S3014-095-85 (s3014-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: S3014-095-85 (s3014-il) Reynolds number: 50,000 Max Cl/Cd: 36.37 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s3014-il-50000-n5.txt Download as CSV file: xf-s3014-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S3014-095-85
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4267 0.09823 0.09142 -0.0236 1.0000 0.0605
-8.750 -0.4262 0.09398 0.08724 -0.0258 1.0000 0.0580
-8.250 -0.4447 0.08290 0.07637 -0.0363 1.0000 0.0519
-8.000 -0.4430 0.07909 0.07262 -0.0375 1.0000 0.0512
-7.750 -0.4425 0.07495 0.06851 -0.0394 1.0000 0.0505
-7.500 -0.4433 0.07069 0.06426 -0.0412 1.0000 0.0498
-7.250 -0.4448 0.06648 0.06003 -0.0426 1.0000 0.0491
-7.000 -0.4468 0.06247 0.05597 -0.0433 1.0000 0.0485
-6.750 -0.4497 0.05865 0.05204 -0.0431 1.0000 0.0479
-6.500 -0.4517 0.05504 0.04828 -0.0423 1.0000 0.0474
-6.250 -0.4522 0.05154 0.04456 -0.0411 1.0000 0.0470
-6.000 -0.4500 0.04819 0.04093 -0.0396 1.0000 0.0468
-5.750 -0.4448 0.04501 0.03741 -0.0381 1.0000 0.0468
-5.500 -0.4366 0.04213 0.03415 -0.0367 1.0000 0.0477
-5.250 -0.4257 0.03942 0.03098 -0.0352 1.0000 0.0493
-5.000 -0.4122 0.03690 0.02794 -0.0337 1.0000 0.0509
-4.750 -0.3964 0.03464 0.02518 -0.0323 1.0000 0.0517
-4.500 -0.3787 0.03258 0.02267 -0.0309 1.0000 0.0522
-4.250 -0.3602 0.03062 0.02045 -0.0296 1.0000 0.0532
-4.000 -0.3302 0.02883 0.01839 -0.0305 0.9953 0.0549
-3.750 -0.2963 0.02731 0.01664 -0.0318 0.9889 0.0576
-3.500 -0.2606 0.02604 0.01510 -0.0332 0.9828 0.0614
-3.250 -0.2274 0.02500 0.01391 -0.0344 0.9756 0.0688
-3.000 -0.1896 0.02407 0.01286 -0.0365 0.9695 0.0825
-2.750 -0.1567 0.02301 0.01177 -0.0376 0.9617 0.1077
-2.500 -0.1213 0.02150 0.01113 -0.0400 0.9557 0.2509
-2.250 -0.0987 0.02004 0.01110 -0.0394 0.9474 0.5184
-2.000 -0.0413 0.01901 0.01107 -0.0422 0.9459 0.8928
-1.750 0.0281 0.01905 0.01052 -0.0506 0.9429 1.0000
-1.500 0.0615 0.01920 0.01030 -0.0521 0.9325 1.0000
-1.250 0.0975 0.01936 0.01011 -0.0541 0.9230 1.0000
-1.000 0.1374 0.01951 0.00996 -0.0567 0.9147 1.0000
-0.750 0.1674 0.01968 0.00991 -0.0573 0.9034 1.0000
-0.500 0.1980 0.01987 0.00988 -0.0581 0.8925 1.0000
-0.250 0.2302 0.02003 0.00987 -0.0589 0.8822 1.0000
0.000 0.2640 0.02017 0.00985 -0.0600 0.8723 1.0000
0.250 0.2905 0.02036 0.00992 -0.0597 0.8600 1.0000
0.500 0.3172 0.02054 0.00999 -0.0594 0.8477 1.0000
0.750 0.3443 0.02071 0.01007 -0.0591 0.8355 1.0000
1.000 0.3717 0.02085 0.01014 -0.0588 0.8230 1.0000
1.250 0.3990 0.02096 0.01019 -0.0583 0.8104 1.0000
1.500 0.4257 0.02106 0.01023 -0.0577 0.7973 1.0000
1.750 0.4518 0.02113 0.01027 -0.0569 0.7836 1.0000
2.000 0.4771 0.02120 0.01034 -0.0559 0.7692 1.0000
