SOMERS S102 AIRFOIL (SHARP) (s102s-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: SOMERS S102 AIRFOIL (SHARP) (s102s-il) Reynolds number: 50,000 Max Cl/Cd: 26.44 at α=9.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s102s-il-50000-n5.txt Download as CSV file: xf-s102s-il-50000-n5.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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.250 -0.4104 0.12187 0.11436 -0.0505 1.0000 0.0443
-12.000 -0.4067 0.11827 0.11080 -0.0508 1.0000 0.0436
-11.750 -0.4059 0.11433 0.10692 -0.0517 1.0000 0.0428
-11.500 -0.4075 0.11004 0.10269 -0.0530 1.0000 0.0421
-11.250 -0.4120 0.10510 0.09782 -0.0548 1.0000 0.0412
-11.000 -0.4199 0.09933 0.09212 -0.0573 1.0000 0.0402
-10.750 -0.4343 0.09287 0.08571 -0.0605 1.0000 0.0392
-10.500 -0.4602 0.08612 0.07898 -0.0639 1.0000 0.0381
-10.000 -0.5275 0.07636 0.06907 -0.0659 1.0000 0.0365
-9.750 -0.5465 0.07373 0.06645 -0.0642 1.0000 0.0363
-9.500 -0.5685 0.07162 0.06436 -0.0614 1.0000 0.0362
-9.250 -0.5913 0.06996 0.06272 -0.0577 1.0000 0.0361
-9.000 -0.6112 0.06805 0.06078 -0.0540 1.0000 0.0359
-8.750 -0.6302 0.06623 0.05890 -0.0503 1.0000 0.0358
-8.500 -0.6472 0.06438 0.05696 -0.0465 1.0000 0.0357
-8.250 -0.6571 0.06211 0.05453 -0.0440 0.9987 0.0356
-8.000 -0.6435 0.05793 0.04993 -0.0463 0.9897 0.0355
-7.750 -0.6261 0.05420 0.04572 -0.0482 0.9816 0.0354
-7.500 -0.6067 0.05074 0.04178 -0.0494 0.9736 0.0355
-7.250 -0.5857 0.04772 0.03827 -0.0501 0.9661 0.0360
-7.000 -0.5601 0.04499 0.03512 -0.0512 0.9598 0.0371
-6.750 -0.5361 0.04304 0.03308 -0.0517 0.9533 0.0390
-6.500 -0.5085 0.04113 0.03088 -0.0523 0.9473 0.0413
-6.250 -0.4735 0.03919 0.02857 -0.0531 0.9435 0.0432
-6.000 -0.4458 0.03781 0.02701 -0.0521 0.9375 0.0450
-5.750 -0.4136 0.03676 0.02599 -0.0520 0.9331 0.0496
-5.500 -0.3790 0.03586 0.02494 -0.0517 0.9298 0.0552
-5.250 -0.3604 0.03508 0.02417 -0.0502 0.9230 0.0608
-5.000 -0.3397 0.03412 0.02319 -0.0494 0.9171 0.0690
-4.750 -0.3217 0.03309 0.02212 -0.0486 0.9110 0.0799
-4.500 -0.3093 0.03191 0.02105 -0.0474 0.9036 0.0972
-4.250 -0.2925 0.02977 0.01940 -0.0481 0.8986 0.1529
-4.000 -0.3046 0.02944 0.02153 -0.0399 0.8902 0.5436
-3.750 -0.2853 0.03175 0.02349 -0.0353 0.8852 0.6423
-3.500 -0.2737 0.03469 0.02640 -0.0255 0.8806 0.6999
-3.250 -0.2562 0.03643 0.02799 -0.0183 0.8759 0.7389
-3.000 -0.2330 0.03623 0.02751 -0.0178 0.8715 0.7479
-2.750 -0.2038 0.03589 0.02687 -0.0188 0.8683 0.7520
-2.500 -0.1964 0.03559 0.02639 -0.0168 0.8620 0.7568
-2.250 -0.1774 0.03523 0.02582 -0.0166 0.8570 0.7608
-2.000 -0.1489 0.03499 0.02535 -0.0175 0.8536 0.7633
-1.750 -0.1276 0.03480 0.02499 -0.0173 0.8495 0.7661
-1.500 -0.1152 0.03468 0.02473 -0.0160 0.8441 0.7692
-1.250 -0.0917 0.03450 0.02438 -0.0165 0.8400 0.7720
-1.000 -0.0624 0.03431 0.02402 -0.0181 0.8369 0.7746
-0.750 -0.0448 0.03429 0.02388 -0.0176 0.8323 0.7767
-0.500 -0.0276 0.03433 0.02383 -0.0168 0.8274 0.7788
-0.250 -0.0021 0.03432 0.02372 -0.0174 0.8236 0.7809
0.000 0.0284 0.03430 0.02360 -0.0188 0.8207 0.7826
