40.53 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s102s-il-100000.txt Download as CSV file: xf-s102s-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: SOMERS S102 AIRFOIL (SHARP)
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
------ -------- --------- --------- -------- -------- --------
-11.000 -0.3850 0.11267 0.10767 -0.0467 1.0000 0.1115
-10.750 -0.3918 0.10922 0.10430 -0.0481 1.0000 0.1172
-10.500 -0.4492 0.10314 0.09842 -0.0569 1.0000 0.1200
-10.250 -0.4016 0.10168 0.09691 -0.0493 1.0000 0.1244
-10.000 -0.4004 0.09888 0.09416 -0.0487 1.0000 0.1296
-9.750 -0.4550 0.09287 0.08835 -0.0551 1.0000 0.1346
-9.500 -0.4291 0.09089 0.08639 -0.0504 1.0000 0.1395
-9.250 -0.4321 0.08840 0.08398 -0.0491 1.0000 0.1451
-9.000 -0.4756 0.08388 0.07961 -0.0506 1.0000 0.1480
-8.750 -0.4090 0.08844 0.08476 -0.0317 1.0000 0.1595
-8.500 -0.4517 0.08044 0.07682 -0.0385 0.9963 0.1645
-8.250 -0.6822 0.08222 0.07777 -0.0416 0.9944 0.1355
-8.000 -0.6235 0.07747 0.07358 -0.0368 0.9984 0.1462
-7.750 -0.6204 0.07220 0.06821 -0.0421 0.9898 0.1564
-6.750 -0.5672 0.04726 0.04069 -0.0552 0.9584 0.0739
-6.500 -0.5488 0.04324 0.03542 -0.0527 0.9510 0.0542
-6.250 -0.5202 0.04051 0.03236 -0.0536 0.9467 0.0538
-6.000 -0.4871 0.03758 0.02915 -0.0551 0.9439 0.0534
-5.750 -0.4681 0.03561 0.02694 -0.0538 0.9380 0.0531
-5.500 -0.4389 0.03350 0.02461 -0.0539 0.9338 0.0528
-5.250 -0.4039 0.03179 0.02268 -0.0547 0.9307 0.0532
-5.000 -0.3701 0.03004 0.02092 -0.0553 0.9281 0.0554
-4.750 -0.3573 0.02927 0.02024 -0.0530 0.9224 0.0588
-4.500 -0.3317 0.02862 0.01951 -0.0526 0.9185 0.0650
-4.250 -0.3057 0.02738 0.01851 -0.0525 0.9155 0.0746
-4.000 -0.2863 0.02661 0.01781 -0.0514 0.9113 0.0912
-3.750 -0.2735 0.02506 0.01669 -0.0502 0.9061 0.1439
-3.500 -0.2765 0.02706 0.02106 -0.0402 0.9015 0.6534
-3.250 -0.2631 0.02967 0.02366 -0.0325 0.8986 0.6956
-3.000 -0.2688 0.03090 0.02490 -0.0242 0.8935 0.7150
-2.750 -0.2642 0.03223 0.02619 -0.0169 0.8892 0.7441
-2.500 -0.2598 0.03372 0.02769 -0.0073 0.8865 0.7773
-2.250 -0.2417 0.03462 0.02850 -0.0023 0.8843 0.8066
-2.000 -0.2240 0.03460 0.02835 -0.0003 0.8813 0.8137
-1.750 -0.2228 0.03425 0.02791 0.0024 0.8769 0.8169
-1.500 -0.2085 0.03398 0.02751 0.0027 0.8739 0.8194
-1.250 -0.1827 0.03375 0.02713 0.0011 0.8707 0.8212
-1.000 -0.1497 0.03364 0.02686 -0.0015 0.8682 0.8227
-0.750 -0.1377 0.03355 0.02668 -0.0004 0.8650 0.8240
-0.500 -0.1241 0.03349 0.02655 0.0004 0.8612 0.8255
-0.250 -0.1012 0.03349 0.02646 -0.0003 0.8579 0.8266
0.000 -0.0699 0.03355 0.02642 -0.0023 0.8546 0.8274
0.250 -0.0309 0.03371 0.02648 -0.0054 0.8517 0.8285
0.500 -0.0230 0.03383 0.02656 -0.0041 0.8471 0.8296
0.750 0.0010 0.03398 0.02666 -0.0051 0.8424 0.8303
1.000 0.0359 0.03417 0.02679 -0.0075 0.8382 0.8316
1.250 0.0678 0.03445 0.02702 -0.0095 0.8338 0.8328
1.500 0.0846 0.03470 0.02725 -0.0096 0.8275 0.8337
