SOMERS S102 AIRFOIL (SHARP) (s102s-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: SOMERS S102 AIRFOIL (SHARP) (s102s-il) Reynolds number: 1,000,000 Max Cl/Cd: 82.25 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s102s-il-1000000-n5.txt Download as CSV file: xf-s102s-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.500 -0.6368 0.06822 0.06611 -0.0678 1.0000 0.0037
-13.250 -0.6563 0.06191 0.05969 -0.0709 1.0000 0.0037
-13.000 -0.6665 0.05799 0.05569 -0.0722 1.0000 0.0037
-12.500 -0.7023 0.04676 0.04408 -0.0778 0.9977 0.0036
-12.250 -0.7078 0.04267 0.03980 -0.0800 0.9929 0.0036
-12.000 -0.7229 0.03727 0.03409 -0.0823 0.9877 0.0036
-11.750 -0.7202 0.03364 0.03022 -0.0846 0.9842 0.0036
-11.500 -0.7134 0.03078 0.02714 -0.0861 0.9788 0.0036
-11.250 -0.6983 0.02813 0.02426 -0.0884 0.9739 0.0036
-10.750 -0.6615 0.02406 0.01979 -0.0915 0.9573 0.0036
-10.500 -0.6436 0.02253 0.01808 -0.0919 0.9396 0.0036
-10.250 -0.6259 0.02127 0.01658 -0.0918 0.9003 0.0036
-10.000 -0.6170 0.02039 0.01541 -0.0896 0.8565 0.0036
-9.750 -0.6084 0.01958 0.01439 -0.0873 0.8303 0.0036
-9.500 -0.5990 0.01883 0.01347 -0.0850 0.8115 0.0036
-9.250 -0.5843 0.01810 0.01260 -0.0834 0.7972 0.0036
-9.000 -0.5679 0.01743 0.01179 -0.0821 0.7846 0.0036
-8.750 -0.5503 0.01678 0.01103 -0.0810 0.7736 0.0036
-8.500 -0.5328 0.01607 0.01021 -0.0799 0.7642 0.0037
-8.000 -0.4961 0.01469 0.00865 -0.0778 0.7483 0.0037
-7.750 -0.4755 0.01416 0.00803 -0.0770 0.7412 0.0038
-7.500 -0.4545 0.01360 0.00740 -0.0763 0.7353 0.0038
-7.250 -0.4325 0.01309 0.00683 -0.0758 0.7294 0.0039
-7.000 -0.4094 0.01268 0.00636 -0.0753 0.7239 0.0040
-6.750 -0.3854 0.01229 0.00592 -0.0750 0.7192 0.0041
-6.500 -0.3607 0.01193 0.00552 -0.0748 0.7144 0.0042
-6.250 -0.3357 0.01161 0.00516 -0.0746 0.7096 0.0044
-6.000 -0.3102 0.01133 0.00483 -0.0745 0.7055 0.0045
-5.750 -0.2840 0.01104 0.00451 -0.0745 0.7014 0.0048
-5.500 -0.2577 0.01078 0.00422 -0.0745 0.6972 0.0052
-5.250 -0.2310 0.01056 0.00395 -0.0745 0.6933 0.0055
-5.000 -0.2045 0.01031 0.00368 -0.0745 0.6900 0.0064
-4.750 -0.1771 0.01010 0.00346 -0.0746 0.6871 0.0073
-4.500 -0.1496 0.00989 0.00324 -0.0748 0.6840 0.0092
-4.250 -0.1221 0.00969 0.00305 -0.0749 0.6809 0.0126
-4.000 -0.0946 0.00950 0.00287 -0.0751 0.6780 0.0187
-3.750 -0.0669 0.00932 0.00270 -0.0753 0.6752 0.0273
-3.500 -0.0393 0.00905 0.00253 -0.0755 0.6729 0.0494