0.250 0.0460 0.03445 0.02367 -0.0184 0.8158 0.7847
0.500 0.0657 0.03461 0.02376 -0.0184 0.8108 0.7873
0.750 0.0944 0.03471 0.02378 -0.0197 0.8069 0.7895
1.000 0.1277 0.03479 0.02380 -0.0217 0.8039 0.7913
1.250 0.1411 0.03513 0.02412 -0.0205 0.7975 0.7930
1.500 0.1654 0.03535 0.02433 -0.0209 0.7926 0.7948
1.750 0.1972 0.03549 0.02446 -0.0223 0.7888 0.7969
2.000 0.2166 0.03585 0.02482 -0.0221 0.7827 0.7994
2.250 0.2407 0.03615 0.02513 -0.0225 0.7766 0.8019
2.500 0.2760 0.03628 0.02527 -0.0244 0.7723 0.8040
2.750 0.2944 0.03674 0.02576 -0.0243 0.7642 0.8064
3.000 0.3257 0.03688 0.02595 -0.0254 0.7580 0.8083
3.250 0.3499 0.03712 0.02627 -0.0254 0.7498 0.8105
3.500 0.3855 0.03692 0.02614 -0.0265 0.7409 0.8130
3.750 0.4178 0.03646 0.02575 -0.0267 0.7266 0.8158
4.000 0.4589 0.03540 0.02475 -0.0273 0.7105 0.8186
4.250 0.4996 0.03424 0.02369 -0.0279 0.6943 0.8214
4.500 0.5311 0.03356 0.02310 -0.0276 0.6794 0.8241
4.750 0.5596 0.03300 0.02266 -0.0270 0.6649 0.8270
5.000 0.5875 0.03245 0.02226 -0.0264 0.6499 0.8301
5.250 0.6139 0.03194 0.02189 -0.0256 0.6334 0.8338
5.500 0.6397 0.03140 0.02148 -0.0248 0.6146 0.8380
5.750 0.6595 0.03097 0.02122 -0.0230 0.5938 0.8423
6.000 0.6680 0.03119 0.02161 -0.0205 0.5653 0.8477
6.500 0.6987 0.03099 0.02165 -0.0167 0.4783 0.8591
6.750 0.7473 0.02890 0.01894 -0.0160 0.3976 0.8639
7.000 0.7628 0.02958 0.01911 -0.0142 0.3440 0.8701
7.250 0.7738 0.03058 0.01988 -0.0124 0.3123 0.8775
7.500 0.7877 0.03158 0.02074 -0.0112 0.2897 0.8862
7.750 0.8033 0.03248 0.02156 -0.0101 0.2725 0.8970
8.000 0.8220 0.03330 0.02237 -0.0095 0.2577 0.9109
8.250 0.8455 0.03408 0.02319 -0.0096 0.2450 0.9316
8.500 0.8724 0.03471 0.02382 -0.0101 0.2350 1.0000
8.750 0.9048 0.03560 0.02475 -0.0115 0.2249 1.0000
9.000 0.9387 0.03653 0.02576 -0.0131 0.2157 1.0000
9.250 0.9772 0.03743 0.02662 -0.0151 0.2071 1.0000
9.500 1.0123 0.03854 0.02795 -0.0168 0.1999 1.0000
9.750 1.0492 0.03968 0.02913 -0.0187 0.1928 1.0000
10.000 1.0790 0.04106 0.03070 -0.0198 0.1862 1.0000
10.250 1.1079 0.04248 0.03229 -0.0209 0.1803 1.0000
10.500 1.1426 0.04399 0.03383 -0.0227 0.1747 1.0000
10.750 1.1563 0.04574 0.03594 -0.0219 0.1694 1.0000
11.000 1.1772 0.04735 0.03770 -0.0220 0.1642 1.0000
11.250 1.2030 0.04909 0.03951 -0.0227 0.1594 1.0000
11.500 1.2050 0.05123 0.04206 -0.0207 0.1553 1.0000
11.750 1.2135 0.05317 0.04423 -0.0196 0.1507 1.0000
12.000 1.2392 0.05477 0.04581 -0.0202 0.1460 1.0000
12.250 1.2301 0.05748 0.04891 -0.0176 0.1429 1.0000
12.500 1.2199 0.06036 0.05212 -0.0155 0.1396 1.0000
12.750 1.2151 0.06306 0.05506 -0.0140 0.1361 1.0000
13.000 1.2325 0.06467 0.05669 -0.0138 0.1319 1.0000
13.250 1.2181 0.06826 0.06055 -0.0124 0.1296 1.0000
13.500 1.1870 0.07325 0.06589 -0.0113 0.1281 1.0000
13.750 1.1515 0.07935 0.07228 -0.0115 0.1270 1.0000
14.000 1.1058 0.08748 0.08067 -0.0133 0.1267 1.0000
14.250 1.0367 0.10056 0.09393 -0.0190 0.1274 1.0000
|
Polar data table (+)
Polar graphs
<< Back to SOMERS S102 AIRFOIL (SHARP) (s102s-il)