SOMERS S102 AIRFOIL (SHARP) (s102s-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: SOMERS S102 AIRFOIL (SHARP) (s102s-il) Reynolds number: 1,000,000 Max Cl/Cd: 95.95 at α=3° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s102s-il-1000000.txt Download as CSV file: xf-s102s-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.4414 0.09572 0.09408 -0.0525 1.0000 0.0106
-11.500 -0.4545 0.08840 0.08679 -0.0557 1.0000 0.0106
-11.250 -0.5068 0.07140 0.06967 -0.0656 1.0000 0.0105
-8.250 -0.4875 0.01942 0.01431 -0.0847 0.8575 0.0077
-8.000 -0.4661 0.01832 0.01307 -0.0838 0.8385 0.0075
-7.750 -0.4459 0.01693 0.01151 -0.0827 0.8231 0.0073
-7.500 -0.4255 0.01589 0.01033 -0.0817 0.8098 0.0072
-7.250 -0.4054 0.01504 0.00936 -0.0806 0.7983 0.0071
-6.750 -0.3645 0.01365 0.00778 -0.0787 0.7786 0.0071
-6.500 -0.3435 0.01306 0.00710 -0.0778 0.7704 0.0071
-6.250 -0.3212 0.01251 0.00648 -0.0773 0.7629 0.0072
-6.000 -0.2983 0.01204 0.00593 -0.0767 0.7559 0.0072
-5.750 -0.2742 0.01158 0.00542 -0.0764 0.7498 0.0074
-5.500 -0.2492 0.01121 0.00499 -0.0762 0.7440 0.0076
-5.250 -0.2254 0.01069 0.00439 -0.0758 0.7386 0.0082
-5.000 -0.1990 0.01037 0.00405 -0.0758 0.7342 0.0092
-4.750 -0.1723 0.01008 0.00372 -0.0758 0.7297 0.0105
-4.500 -0.1457 0.00979 0.00340 -0.0758 0.7254 0.0139
-4.250 -0.1191 0.00944 0.00310 -0.0759 0.7215 0.0289
-4.000 -0.0920 0.00911 0.00288 -0.0761 0.7180 0.0541
-3.750 -0.0653 0.00865 0.00262 -0.0764 0.7145 0.1090
-3.500 -0.0415 0.00739 0.00208 -0.0770 0.7110 0.3114
-3.250 -0.0164 0.00636 0.00181 -0.0775 0.7074 0.5538
-3.000 0.0130 0.00648 0.00194 -0.0778 0.7045 0.5733
-2.750 0.0426 0.00664 0.00205 -0.0781 0.7017 0.5843
-2.500 0.0717 0.00674 0.00217 -0.0782 0.6990 0.5929
-2.250 0.1008 0.00694 0.00234 -0.0783 0.6964 0.6033
-2.000 0.1297 0.00717 0.00258 -0.0784 0.6938 0.6113
-1.750 0.1590 0.00720 0.00254 -0.0788 0.6912 0.6123
-1.500 0.1884 0.00719 0.00250 -0.0791 0.6889 0.6130
-1.250 0.2176 0.00715 0.00244 -0.0795 0.6855 0.6136
-1.000 0.2466 0.00713 0.00238 -0.0797 0.6806 0.6142
-0.750 0.2753 0.00716 0.00234 -0.0800 0.6752 0.6147
-0.500 0.3043 0.00714 0.00230 -0.0803 0.6704 0.6153
-0.250 0.3333 0.00713 0.00226 -0.0805 0.6654 0.6158
0.000 0.3619 0.00712 0.00221 -0.0807 0.6605 0.6166
0.250 0.3906 0.00708 0.00215 -0.0810 0.6552 0.6175
0.500 0.4192 0.00703 0.00211 -0.0812 0.6488 0.6183
0.750 0.4475 0.00706 0.00209 -0.0813 0.6426 0.6191
1.000 0.4763 0.00702 0.00207 -0.0816 0.6369 0.6198
1.250 0.5048 0.00703 0.00206 -0.0818 0.6305 0.6206
1.500 0.5332 0.00705 0.00208 -0.0819 0.6244 0.6213
1.750 0.5618 0.00705 0.00208 -0.0821 0.6171 0.6221
2.000 0.5898 0.00709 0.00210 -0.0822 0.6096 0.6229
2.250 0.6183 0.00710 0.00212 -0.0824 0.6011 0.6238
2.500 0.6462 0.00714 0.00215 -0.0825 0.5911 0.6247
2.750 0.6737 0.00720 0.00218 -0.0825 0.5771 0.6257
3.000 0.7004 0.00730 0.00222 -0.0824 0.5529 0.6267
3.250 0.7206 0.00778 0.00237 -0.0811 0.4745 0.6277
3.500 0.7345 0.00877 0.00283 -0.0788 0.3609 0.6285
3.750 0.7526 0.00948 0.00318 -0.0773 0.2862 0.6294
4.000 0.7733 0.00999 0.00346 -0.0763 0.2383 0.6302
4.500 0.8192 0.01068 0.00391 -0.0749 0.1867 0.6317
