SOMERS S102 AIRFOIL (BLUNT) (s102b-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: SOMERS S102 AIRFOIL (BLUNT) (s102b-il) Reynolds number: 200,000 Max Cl/Cd: 57.64 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s102b-il-200000-n5.txt Download as CSV file: xf-s102b-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: SOMERS S102 AIRFOIL (BLUNT)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.4763 0.09083 0.08721 -0.0493 1.0000 0.0131
-11.000 -0.4917 0.08137 0.07772 -0.0558 1.0000 0.0128
-10.750 -0.5125 0.07367 0.06993 -0.0608 1.0000 0.0126
-10.500 -0.5337 0.06748 0.06364 -0.0641 1.0000 0.0124
-10.250 -0.5545 0.06234 0.05839 -0.0660 1.0000 0.0122
-10.000 -0.5758 0.05818 0.05412 -0.0662 1.0000 0.0121
-9.750 -0.5953 0.05430 0.05010 -0.0661 0.9946 0.0119
-9.500 -0.6028 0.04788 0.04325 -0.0698 0.9744 0.0115
-9.250 -0.6104 0.03947 0.03391 -0.0711 0.9574 0.0108
-9.000 -0.5957 0.03608 0.03006 -0.0717 0.9445 0.0107
-8.750 -0.5771 0.03329 0.02689 -0.0722 0.9327 0.0107
-8.500 -0.5561 0.03086 0.02413 -0.0725 0.9216 0.0107
-8.250 -0.5342 0.02882 0.02183 -0.0725 0.9099 0.0108
-8.000 -0.5119 0.02711 0.01991 -0.0722 0.8980 0.0109
-7.750 -0.4888 0.02566 0.01827 -0.0719 0.8867 0.0111
-7.500 -0.4653 0.02438 0.01683 -0.0714 0.8759 0.0113
-7.250 -0.4423 0.02325 0.01556 -0.0709 0.8645 0.0115
-7.000 -0.4192 0.02222 0.01440 -0.0703 0.8544 0.0119
-6.750 -0.3962 0.02125 0.01332 -0.0696 0.8453 0.0123
-6.500 -0.3736 0.02036 0.01231 -0.0691 0.8363 0.0128
-6.000 -0.3278 0.01870 0.01047 -0.0684 0.8205 0.0140
-5.750 -0.3037 0.01804 0.00975 -0.0683 0.8138 0.0151
-5.500 -0.2787 0.01746 0.00907 -0.0684 0.8070 0.0172
-5.250 -0.2534 0.01689 0.00847 -0.0685 0.8005 0.0198
-5.000 -0.2277 0.01627 0.00777 -0.0687 0.7950 0.0230
-4.750 -0.2014 0.01570 0.00715 -0.0691 0.7889 0.0290
-4.500 -0.1747 0.01510 0.00658 -0.0695 0.7838 0.0431
-4.250 -0.1478 0.01435 0.00600 -0.0702 0.7796 0.0863
-4.000 -0.1246 0.01178 0.00539 -0.0728 0.7745 0.4898
-3.750 -0.0955 0.01228 0.00587 -0.0726 0.7701 0.5744
-3.500 -0.0667 0.01276 0.00622 -0.0723 0.7664 0.5995
-3.250 -0.0396 0.01341 0.00684 -0.0714 0.7628 0.6195
-3.000 -0.0132 0.01401 0.00744 -0.0703 0.7584 0.6354
-2.750 0.0148 0.01409 0.00745 -0.0701 0.7544 0.6386
-2.500 0.0442 0.01400 0.00723 -0.0706 0.7511 0.6399
-2.250 0.0738 0.01393 0.00703 -0.0711 0.7483 0.6414
-2.000 0.1034 0.01384 0.00685 -0.0718 0.7450 0.6427
-1.750 0.1330 0.01375 0.00669 -0.0724 0.7417 0.6439
-1.500 0.1628 0.01369 0.00654 -0.0731 0.7386 0.6456
-1.250 0.1926 0.01363 0.00639 -0.0737 0.7357 0.6470
-1.000 0.2227 0.01357 0.00623 -0.0744 0.7331 0.6481
-0.750 0.2526 0.01354 0.00612 -0.0751 0.7303 0.6493
-0.500 0.2819 0.01351 0.00607 -0.0757 0.7273 0.6502
-0.250 0.3109 0.01351 0.00606 -0.0761 0.7245 0.6511
0.000 0.3400 0.01352 0.00607 -0.0765 0.7219 0.6521
0.250 0.3693 0.01353 0.00606 -0.0769 0.7193 0.6531
0.500 0.3986 0.01353 0.00601 -0.0773 0.7159 0.6540
0.750 0.4267 0.01350 0.00601 -0.0775 0.7085 0.6550
1.000 0.4553 0.01343 0.00587 -0.0776 0.7004 0.6560
1.250 0.4832 0.01338 0.00582 -0.0777 0.6905 0.6571
1.500 0.5117 0.01334 0.00573 -0.0779 0.6825 0.6582
1.750 0.5397 0.01330 0.00569 -0.0780 0.6726 0.6594
2.000 0.5678 0.01326 0.00565 -0.0781 0.6625 0.6608
2.250 0.5960 0.01323 0.00556 -0.0782 0.6516 0.6623
2.500 0.6239 0.01321 0.00555 -0.0783 0.6393 0.6639
2.750 0.6519 0.01321 0.00557 -0.0784 0.6276 0.6653
3.000 0.6795 0.01321 0.00558 -0.0785 0.6157 0.6663
