S3010-103-84 (s3010-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: S3010-103-84 (s3010-il) Reynolds number: 1,000,000 Max Cl/Cd: 104.17 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s3010-il-1000000-n5.txt Download as CSV file: xf-s3010-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S3010-103-84
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
------ -------- --------- --------- -------- -------- --------
-10.750 -0.7513 0.04135 0.03938 -0.0523 1.0000 0.0062
-10.500 -0.7740 0.03419 0.03183 -0.0560 1.0000 0.0063
-10.250 -0.7735 0.03001 0.02730 -0.0569 1.0000 0.0063
-10.000 -0.7585 0.02684 0.02381 -0.0582 0.9815 0.0064
-9.750 -0.7364 0.02413 0.02077 -0.0599 0.9569 0.0065
-9.500 -0.7186 0.02245 0.01882 -0.0594 0.9355 0.0066
-9.250 -0.7001 0.02107 0.01722 -0.0585 0.9184 0.0067
-9.000 -0.6800 0.01980 0.01572 -0.0578 0.9038 0.0068
-8.750 -0.6581 0.01875 0.01447 -0.0572 0.8907 0.0070
-8.500 -0.6352 0.01778 0.01330 -0.0567 0.8787 0.0071
-8.250 -0.6115 0.01694 0.01229 -0.0563 0.8671 0.0072
-8.000 -0.5869 0.01617 0.01137 -0.0559 0.8557 0.0073
-7.750 -0.5616 0.01554 0.01060 -0.0556 0.8449 0.0074
-7.500 -0.5362 0.01490 0.00983 -0.0553 0.8342 0.0075
-7.250 -0.5101 0.01437 0.00916 -0.0550 0.8232 0.0075
-7.000 -0.4844 0.01368 0.00835 -0.0548 0.8127 0.0076
-6.750 -0.4590 0.01282 0.00735 -0.0545 0.8021 0.0078
-6.500 -0.4327 0.01225 0.00667 -0.0543 0.7910 0.0080
-6.250 -0.4059 0.01179 0.00612 -0.0541 0.7802 0.0081
-6.000 -0.3788 0.01139 0.00565 -0.0540 0.7696 0.0083
-5.750 -0.3515 0.01105 0.00522 -0.0538 0.7585 0.0085
-5.500 -0.3241 0.01070 0.00480 -0.0537 0.7476 0.0087
-5.250 -0.2965 0.01039 0.00442 -0.0536 0.7371 0.0089
-5.000 -0.2688 0.01012 0.00407 -0.0534 0.7262 0.0092
-4.750 -0.2409 0.00988 0.00377 -0.0534 0.7152 0.0096
-4.500 -0.2130 0.00964 0.00347 -0.0533 0.7043 0.0099
-4.250 -0.1850 0.00942 0.00318 -0.0532 0.6934 0.0102
-4.000 -0.1570 0.00924 0.00292 -0.0531 0.6822 0.0104
-3.750 -0.1289 0.00895 0.00258 -0.0530 0.6711 0.0109
-3.500 -0.1008 0.00877 0.00233 -0.0530 0.6598 0.0115
-3.250 -0.0726 0.00862 0.00213 -0.0529 0.6484 0.0121
-3.000 -0.0443 0.00851 0.00196 -0.0529 0.6363 0.0127
-2.750 -0.0160 0.00840 0.00179 -0.0528 0.6243 0.0135
-2.500 0.0124 0.00829 0.00164 -0.0528 0.6119 0.0155
-2.250 0.0406 0.00814 0.00149 -0.0528 0.5993 0.0248
-2.000 0.0686 0.00795 0.00136 -0.0528 0.5863 0.0518
-1.750 0.0967 0.00778 0.00126 -0.0528 0.5732 0.0816
-1.500 0.1249 0.00764 0.00118 -0.0528 0.5603 0.1135
-1.250 0.1531 0.00752 0.00112 -0.0528 0.5475 0.1474
-1.000 0.1813 0.00737 0.00107 -0.0529 0.5351 0.1904
-0.750 0.2093 0.00723 0.00103 -0.0529 0.5226 0.2400
-0.500 0.2373 0.00707 0.00101 -0.0530 0.5100 0.3011
-0.250 0.2652 0.00691 0.00100 -0.0531 0.4968 0.3709
0.000 0.2933 0.00682 0.00100 -0.0531 0.4833 0.4209
0.250 0.3214 0.00678 0.00101 -0.0531 0.4697 0.4621
0.500 0.3494 0.00671 0.00104 -0.0531 0.4569 0.5122
0.750 0.3774 0.00665 0.00107 -0.0531 0.4446 0.5639
1.000 0.4053 0.00661 0.00111 -0.0531 0.4326 0.6122
1.250 0.4331 0.00658 0.00116 -0.0530 0.4206 0.6581
1.500 0.4607 0.00656 0.00122 -0.0529 0.4084 0.7039
1.750 0.4881 0.00653 0.00129 -0.0527 0.3964 0.7524
2.000 0.5149 0.00651 0.00137 -0.0524 0.3847 0.8032
2.250 0.5407 0.00648 0.00145 -0.0518 0.3722 0.8549
2.500 0.5647 0.00647 0.00153 -0.0507 0.3598 0.9103
2.750 0.5952 0.00651 0.00159 -0.0511 0.3454 0.9734
3.000 0.6280 0.00665 0.00167 -0.0521 0.3310 1.0000
3.250 0.6557 0.00681 0.00176 -0.0521 0.3179 1.0000