4.750 0.8430 0.01095 0.00411 -0.0743 0.1718 0.6324
5.000 0.8665 0.01120 0.00431 -0.0737 0.1603 0.6338
5.250 0.8911 0.01138 0.00449 -0.0733 0.1536 0.6351
5.500 0.9142 0.01164 0.00472 -0.0726 0.1454 0.6363
5.750 0.9390 0.01181 0.00492 -0.0722 0.1418 0.6375
6.000 0.9626 0.01203 0.00514 -0.0716 0.1375 0.6387
6.250 0.9850 0.01232 0.00541 -0.0708 0.1324 0.6400
6.500 1.0085 0.01253 0.00565 -0.0701 0.1298 0.6412
6.750 1.0321 0.01271 0.00587 -0.0695 0.1272 0.6426
7.000 1.0546 0.01295 0.00611 -0.0688 0.1243 0.6439
7.250 1.0760 0.01323 0.00639 -0.0678 0.1210 0.6454
7.500 1.0933 0.01359 0.00676 -0.0660 0.1169 0.6468
7.750 1.1140 0.01378 0.00699 -0.0649 0.1158 0.6480
8.000 1.1347 0.01397 0.00723 -0.0638 0.1140 0.6497
8.250 1.1547 0.01420 0.00751 -0.0626 0.1119 0.6516
8.500 1.1739 0.01449 0.00783 -0.0613 0.1095 0.6535
8.750 1.1916 0.01485 0.00820 -0.0597 0.1064 0.6553
9.000 1.2067 0.01535 0.00872 -0.0578 0.1031 0.6572
9.250 1.2276 0.01558 0.00902 -0.0569 0.1020 0.6592
9.500 1.2479 0.01585 0.00934 -0.0559 0.1003 0.6612
9.750 1.2673 0.01616 0.00968 -0.0548 0.0978 0.6631
10.000 1.2854 0.01654 0.01007 -0.0535 0.0950 0.6651
10.250 1.3003 0.01707 0.01063 -0.0518 0.0915 0.6680
10.500 1.3189 0.01744 0.01106 -0.0507 0.0896 0.6708
10.750 1.3385 0.01776 0.01144 -0.0498 0.0871 0.6736
11.000 1.3561 0.01819 0.01188 -0.0486 0.0833 0.6767
11.250 1.3702 0.01884 0.01252 -0.0471 0.0789 0.6796
11.500 1.3884 0.01926 0.01303 -0.0461 0.0773 0.6833
11.750 1.4049 0.01978 0.01360 -0.0449 0.0741 0.6875
12.000 1.4186 0.02050 0.01431 -0.0435 0.0684 0.6921
12.250 1.4343 0.02112 0.01497 -0.0423 0.0647 0.6967
12.500 1.4461 0.02199 0.01583 -0.0409 0.0584 0.7025
12.750 1.4601 0.02276 0.01666 -0.0397 0.0550 0.7089
13.000 1.4704 0.02380 0.01770 -0.0382 0.0489 0.7158
13.250 1.4819 0.02478 0.01873 -0.0369 0.0449 0.7244
13.500 1.4917 0.02591 0.01989 -0.0355 0.0401 0.7344
13.750 1.5007 0.02714 0.02116 -0.0342 0.0359 0.7473
14.000 1.5108 0.02829 0.02240 -0.0330 0.0326 0.7645
14.250 1.5179 0.02970 0.02388 -0.0317 0.0287 0.7896
14.500 1.5265 0.03087 0.02524 -0.0304 0.0260 0.8403
14.750 1.5317 0.03214 0.02677 -0.0289 0.0232 1.0000
15.000 1.5402 0.03361 0.02828 -0.0280 0.0210 1.0000
15.250 1.5462 0.03534 0.03003 -0.0271 0.0187 1.0000
15.500 1.5533 0.03699 0.03174 -0.0263 0.0171 1.0000
15.750 1.5574 0.03897 0.03375 -0.0254 0.0153 1.0000
16.000 1.5639 0.04078 0.03563 -0.0248 0.0140 1.0000
16.250 1.5675 0.04291 0.03780 -0.0242 0.0128 1.0000
16.500 1.5709 0.04511 0.04009 -0.0237 0.0118 1.0000
16.750 1.5745 0.04736 0.04240 -0.0234 0.0109 1.0000
17.000 1.5755 0.04994 0.04506 -0.0231 0.0102 1.0000
17.250 1.5754 0.05274 0.04794 -0.0230 0.0094 1.0000
17.500 1.5771 0.05541 0.05069 -0.0230 0.0089 1.0000
17.750 1.5763 0.05845 0.05382 -0.0232 0.0084 1.0000
18.000 1.5737 0.06183 0.05729 -0.0236 0.0080 1.0000
18.250 1.5679 0.06575 0.06131 -0.0243 0.0075 1.0000
18.500 1.5636 0.06959 0.06526 -0.0252 0.0071 1.0000
18.750 1.5578 0.07379 0.06958 -0.0264 0.0069 1.0000
19.000 1.5503 0.07843 0.07433 -0.0279 0.0066 1.0000
19.250 1.5397 0.08372 0.07975 -0.0299 0.0064 1.0000
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