2.250 0.5018 0.02127 0.01039 -0.0548 0.7542 1.0000
2.500 0.5262 0.02132 0.01044 -0.0536 0.7387 1.0000
2.750 0.5508 0.02136 0.01048 -0.0524 0.7227 1.0000
3.000 0.5755 0.02137 0.01053 -0.0512 0.7064 1.0000
3.250 0.6007 0.02135 0.01052 -0.0500 0.6899 1.0000
3.500 0.6257 0.02133 0.01052 -0.0487 0.6728 1.0000
3.750 0.6487 0.02144 0.01067 -0.0474 0.6529 1.0000
4.000 0.6734 0.02145 0.01073 -0.0461 0.6336 1.0000
4.250 0.6972 0.02154 0.01085 -0.0447 0.6125 1.0000
4.500 0.7214 0.02162 0.01094 -0.0434 0.5906 1.0000
4.750 0.7445 0.02181 0.01114 -0.0420 0.5665 1.0000
5.000 0.7678 0.02200 0.01138 -0.0407 0.5420 1.0000
5.250 0.7908 0.02225 0.01161 -0.0393 0.5165 1.0000
5.500 0.8131 0.02259 0.01193 -0.0380 0.4899 1.0000
5.750 0.8346 0.02302 0.01235 -0.0366 0.4627 1.0000
6.000 0.8557 0.02353 0.01283 -0.0353 0.4357 1.0000
6.250 0.8764 0.02410 0.01345 -0.0340 0.4095 1.0000
6.500 0.8967 0.02475 0.01407 -0.0327 0.3845 1.0000
6.750 0.9168 0.02544 0.01472 -0.0314 0.3610 1.0000
7.000 0.9363 0.02622 0.01554 -0.0302 0.3378 1.0000
7.250 0.9557 0.02704 0.01636 -0.0290 0.3165 1.0000
7.500 0.9746 0.02793 0.01735 -0.0277 0.2958 1.0000
7.750 0.9934 0.02885 0.01825 -0.0265 0.2770 1.0000
8.000 1.0115 0.02985 0.01938 -0.0253 0.2582 1.0000
8.250 1.0291 0.03088 0.02050 -0.0241 0.2406 1.0000
8.500 1.0463 0.03197 0.02167 -0.0228 0.2244 1.0000
8.750 1.0627 0.03310 0.02287 -0.0215 0.2090 1.0000
9.000 1.0786 0.03431 0.02419 -0.0202 0.1946 1.0000
9.250 1.0931 0.03557 0.02562 -0.0187 0.1806 1.0000
9.500 1.1070 0.03694 0.02715 -0.0173 0.1676 1.0000
9.750 1.1186 0.03836 0.02874 -0.0157 0.1549 1.0000
10.000 1.1287 0.03990 0.03046 -0.0140 0.1429 1.0000
10.250 1.1370 0.04156 0.03228 -0.0123 0.1317 1.0000
10.500 1.1410 0.04321 0.03405 -0.0102 0.1212 1.0000
10.750 1.1440 0.04493 0.03578 -0.0081 0.1117 1.0000
11.000 1.1413 0.04703 0.03811 -0.0061 0.1017 1.0000
11.250 1.1360 0.04943 0.04068 -0.0045 0.0922 1.0000
11.500 1.1279 0.05195 0.04325 -0.0034 0.0836 1.0000
11.750 1.1190 0.05482 0.04618 -0.0030 0.0757 1.0000
12.000 1.1107 0.05838 0.04995 -0.0030 0.0687 1.0000
12.250 1.1008 0.06198 0.05356 -0.0036 0.0627 1.0000
12.500 1.0919 0.06646 0.05834 -0.0043 0.0575 1.0000
12.750 1.0823 0.07092 0.06290 -0.0056 0.0532 1.0000
13.000 1.0747 0.07526 0.06722 -0.0069 0.0504 1.0000
13.250 1.0630 0.08104 0.07334 -0.0089 0.0482 1.0000
13.500 1.0491 0.08732 0.07987 -0.0117 0.0462 1.0000
13.750 1.0350 0.09397 0.08674 -0.0148 0.0451 1.0000
14.000 1.0185 0.10153 0.09450 -0.0186 0.0446 1.0000
14.250 0.9966 0.11100 0.10419 -0.0237 0.0455 1.0000
14.500 0.9710 0.12213 0.11540 -0.0298 0.0474 1.0000
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Polar data table (+)
Polar graphs
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