S9000 (9%) (s9000-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: S9000 (9%) (s9000-il) Reynolds number: 1,000,000 Max Cl/Cd: 108.18 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s9000-il-1000000.txt Download as CSV file: xf-s9000-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: S9000 (9%)
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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4398 0.08479 0.08319 -0.0271 1.0000 0.0092
-8.500 -0.4429 0.08096 0.07939 -0.0283 1.0000 0.0094
-8.250 -0.4485 0.07714 0.07560 -0.0294 1.0000 0.0095
-8.000 -0.4593 0.07338 0.07188 -0.0300 1.0000 0.0096
-7.750 -0.4758 0.07013 0.06869 -0.0297 1.0000 0.0095
-7.500 -0.4854 0.06469 0.06325 -0.0345 1.0000 0.0094
-7.250 -0.4872 0.05763 0.05613 -0.0405 0.9993 0.0095
-7.000 -0.4632 0.04708 0.04535 -0.0521 0.9960 0.0099
-6.750 -0.4349 0.03839 0.03627 -0.0582 0.9934 0.0109
-6.500 -0.4085 0.03338 0.03084 -0.0618 0.9895 0.0110
-6.250 -0.3526 0.01080 0.00783 -0.0688 0.9842 0.0120
-6.000 -0.3259 0.00913 0.00599 -0.0700 0.9809 0.0125
-5.750 -0.3283 0.01481 0.01046 -0.0685 0.9805 0.0066
-5.500 -0.2987 0.01202 0.00722 -0.0688 0.9770 0.0056
-5.250 -0.2652 0.01110 0.00618 -0.0700 0.9747 0.0055
-5.000 -0.2304 0.01022 0.00519 -0.0715 0.9729 0.0055
-4.750 -0.1949 0.00951 0.00440 -0.0732 0.9712 0.0055
-4.500 -0.1670 0.00892 0.00374 -0.0732 0.9647 0.0057
-4.250 -0.1350 0.00843 0.00319 -0.0739 0.9595 0.0061
-4.000 -0.1046 0.00805 0.00276 -0.0743 0.9523 0.0070
-3.750 -0.0730 0.00754 0.00224 -0.0749 0.9446 0.0149
-3.500 -0.0430 0.00720 0.00197 -0.0753 0.9343 0.0331
-3.250 -0.0130 0.00693 0.00175 -0.0757 0.9227 0.0530
-3.000 0.0156 0.00663 0.00155 -0.0759 0.9086 0.0924
-2.750 0.0428 0.00625 0.00139 -0.0758 0.8920 0.1635
-2.500 0.0697 0.00598 0.00126 -0.0757 0.8742 0.2269
-2.250 0.0965 0.00577 0.00115 -0.0755 0.8573 0.2866
-2.000 0.1233 0.00557 0.00107 -0.0753 0.8409 0.3509
-1.750 0.1501 0.00537 0.00101 -0.0751 0.8242 0.4179
-1.500 0.1768 0.00515 0.00096 -0.0749 0.8070 0.4984
-1.250 0.2033 0.00497 0.00093 -0.0746 0.7894 0.5747
-1.000 0.2297 0.00482 0.00092 -0.0742 0.7706 0.6520
-0.750 0.2562 0.00476 0.00094 -0.0738 0.7505 0.7102
-0.500 0.2829 0.00477 0.00095 -0.0734 0.7315 0.7442
-0.250 0.3096 0.00480 0.00097 -0.0730 0.7130 0.7730
0.000 0.3363 0.00483 0.00099 -0.0726 0.6935 0.7955
0.500 0.3894 0.00497 0.00104 -0.0718 0.6521 0.8323
0.750 0.4153 0.00506 0.00108 -0.0712 0.6269 0.8508
1.000 0.4411 0.00516 0.00112 -0.0707 0.6025 0.8683
1.250 0.4671 0.00525 0.00117 -0.0701 0.5809 0.8840
1.500 0.4924 0.00533 0.00122 -0.0694 0.5603 0.9015
1.750 0.5166 0.00542 0.00127 -0.0685 0.5392 0.9199
2.000 0.5398 0.00551 0.00133 -0.0673 0.5161 0.9413
2.250 0.5649 0.00559 0.00136 -0.0666 0.4947 0.9670
2.500 0.5995 0.00574 0.00141 -0.0681 0.4677 0.9991
2.750 0.6264 0.00596 0.00150 -0.0680 0.4385 1.0000
3.000 0.6533 0.00617 0.00161 -0.0679 0.4129 1.0000
3.250 0.6803 0.00637 0.00172 -0.0678 0.3895 1.0000
