SOMERS S102 AIRFOIL (SHARP) (s102s-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: SOMERS S102 AIRFOIL (SHARP) (s102s-il) Reynolds number: 500,000 Max Cl/Cd: 82.29 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s102s-il-500000.txt Download as CSV file: xf-s102s-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.3462 0.08808 0.08603 -0.0541 1.0000 0.0209
-11.000 -0.3599 0.08175 0.07973 -0.0559 1.0000 0.0209
-10.750 -0.4236 0.06419 0.06199 -0.0662 0.9995 0.0206
-10.500 -0.4508 0.05597 0.05360 -0.0715 0.9972 0.0205
-10.250 -0.4649 0.04989 0.04739 -0.0757 0.9944 0.0206
-10.000 -0.5584 0.06037 0.05752 -0.0729 0.9945 0.0200
-9.750 -0.5645 0.05591 0.05273 -0.0782 0.9855 0.0201
-7.750 -0.4394 0.02289 0.01718 -0.0850 0.9074 0.0131
-7.500 -0.4120 0.02088 0.01508 -0.0851 0.8919 0.0125
-7.250 -0.3867 0.01916 0.01316 -0.0846 0.8756 0.0121
-7.000 -0.3627 0.01786 0.01167 -0.0838 0.8603 0.0118
-6.750 -0.3402 0.01686 0.01051 -0.0829 0.8467 0.0117
-6.500 -0.3189 0.01605 0.00956 -0.0818 0.8348 0.0117
-6.250 -0.2984 0.01535 0.00876 -0.0808 0.8237 0.0119
-6.000 -0.2777 0.01471 0.00804 -0.0798 0.8145 0.0122
-5.750 -0.2565 0.01414 0.00737 -0.0790 0.8060 0.0126
-5.500 -0.2365 0.01338 0.00655 -0.0781 0.7985 0.0136
-5.250 -0.2134 0.01292 0.00604 -0.0777 0.7914 0.0146
-5.000 -0.1894 0.01246 0.00550 -0.0773 0.7853 0.0166
-4.750 -0.1649 0.01203 0.00505 -0.0771 0.7792 0.0196
-4.500 -0.1401 0.01155 0.00456 -0.0769 0.7741 0.0299
-4.250 -0.1166 0.01078 0.00404 -0.0768 0.7694 0.0842
-4.000 -0.0967 0.00914 0.00327 -0.0773 0.7645 0.3050
-3.750 -0.0734 0.00826 0.00325 -0.0774 0.7602 0.5660
-3.500 -0.0445 0.00865 0.00359 -0.0773 0.7565 0.5892
-3.250 -0.0157 0.00899 0.00388 -0.0772 0.7529 0.6034
-3.000 0.0130 0.00936 0.00421 -0.0771 0.7491 0.6155
-2.750 0.0408 0.00970 0.00462 -0.0766 0.7454 0.6257
-2.500 0.0684 0.01022 0.00518 -0.0759 0.7422 0.6387
-2.250 0.0975 0.01033 0.00521 -0.0762 0.7394 0.6421
-2.000 0.1266 0.01027 0.00509 -0.0766 0.7366 0.6433
-1.750 0.1557 0.01021 0.00498 -0.0770 0.7337 0.6444
-1.500 0.1849 0.01015 0.00486 -0.0775 0.7308 0.6453
-1.250 0.2142 0.01010 0.00475 -0.0780 0.7281 0.6462
-1.000 0.2436 0.01009 0.00467 -0.0784 0.7256 0.6472
-0.750 0.2732 0.01011 0.00461 -0.0790 0.7227 0.6480
-0.500 0.3017 0.01003 0.00452 -0.0792 0.7186 0.6486
-0.250 0.3299 0.00992 0.00437 -0.0794 0.7127 0.6494
0.000 0.3586 0.00987 0.00426 -0.0796 0.7072 0.6501
0.250 0.3864 0.00979 0.00419 -0.0797 0.7012 0.6509
0.500 0.4146 0.00974 0.00412 -0.0798 0.6953 0.6518
0.750 0.4433 0.00975 0.00407 -0.0800 0.6900 0.6528
1.000 0.4710 0.00968 0.00403 -0.0800 0.6835 0.6536
1.250 0.4990 0.00964 0.00395 -0.0801 0.6764 0.6544
1.500 0.5266 0.00960 0.00391 -0.0801 0.6687 0.6553
1.750 0.5545 0.00956 0.00386 -0.0802 0.6616 0.6562
2.000 0.5826 0.00956 0.00385 -0.0803 0.6557 0.6572
2.250 0.6105 0.00953 0.00384 -0.0804 0.6491 0.6582
2.500 0.6384 0.00954 0.00382 -0.0804 0.6419 0.6592
2.750 0.6656 0.00950 0.00382 -0.0804 0.6326 0.6602
3.000 0.6930 0.00950 0.00381 -0.0803 0.6234 0.6613
3.250 0.7199 0.00951 0.00381 -0.0802 0.6120 0.6625
3.500 0.7466 0.00953 0.00383 -0.0800 0.5978 0.6637
3.750 0.7723 0.00957 0.00384 -0.0797 0.5776 0.6646
4.000 0.7949 0.00966 0.00382 -0.0787 0.5334 0.6657
4.250 0.8018 0.01065 0.00418 -0.0750 0.4036 0.6668