3.250 0.7066 0.01321 0.00561 -0.0784 0.6010 0.6673
3.500 0.7335 0.01323 0.00568 -0.0782 0.5823 0.6684
3.750 0.7596 0.01328 0.00571 -0.0780 0.5538 0.6696
4.000 0.7810 0.01355 0.00565 -0.0767 0.4762 0.6709
4.250 0.7934 0.01457 0.00605 -0.0743 0.3693 0.6722
4.500 0.8090 0.01551 0.00662 -0.0727 0.2983 0.6737
4.750 0.8279 0.01623 0.00711 -0.0716 0.2538 0.6752
5.000 0.8487 0.01680 0.00754 -0.0708 0.2262 0.6768
5.250 0.8703 0.01730 0.00797 -0.0702 0.2076 0.6786
5.500 0.8923 0.01776 0.00839 -0.0695 0.1941 0.6805
5.750 0.9139 0.01823 0.00882 -0.0688 0.1838 0.6823
6.000 0.9352 0.01867 0.00928 -0.0680 0.1750 0.6839
6.250 0.9561 0.01912 0.00976 -0.0672 0.1680 0.6856
6.500 0.9772 0.01956 0.01023 -0.0664 0.1617 0.6873
6.750 0.9965 0.02010 0.01077 -0.0654 0.1569 0.6892
7.000 1.0173 0.02054 0.01129 -0.0645 0.1529 0.6913
7.250 1.0375 0.02101 0.01182 -0.0636 0.1488 0.6934
7.500 1.0555 0.02154 0.01237 -0.0623 0.1449 0.6957
7.750 1.0709 0.02218 0.01300 -0.0607 0.1414 0.6979
8.000 1.0898 0.02264 0.01359 -0.0596 0.1383 0.6999
8.250 1.1088 0.02318 0.01424 -0.0586 0.1353 0.7022
8.500 1.1272 0.02378 0.01491 -0.0576 0.1321 0.7048
8.750 1.1443 0.02448 0.01565 -0.0565 0.1290 0.7077
9.000 1.1616 0.02523 0.01643 -0.0554 0.1262 0.7110
9.250 1.1807 0.02582 0.01716 -0.0546 0.1234 0.7143
9.500 1.1987 0.02645 0.01792 -0.0536 0.1204 0.7174
9.750 1.2159 0.02715 0.01873 -0.0526 0.1174 0.7210
10.000 1.2319 0.02797 0.01959 -0.0516 0.1147 0.7249
10.250 1.2484 0.02880 0.02049 -0.0506 0.1119 0.7291
10.500 1.2658 0.02950 0.02137 -0.0497 0.1090 0.7329
10.750 1.2821 0.03026 0.02229 -0.0488 0.1058 0.7375
11.000 1.2971 0.03111 0.02324 -0.0479 0.1028 0.7427
11.250 1.3102 0.03215 0.02431 -0.0468 0.1000 0.7479
11.500 1.3260 0.03297 0.02534 -0.0459 0.0970 0.7542
11.750 1.3408 0.03388 0.02641 -0.0451 0.0936 0.7613
12.000 1.3536 0.03487 0.02753 -0.0442 0.0902 0.7692
12.250 1.3640 0.03610 0.02882 -0.0431 0.0873 0.7786
12.500 1.3783 0.03706 0.03003 -0.0423 0.0836 0.7906
12.750 1.3901 0.03816 0.03132 -0.0414 0.0798 0.8058
13.000 1.3984 0.03948 0.03275 -0.0403 0.0766 0.8267
13.250 1.4075 0.04055 0.03408 -0.0389 0.0729 0.8655
13.500 1.4110 0.04162 0.03536 -0.0368 0.0692 1.0000
13.750 1.4184 0.04337 0.03713 -0.0363 0.0654 1.0000
14.000 1.4289 0.04490 0.03882 -0.0358 0.0609 1.0000
14.250 1.4348 0.04685 0.04082 -0.0353 0.0569 1.0000
14.500 1.4412 0.04880 0.04288 -0.0348 0.0530 1.0000
14.750 1.4452 0.05102 0.04518 -0.0344 0.0493 1.0000
15.000 1.4470 0.05350 0.04774 -0.0340 0.0462 1.0000
15.250 1.4492 0.05603 0.05040 -0.0337 0.0430 1.0000
15.500 1.4472 0.05909 0.05354 -0.0335 0.0403 1.0000
15.750 1.4460 0.06215 0.05674 -0.0335 0.0379 1.0000
16.000 1.4429 0.06553 0.06027 -0.0336 0.0355 1.0000
16.250 1.4360 0.06952 0.06436 -0.0341 0.0337 1.0000
16.500 1.4287 0.07374 0.06872 -0.0348 0.0321 1.0000
16.750 1.4211 0.07813 0.07329 -0.0358 0.0305 1.0000
17.000 1.4101 0.08320 0.07851 -0.0372 0.0292 1.0000
17.250 1.3959 0.08901 0.08447 -0.0392 0.0282 1.0000
17.500 1.3784 0.09568 0.09129 -0.0419 0.0276 1.0000
17.750 1.3586 0.10307 0.09884 -0.0453 0.0271 1.0000
18.000 1.3387 0.11079 0.10677 -0.0490 0.0266 1.0000
18.250 1.3157 0.11944 0.11561 -0.0536 0.0264 1.0000
18.500 1.2904 0.12885 0.12521 -0.0587 0.0263 1.0000
18.750 1.2647 0.13856 0.13507 -0.0642 0.0262 1.0000
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Polar data table (+)
Polar graphs
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