3.500 0.7071 0.00659 0.00184 -0.0676 0.3650 1.0000
3.750 0.7337 0.00682 0.00197 -0.0675 0.3425 1.0000
4.000 0.7605 0.00703 0.00211 -0.0673 0.3208 1.0000
4.250 0.7868 0.00731 0.00227 -0.0671 0.2944 1.0000
4.500 0.8126 0.00762 0.00246 -0.0668 0.2644 1.0000
4.750 0.8387 0.00790 0.00265 -0.0666 0.2426 1.0000
5.000 0.8650 0.00816 0.00284 -0.0664 0.2230 1.0000
5.250 0.8910 0.00845 0.00305 -0.0662 0.2040 1.0000
5.500 0.9170 0.00874 0.00327 -0.0659 0.1865 1.0000
5.750 0.9429 0.00903 0.00351 -0.0656 0.1691 1.0000
6.000 0.9684 0.00936 0.00376 -0.0653 0.1506 1.0000
6.250 0.9936 0.00972 0.00404 -0.0650 0.1340 1.0000
6.500 1.0190 0.01005 0.00432 -0.0646 0.1195 1.0000
6.750 1.0439 0.01043 0.00464 -0.0643 0.1018 1.0000
7.000 1.0683 0.01086 0.00498 -0.0638 0.0853 1.0000
7.250 1.0928 0.01127 0.00534 -0.0633 0.0727 1.0000
7.500 1.1175 0.01165 0.00570 -0.0629 0.0629 1.0000
7.750 1.1417 0.01207 0.00608 -0.0624 0.0533 1.0000
8.000 1.1656 0.01252 0.00651 -0.0619 0.0449 1.0000
8.250 1.1894 0.01296 0.00693 -0.0614 0.0388 1.0000
8.500 1.2135 0.01337 0.00735 -0.0609 0.0338 1.0000
8.750 1.2366 0.01386 0.00781 -0.0602 0.0282 1.0000
9.000 1.2601 0.01428 0.00826 -0.0597 0.0238 1.0000
9.250 1.2821 0.01487 0.00881 -0.0589 0.0180 1.0000
9.500 1.3036 0.01549 0.00941 -0.0581 0.0139 1.0000
9.750 1.3255 0.01605 0.01002 -0.0573 0.0117 1.0000
10.000 1.3462 0.01671 0.01070 -0.0563 0.0099 1.0000
10.250 1.3666 0.01737 0.01143 -0.0553 0.0086 1.0000
10.500 1.3877 0.01792 0.01205 -0.0544 0.0078 1.0000
10.750 1.4072 0.01859 0.01275 -0.0534 0.0069 1.0000
11.000 1.4241 0.01949 0.01373 -0.0519 0.0059 1.0000
11.250 1.4439 0.02004 0.01434 -0.0509 0.0053 1.0000
11.500 1.4611 0.02078 0.01514 -0.0496 0.0043 1.0000
11.750 1.4753 0.02174 0.01619 -0.0478 0.0034 1.0000
12.000 1.4886 0.02267 0.01717 -0.0459 0.0026 1.0000
12.250 1.4919 0.02403 0.01867 -0.0425 0.0022 1.0000
12.500 1.5001 0.02498 0.01972 -0.0399 0.0019 1.0000
12.750 1.5059 0.02611 0.02096 -0.0372 0.0019 1.0000
13.000 1.5106 0.02735 0.02231 -0.0345 0.0017 1.0000
13.250 1.5139 0.02875 0.02382 -0.0321 0.0017 1.0000
13.500 1.5152 0.03037 0.02556 -0.0298 0.0016 1.0000
13.750 1.5150 0.03225 0.02756 -0.0278 0.0015 1.0000
14.000 1.5129 0.03442 0.02987 -0.0261 0.0015 1.0000
14.250 1.5076 0.03711 0.03269 -0.0247 0.0014 1.0000
14.500 1.5029 0.03998 0.03570 -0.0240 0.0014 1.0000
14.750 1.4901 0.04407 0.03996 -0.0240 0.0014 1.0000
15.000 1.4844 0.04768 0.04370 -0.0245 0.0014 1.0000
15.250 1.4701 0.05280 0.04899 -0.0259 0.0014 1.0000
15.500 1.4545 0.05857 0.05492 -0.0282 0.0013 1.0000
15.750 1.4357 0.06539 0.06191 -0.0314 0.0013 1.0000
16.000 1.4214 0.07181 0.06848 -0.0347 0.0013 1.0000
16.250 1.4005 0.07989 0.07671 -0.0390 0.0013 1.0000
16.500 1.3830 0.08760 0.08458 -0.0432 0.0014 1.0000
16.750 1.3577 0.09724 0.09437 -0.0486 0.0014 1.0000
17.000 1.3355 0.10649 0.10376 -0.0538 0.0014 1.0000
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