S9037 (9%) (s9037-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: S9037 (9%) (s9037-il) Reynolds number: 100,000 Max Cl/Cd: 56.84 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s9037-il-100000.txt Download as CSV file: xf-s9037-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: S9037 (9%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3465 0.10393 0.09910 -0.0327 1.0000 0.0757
-8.500 -0.3590 0.10273 0.09803 -0.0361 1.0000 0.0764
-8.250 -0.3729 0.10132 0.09676 -0.0378 1.0000 0.0767
-8.000 -0.3393 0.09401 0.08937 -0.0330 1.0000 0.0796
-7.750 -0.3352 0.09136 0.08678 -0.0321 1.0000 0.0819
-7.500 -0.3379 0.08908 0.08459 -0.0315 1.0000 0.0845
-7.250 -0.3478 0.08730 0.08292 -0.0305 1.0000 0.0866
-7.000 -0.3638 0.08585 0.08161 -0.0297 1.0000 0.0882
-6.750 -0.3834 0.08439 0.08025 -0.0329 1.0000 0.0897
-6.500 -0.3993 0.08249 0.07829 -0.0383 1.0000 0.0905
-6.250 -0.3955 0.07835 0.07432 -0.0320 1.0000 0.0919
-6.000 -0.3936 0.07612 0.07216 -0.0274 1.0000 0.0941
-5.750 -0.3948 0.07389 0.06997 -0.0261 1.0000 0.0968
-5.500 -0.3953 0.07105 0.06679 -0.0372 1.0000 0.1044
-5.250 -0.3930 0.06699 0.06293 -0.0334 1.0000 0.1058
-5.000 -0.3896 0.06464 0.06065 -0.0298 1.0000 0.1082
-4.750 -0.3827 0.06213 0.05812 -0.0297 1.0000 0.1134
-4.500 -0.3712 0.05823 0.05408 -0.0331 1.0000 0.1212
-4.250 -0.3616 0.05597 0.05182 -0.0320 1.0000 0.1264
-4.000 -0.3346 0.05210 0.04780 -0.0363 0.9969 0.1380
-3.750 -0.2912 0.04814 0.04349 -0.0440 0.9900 0.1627
-3.500 -0.2238 0.03502 0.02862 -0.0521 0.9875 0.0618
-3.250 -0.1808 0.03122 0.02431 -0.0557 0.9828 0.0599
-3.000 -0.1412 0.02823 0.02075 -0.0580 0.9762 0.0580
-2.750 -0.0957 0.02558 0.01745 -0.0607 0.9712 0.0565
-2.500 -0.0572 0.02382 0.01530 -0.0622 0.9637 0.0588
-2.250 -0.0133 0.02232 0.01365 -0.0649 0.9577 0.0713
-2.000 0.0224 0.02103 0.01242 -0.0662 0.9492 0.0964
-1.750 0.0651 0.01933 0.01133 -0.0689 0.9433 0.2060
-1.500 0.0896 0.01721 0.01124 -0.0681 0.9351 0.6574
-1.250 0.1492 0.01664 0.01084 -0.0729 0.9299 1.0000
-1.000 0.1864 0.01679 0.01064 -0.0748 0.9192 1.0000
-0.750 0.2299 0.01689 0.01043 -0.0777 0.9105 1.0000
-0.500 0.2746 0.01690 0.01021 -0.0808 0.9017 1.0000
-0.250 0.3115 0.01695 0.01006 -0.0825 0.8909 1.0000
0.000 0.3534 0.01690 0.00985 -0.0848 0.8822 1.0000
0.250 0.3932 0.01679 0.00961 -0.0866 0.8729 1.0000
0.500 0.4249 0.01678 0.00949 -0.0869 0.8611 1.0000
0.750 0.4575 0.01673 0.00935 -0.0873 0.8499 1.0000
1.000 0.4924 0.01657 0.00910 -0.0879 0.8398 1.0000
1.250 0.5262 0.01636 0.00882 -0.0882 0.8294 1.0000
1.500 0.5543 0.01628 0.00869 -0.0876 0.8163 1.0000
1.750 0.5823 0.01619 0.00855 -0.0869 0.8030 1.0000
2.000 0.6100 0.01610 0.00842 -0.0861 0.7896 1.0000
2.250 0.6375 0.01602 0.00831 -0.0853 0.7758 1.0000