-3.250 -0.0122 0.00861 0.00230 -0.0759 0.6704 0.1085
-3.000 0.0135 0.00766 0.00191 -0.0765 0.6677 0.2698
-2.750 0.0385 0.00635 0.00153 -0.0773 0.6650 0.5444
-2.500 0.0677 0.00640 0.00156 -0.0775 0.6626 0.5608
-2.250 0.0969 0.00649 0.00164 -0.0778 0.6604 0.5748
-2.000 0.1262 0.00664 0.00172 -0.0780 0.6582 0.5846
-1.750 0.1555 0.00661 0.00168 -0.0784 0.6565 0.5859
-1.500 0.1849 0.00660 0.00165 -0.0787 0.6545 0.5867
-1.250 0.2140 0.00659 0.00162 -0.0790 0.6509 0.5874
-1.000 0.2427 0.00661 0.00159 -0.0792 0.6453 0.5880
-0.750 0.2716 0.00662 0.00157 -0.0795 0.6396 0.5887
-0.500 0.3004 0.00663 0.00155 -0.0797 0.6329 0.5893
-0.250 0.3288 0.00667 0.00154 -0.0799 0.6263 0.5900
0.000 0.3579 0.00667 0.00153 -0.0801 0.6204 0.5907
0.250 0.3863 0.00671 0.00153 -0.0803 0.6123 0.5914
0.500 0.4149 0.00673 0.00153 -0.0805 0.6032 0.5921
0.750 0.4430 0.00678 0.00153 -0.0806 0.5935 0.5928
1.000 0.4713 0.00683 0.00155 -0.0808 0.5817 0.5935
1.250 0.4991 0.00690 0.00157 -0.0808 0.5663 0.5943
1.500 0.5260 0.00703 0.00160 -0.0807 0.5402 0.5952
1.750 0.5463 0.00760 0.00178 -0.0795 0.4509 0.5961
2.000 0.5656 0.00832 0.00210 -0.0781 0.3625 0.5968
2.250 0.5878 0.00880 0.00233 -0.0773 0.3048 0.5975
2.500 0.6114 0.00918 0.00252 -0.0767 0.2637 0.5981
2.750 0.6356 0.00949 0.00269 -0.0763 0.2325 0.5988
3.000 0.6602 0.00977 0.00286 -0.0758 0.2083 0.5993
3.500 0.7103 0.01023 0.00317 -0.0751 0.1746 0.6009
3.750 0.7354 0.01044 0.00333 -0.0748 0.1620 0.6018
4.000 0.7609 0.01062 0.00348 -0.0745 0.1534 0.6027
4.250 0.7860 0.01082 0.00365 -0.0741 0.1456 0.6037
4.500 0.8118 0.01097 0.00381 -0.0739 0.1412 0.6046
4.750 0.8369 0.01115 0.00398 -0.0735 0.1361 0.6055
5.000 0.8617 0.01135 0.00417 -0.0731 0.1310 0.6065
5.250 0.8870 0.01151 0.00434 -0.0728 0.1284 0.6075
5.500 0.9118 0.01169 0.00453 -0.0724 0.1249 0.6085
5.750 0.9359 0.01191 0.00473 -0.0719 0.1211 0.6095
6.000 0.9597 0.01213 0.00495 -0.0713 0.1172 0.6106
6.250 0.9841 0.01231 0.00515 -0.0709 0.1156 0.6118
6.500 1.0081 0.01249 0.00537 -0.0703 0.1138 0.6129
6.750 1.0315 0.01270 0.00559 -0.0697 0.1113 0.6141
7.000 1.0541 0.01294 0.00583 -0.0689 0.1085 0.6150
7.250 1.0760 0.01319 0.00609 -0.0680 0.1057 0.6159
7.500 1.0967 0.01343 0.00635 -0.0669 0.1030 0.6172
7.750 1.1174 0.01362 0.00659 -0.0658 0.1018 0.6185
8.000 1.1375 0.01383 0.00684 -0.0645 0.1000 0.6199
8.250 1.1571 0.01409 0.00714 -0.0632 0.0978 0.6213