1.750 0.1229 0.03491 0.02742 -0.0124 0.8221 0.8344
2.000 0.1499 0.03524 0.02773 -0.0137 0.8155 0.8355
2.250 0.1798 0.03547 0.02795 -0.0153 0.8079 0.8369
2.500 0.2185 0.03566 0.02814 -0.0178 0.8004 0.8382
2.750 0.2658 0.03521 0.02770 -0.0206 0.7885 0.8391
3.000 0.3378 0.03343 0.02592 -0.0250 0.7711 0.8397
3.250 0.3880 0.03203 0.02456 -0.0270 0.7559 0.8407
3.500 0.4102 0.03198 0.02456 -0.0265 0.7435 0.8422
3.750 0.4880 0.02992 0.02258 -0.0321 0.7394 0.8432
4.000 0.5073 0.02982 0.02256 -0.0309 0.7268 0.8454
4.250 0.5887 0.02747 0.02028 -0.0369 0.7228 0.8470
4.500 0.6150 0.02701 0.01993 -0.0364 0.7097 0.8493
4.750 0.6550 0.02595 0.01895 -0.0374 0.6972 0.8511
5.000 0.7021 0.02451 0.01761 -0.0392 0.6836 0.8529
5.250 0.7411 0.02322 0.01641 -0.0396 0.6672 0.8548
5.500 0.7773 0.02183 0.01509 -0.0394 0.6454 0.8570
5.750 0.8001 0.02075 0.01411 -0.0373 0.6131 0.8596
6.000 0.8075 0.02007 0.01347 -0.0330 0.5533 0.8632
6.250 0.8134 0.02007 0.01233 -0.0281 0.3963 0.8670
6.500 0.8134 0.02130 0.01294 -0.0240 0.3352 0.8708
6.750 0.8261 0.02225 0.01357 -0.0220 0.3037 0.8747
7.000 0.8489 0.02313 0.01421 -0.0218 0.2819 0.8786
7.250 0.8773 0.02399 0.01492 -0.0226 0.2653 0.8828
7.500 0.9078 0.02486 0.01566 -0.0236 0.2524 0.8869
7.750 0.9358 0.02559 0.01644 -0.0240 0.2424 0.8919
8.000 0.9679 0.02654 0.01737 -0.0254 0.2334 0.8974
8.250 0.9960 0.02734 0.01819 -0.0259 0.2252 0.9035
8.500 1.0259 0.02833 0.01924 -0.0267 0.2183 0.9113
8.750 1.0516 0.02916 0.02021 -0.0268 0.2119 0.9205
9.000 1.0853 0.03042 0.02141 -0.0283 0.2056 0.9310
9.250 1.1073 0.03126 0.02258 -0.0279 0.1998 0.9474
9.500 1.1437 0.03251 0.02392 -0.0305 0.1935 0.9810
9.750 1.1752 0.03414 0.02575 -0.0324 0.1877 1.0000
10.000 1.2027 0.03555 0.02737 -0.0338 0.1816 1.0000
10.250 1.2407 0.03761 0.02931 -0.0369 0.1756 1.0000
10.500 1.2556 0.03904 0.03120 -0.0362 0.1705 1.0000
10.750 1.2805 0.04058 0.03289 -0.0371 0.1647 1.0000
11.000 1.3065 0.04271 0.03506 -0.0382 0.1592 1.0000
11.250 1.3132 0.04447 0.03723 -0.0363 0.1543 1.0000
11.500 1.3352 0.04590 0.03870 -0.0365 0.1486 1.0000
11.750 1.3480 0.04823 0.04118 -0.0358 0.1438 1.0000
12.000 1.3432 0.05034 0.04370 -0.0325 0.1398 1.0000
12.250 1.3601 0.05160 0.04500 -0.0319 0.1342 1.0000
12.500 1.3696 0.05399 0.04747 -0.0308 0.1297 1.0000
12.750 1.3477 0.05640 0.05026 -0.0258 0.1274 1.0000
13.000 1.3296 0.05904 0.05320 -0.0220 0.1247 1.0000
13.250 1.3787 0.05962 0.05344 -0.0248 0.1167 1.0000
13.500 1.3469 0.06255 0.05674 -0.0200 0.1156 1.0000
13.750 1.3149 0.06641 0.06095 -0.0166 0.1147 1.0000
14.000 1.2804 0.07113 0.06598 -0.0145 0.1140 1.0000
14.250 1.2420 0.07698 0.07211 -0.0136 0.1138 1.0000
14.500 1.1991 0.08419 0.07956 -0.0143 0.1142 1.0000
14.750 1.1518 0.09318 0.08875 -0.0168 0.1151 1.0000
15.000 1.1019 0.10418 0.09988 -0.0214 0.1161 1.0000
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