3.500 0.6833 0.00698 0.00186 -0.0520 0.3036 1.0000
3.750 0.7109 0.00716 0.00198 -0.0520 0.2899 1.0000
4.000 0.7383 0.00735 0.00210 -0.0519 0.2759 1.0000
4.250 0.7658 0.00754 0.00223 -0.0519 0.2634 1.0000
4.500 0.7931 0.00775 0.00238 -0.0518 0.2492 1.0000
4.750 0.8203 0.00796 0.00254 -0.0517 0.2364 1.0000
5.000 0.8474 0.00819 0.00270 -0.0516 0.2225 1.0000
5.250 0.8744 0.00841 0.00287 -0.0515 0.2111 1.0000
5.500 0.9012 0.00866 0.00306 -0.0514 0.1983 1.0000
5.750 0.9280 0.00892 0.00326 -0.0513 0.1859 1.0000
6.000 0.9547 0.00917 0.00346 -0.0511 0.1743 1.0000
6.250 0.9813 0.00942 0.00368 -0.0510 0.1636 1.0000
6.500 1.0076 0.00970 0.00392 -0.0508 0.1525 1.0000
6.750 1.0336 0.01001 0.00417 -0.0506 0.1400 1.0000
7.000 1.0595 0.01034 0.00444 -0.0504 0.1283 1.0000
7.250 1.0851 0.01068 0.00473 -0.0502 0.1174 1.0000
7.500 1.1110 0.01096 0.00500 -0.0500 0.1096 1.0000
7.750 1.1365 0.01129 0.00530 -0.0497 0.1015 1.0000
8.000 1.1613 0.01169 0.00564 -0.0494 0.0907 1.0000
8.250 1.1857 0.01212 0.00602 -0.0490 0.0795 1.0000
8.500 1.2103 0.01250 0.00637 -0.0487 0.0716 1.0000
8.750 1.2349 0.01288 0.00673 -0.0483 0.0657 1.0000
9.000 1.2588 0.01330 0.00713 -0.0479 0.0591 1.0000
9.250 1.2826 0.01372 0.00753 -0.0475 0.0528 1.0000
9.500 1.3056 0.01420 0.00799 -0.0469 0.0469 1.0000
9.750 1.3285 0.01467 0.00844 -0.0464 0.0415 1.0000
10.000 1.3508 0.01517 0.00893 -0.0458 0.0362 1.0000
10.250 1.3721 0.01573 0.00948 -0.0451 0.0313 1.0000
10.500 1.3939 0.01621 0.00997 -0.0444 0.0282 1.0000
10.750 1.4145 0.01678 0.01054 -0.0436 0.0249 1.0000
11.000 1.4348 0.01733 0.01110 -0.0427 0.0219 1.0000
11.250 1.4538 0.01795 0.01173 -0.0417 0.0189 1.0000
11.500 1.4709 0.01866 0.01245 -0.0405 0.0151 1.0000
11.750 1.4858 0.01947 0.01325 -0.0390 0.0110 1.0000
12.000 1.4986 0.02033 0.01413 -0.0372 0.0084 1.0000
12.250 1.5083 0.02109 0.01493 -0.0349 0.0074 1.0000
12.500 1.5172 0.02189 0.01579 -0.0326 0.0067 1.0000
12.750 1.5252 0.02281 0.01677 -0.0304 0.0062 1.0000
13.000 1.5326 0.02385 0.01787 -0.0285 0.0058 1.0000
13.250 1.5394 0.02502 0.01911 -0.0267 0.0055 1.0000
13.500 1.5456 0.02633 0.02048 -0.0251 0.0052 1.0000
13.750 1.5526 0.02767 0.02190 -0.0238 0.0050 1.0000
14.000 1.5586 0.02917 0.02348 -0.0227 0.0049 1.0000
14.250 1.5637 0.03085 0.02525 -0.0218 0.0048 1.0000
14.500 1.5675 0.03274 0.02722 -0.0210 0.0047 1.0000
14.750 1.5701 0.03485 0.02943 -0.0204 0.0045 1.0000
15.000 1.5722 0.03714 0.03181 -0.0201 0.0045 1.0000
15.250 1.5719 0.03979 0.03456 -0.0200 0.0044 1.0000
15.500 1.5708 0.04266 0.03753 -0.0202 0.0043 1.0000
15.750 1.5684 0.04582 0.04078 -0.0206 0.0042 1.0000
16.000 1.5640 0.04936 0.04444 -0.0213 0.0041 1.0000
16.250 1.5574 0.05336 0.04854 -0.0223 0.0041 1.0000
16.500 1.5500 0.05762 0.05292 -0.0236 0.0040 1.0000
16.750 1.5414 0.06226 0.05768 -0.0253 0.0039 1.0000
17.000 1.5318 0.06725 0.06278 -0.0272 0.0039 1.0000
17.250 1.5179 0.07311 0.06878 -0.0297 0.0038 1.0000
17.500 1.5070 0.07868 0.07446 -0.0322 0.0039 1.0000
17.750 1.4901 0.08545 0.08137 -0.0354 0.0038 1.0000
18.000 1.4717 0.09272 0.08878 -0.0390 0.0038 1.0000
18.250 1.4545 0.10000 0.09619 -0.0427 0.0038 1.0000
18.500 1.4348 0.10789 0.10423 -0.0468 0.0037 1.0000
18.750 1.4181 0.11544 0.11190 -0.0509 0.0038 1.0000
19.000 1.4005 0.12329 0.11988 -0.0552 0.0038 1.0000
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Polar data table (+)
Polar graphs
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