8.500 1.1763 0.01439 0.00745 -0.0619 0.0953 0.6227
8.750 1.1948 0.01472 0.00779 -0.0605 0.0923 0.6242
9.000 1.2137 0.01504 0.00815 -0.0592 0.0900 0.6258
9.250 1.2332 0.01534 0.00850 -0.0581 0.0885 0.6274
9.500 1.2520 0.01567 0.00886 -0.0568 0.0862 0.6289
9.750 1.2699 0.01606 0.00926 -0.0555 0.0831 0.6304
10.000 1.2867 0.01651 0.00971 -0.0540 0.0795 0.6318
10.250 1.3048 0.01689 0.01015 -0.0528 0.0773 0.6336
10.500 1.3221 0.01732 0.01062 -0.0514 0.0741 0.6357
10.750 1.3375 0.01787 0.01116 -0.0499 0.0694 0.6377
11.000 1.3532 0.01841 0.01172 -0.0485 0.0648 0.6400
11.250 1.3666 0.01910 0.01239 -0.0469 0.0589 0.6425
11.500 1.3821 0.01969 0.01303 -0.0455 0.0559 0.6450
11.750 1.3952 0.02045 0.01379 -0.0440 0.0513 0.6474
12.000 1.4067 0.02133 0.01466 -0.0424 0.0449 0.6500
12.250 1.4179 0.02226 0.01560 -0.0408 0.0399 0.6529
12.500 1.4275 0.02335 0.01668 -0.0391 0.0340 0.6560
12.750 1.4404 0.02422 0.01760 -0.0379 0.0316 0.6593
13.000 1.4495 0.02542 0.01880 -0.0364 0.0266 0.6624
13.500 1.4700 0.02771 0.02116 -0.0338 0.0207 0.6696
13.750 1.4796 0.02895 0.02244 -0.0326 0.0183 0.6740
14.000 1.4899 0.03016 0.02370 -0.0316 0.0166 0.6785
14.250 1.4979 0.03159 0.02517 -0.0305 0.0142 0.6830
14.500 1.5060 0.03303 0.02667 -0.0294 0.0125 0.6886
14.750 1.5143 0.03451 0.02822 -0.0285 0.0110 0.6946
15.000 1.5222 0.03604 0.02983 -0.0276 0.0100 0.7008
15.250 1.5288 0.03771 0.03157 -0.0268 0.0088 0.7085
15.500 1.5357 0.03940 0.03335 -0.0261 0.0081 0.7167
15.750 1.5412 0.04128 0.03532 -0.0254 0.0073 0.7265
16.000 1.5467 0.04319 0.03733 -0.0249 0.0066 0.7380
16.250 1.5516 0.04520 0.03945 -0.0244 0.0062 0.7525
16.500 1.5550 0.04741 0.04180 -0.0240 0.0057 0.7733
16.750 1.5582 0.04968 0.04423 -0.0237 0.0052 0.8039
17.000 1.5600 0.05171 0.04668 -0.0232 0.0050 0.9883
17.250 1.5609 0.05434 0.04940 -0.0230 0.0048 1.0000
17.500 1.5606 0.05730 0.05245 -0.0232 0.0044 1.0000
17.750 1.5588 0.06055 0.05579 -0.0235 0.0041 1.0000
18.000 1.5568 0.06394 0.05927 -0.0241 0.0040 1.0000
18.250 1.5542 0.06750 0.06293 -0.0248 0.0038 1.0000
18.500 1.5493 0.07150 0.06704 -0.0258 0.0036 1.0000
18.750 1.5433 0.07584 0.07149 -0.0271 0.0035 1.0000
19.000 1.5339 0.08085 0.07663 -0.0289 0.0032 1.0000
19.250 1.5227 0.08637 0.08228 -0.0311 0.0031 1.0000
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Polar data table (+)
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