4.500 0.8116 0.01170 0.00474 -0.0722 0.3054 0.6679
4.750 0.8268 0.01243 0.00516 -0.0702 0.2466 0.6690
5.000 0.8454 0.01295 0.00552 -0.0688 0.2136 0.6702
5.250 0.8653 0.01338 0.00584 -0.0677 0.1939 0.6715
5.500 0.8861 0.01373 0.00615 -0.0666 0.1811 0.6729
5.750 0.9069 0.01407 0.00646 -0.0656 0.1722 0.6743
6.000 0.9276 0.01441 0.00678 -0.0645 0.1649 0.6758
6.250 0.9473 0.01477 0.00713 -0.0633 0.1588 0.6773
6.500 0.9679 0.01504 0.00742 -0.0622 0.1542 0.6788
6.750 0.9854 0.01539 0.00776 -0.0605 0.1499 0.6802
7.000 0.9994 0.01585 0.00823 -0.0583 0.1455 0.6821
7.250 1.0197 0.01610 0.00856 -0.0572 0.1430 0.6839
7.500 1.0391 0.01641 0.00893 -0.0559 0.1397 0.6858
7.750 1.0570 0.01680 0.00936 -0.0545 0.1366 0.6877
8.000 1.0725 0.01734 0.00989 -0.0528 0.1332 0.6897
8.250 1.0883 0.01790 0.01049 -0.0511 0.1302 0.6918
8.500 1.1080 0.01824 0.01091 -0.0501 0.1281 0.6940
8.750 1.1268 0.01864 0.01136 -0.0489 0.1254 0.6961
9.000 1.1446 0.01907 0.01185 -0.0477 0.1228 0.6985
9.250 1.1604 0.01963 0.01244 -0.0463 0.1201 0.7010
9.500 1.1730 0.02049 0.01332 -0.0444 0.1167 0.7036
9.750 1.1926 0.02083 0.01377 -0.0436 0.1149 0.7066
10.000 1.2111 0.02127 0.01429 -0.0426 0.1124 0.7098
10.250 1.2286 0.02177 0.01486 -0.0416 0.1098 0.7130
10.500 1.2447 0.02234 0.01548 -0.0404 0.1070 0.7165
10.750 1.2567 0.02330 0.01647 -0.0388 0.1035 0.7204
11.000 1.2750 0.02377 0.01705 -0.0380 0.1015 0.7252
11.250 1.2927 0.02427 0.01766 -0.0372 0.0988 0.7300
11.500 1.3095 0.02482 0.01830 -0.0363 0.0957 0.7354
11.750 1.3231 0.02564 0.01914 -0.0352 0.0923 0.7418
12.000 1.3380 0.02640 0.02001 -0.0342 0.0892 0.7484
12.250 1.3562 0.02690 0.02064 -0.0336 0.0857 0.7571
12.500 1.3711 0.02763 0.02144 -0.0328 0.0819 0.7673
12.750 1.3828 0.02865 0.02253 -0.0317 0.0783 0.7805
13.000 1.3999 0.02923 0.02330 -0.0310 0.0746 0.8003
13.250 1.4118 0.03007 0.02430 -0.0299 0.0707 0.8369
13.500 1.4216 0.03089 0.02537 -0.0285 0.0669 1.0000
13.750 1.4357 0.03191 0.02643 -0.0279 0.0624 1.0000
14.000 1.4454 0.03330 0.02782 -0.0271 0.0579 1.0000
14.250 1.4572 0.03455 0.02911 -0.0265 0.0532 1.0000
14.500 1.4647 0.03618 0.03075 -0.0257 0.0488 1.0000
14.750 1.4732 0.03776 0.03237 -0.0250 0.0446 1.0000
15.000 1.4782 0.03970 0.03434 -0.0242 0.0407 1.0000
15.250 1.4843 0.04158 0.03627 -0.0236 0.0368 1.0000
15.500 1.4874 0.04380 0.03854 -0.0230 0.0336 1.0000
15.750 1.4911 0.04600 0.04078 -0.0226 0.0303 1.0000
16.000 1.4925 0.04852 0.04335 -0.0222 0.0274 1.0000
16.250 1.4939 0.05111 0.04602 -0.0220 0.0251 1.0000
16.500 1.4903 0.05435 0.04932 -0.0219 0.0232 1.0000
16.750 1.4925 0.05701 0.05208 -0.0220 0.0212 1.0000
17.000 1.4880 0.06057 0.05572 -0.0223 0.0198 1.0000
17.250 1.4815 0.06456 0.05983 -0.0229 0.0186 1.0000
17.500 1.4794 0.06809 0.06349 -0.0236 0.0173 1.0000
17.750 1.4719 0.07252 0.06802 -0.0247 0.0164 1.0000
18.000 1.4604 0.07774 0.07337 -0.0264 0.0159 1.0000
18.250 1.4434 0.08411 0.07989 -0.0288 0.0153 1.0000
18.500 1.4340 0.08954 0.08547 -0.0311 0.0147 1.0000
18.750 1.4183 0.09631 0.09241 -0.0343 0.0144 1.0000
19.000 1.4005 0.10378 0.10005 -0.0381 0.0141 1.0000
19.250 1.3782 0.11234 0.10879 -0.0427 0.0140 1.0000
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Polar data table (+)
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