2.500 0.6648 0.01595 0.00820 -0.0845 0.7616 1.0000
2.750 0.6919 0.01588 0.00809 -0.0836 0.7469 1.0000
3.000 0.7190 0.01582 0.00799 -0.0827 0.7317 1.0000
3.250 0.7461 0.01576 0.00791 -0.0818 0.7158 1.0000
3.500 0.7709 0.01583 0.00796 -0.0806 0.6973 1.0000
3.750 0.7964 0.01589 0.00799 -0.0796 0.6788 1.0000
4.000 0.8226 0.01594 0.00799 -0.0787 0.6607 1.0000
4.250 0.8479 0.01608 0.00813 -0.0777 0.6415 1.0000
4.500 0.8725 0.01624 0.00827 -0.0767 0.6208 1.0000
4.750 0.8980 0.01640 0.00836 -0.0757 0.6007 1.0000
5.000 0.9217 0.01663 0.00858 -0.0746 0.5780 1.0000
5.250 0.9459 0.01687 0.00881 -0.0736 0.5559 1.0000
5.500 0.9697 0.01716 0.00906 -0.0725 0.5332 1.0000
5.750 0.9928 0.01751 0.00940 -0.0714 0.5097 1.0000
6.000 1.0163 0.01788 0.00971 -0.0703 0.4868 1.0000
6.250 1.0385 0.01830 0.01015 -0.0692 0.4622 1.0000
6.500 1.0602 0.01877 0.01061 -0.0680 0.4371 1.0000
6.750 1.0815 0.01928 0.01108 -0.0667 0.4118 1.0000
7.000 1.1023 0.01984 0.01157 -0.0654 0.3866 1.0000
7.250 1.1224 0.02045 0.01216 -0.0641 0.3611 1.0000
7.500 1.1416 0.02112 0.01284 -0.0627 0.3353 1.0000
7.750 1.1603 0.02186 0.01357 -0.0613 0.3103 1.0000
8.000 1.1786 0.02267 0.01434 -0.0598 0.2860 1.0000
8.250 1.1961 0.02355 0.01514 -0.0583 0.2626 1.0000
8.500 1.2124 0.02449 0.01612 -0.0566 0.2391 1.0000
8.750 1.2278 0.02551 0.01712 -0.0550 0.2171 1.0000
9.000 1.2424 0.02657 0.01819 -0.0532 0.1961 1.0000
9.250 1.2569 0.02782 0.01936 -0.0515 0.1772 1.0000
9.500 1.2701 0.02912 0.02075 -0.0496 0.1590 1.0000
9.750 1.2826 0.03048 0.02211 -0.0477 0.1428 1.0000
10.000 1.2958 0.03203 0.02368 -0.0459 0.1285 1.0000
10.250 1.3080 0.03368 0.02538 -0.0441 0.1155 1.0000
10.500 1.3188 0.03543 0.02727 -0.0421 0.1039 1.0000
10.750 1.3304 0.03744 0.02938 -0.0404 0.0938 1.0000
11.000 1.3401 0.03937 0.03129 -0.0385 0.0844 1.0000
11.250 1.3429 0.04098 0.03307 -0.0357 0.0769 1.0000
11.500 1.3451 0.04326 0.03555 -0.0332 0.0697 1.0000
11.750 1.3514 0.04571 0.03790 -0.0316 0.0618 1.0000
12.000 1.3411 0.04770 0.04031 -0.0283 0.0573 1.0000
12.250 1.3453 0.05066 0.04312 -0.0270 0.0506 1.0000
12.500 1.3344 0.05337 0.04627 -0.0246 0.0480 1.0000
12.750 1.3268 0.05652 0.04971 -0.0230 0.0449 1.0000
13.000 1.3258 0.05939 0.05255 -0.0222 0.0413 1.0000
13.250 1.2003 0.06213 0.05637 -0.0163 0.0474 1.0000
13.500 1.1803 0.06781 0.06234 -0.0165 0.0465 1.0000
13.750 1.1582 0.07389 0.06869 -0.0174 0.0460 1.0000
14.000 1.1325 0.08049 0.07556 -0.0192 0.0461 1.0000
14.250 1.1038 0.08756 0.08290 -0.0217 0.0470 1.0000
14.500 1.0731 0.09491 0.09048 -0.0250 0.0481 1.0000
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Polar data table (+)
Polar graphs
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