SA7036 (sa7036-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: SA7036 (sa7036-il) Reynolds number: 100,000 Max Cl/Cd: 54.47 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sa7036-il-100000-n5.txt Download as CSV file: xf-sa7036-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: SA7036
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.4085 0.07675 0.07216 -0.0388 1.0000 0.0243
-7.500 -0.4142 0.07331 0.06880 -0.0396 1.0000 0.0240
-7.250 -0.4192 0.06965 0.06518 -0.0407 1.0000 0.0236
-7.000 -0.4242 0.06588 0.06144 -0.0416 1.0000 0.0232
-6.750 -0.4288 0.06186 0.05739 -0.0423 1.0000 0.0229
-6.500 -0.4315 0.05780 0.05326 -0.0427 1.0000 0.0225
-6.250 -0.4316 0.05364 0.04898 -0.0430 1.0000 0.0221
-6.000 -0.4291 0.04911 0.04425 -0.0433 1.0000 0.0217
-5.750 -0.4223 0.04465 0.03950 -0.0435 0.9999 0.0213
-5.500 -0.3921 0.03859 0.03285 -0.0481 0.9943 0.0211
-5.250 -0.3617 0.03378 0.02738 -0.0510 0.9885 0.0211
-5.000 -0.3279 0.03012 0.02305 -0.0534 0.9838 0.0223
-4.750 -0.2949 0.02767 0.01991 -0.0548 0.9782 0.0244
-4.500 -0.2618 0.02488 0.01667 -0.0563 0.9734 0.0255
-4.250 -0.2265 0.02291 0.01442 -0.0581 0.9693 0.0267
-4.000 -0.1953 0.02150 0.01282 -0.0588 0.9628 0.0285
-3.750 -0.1589 0.02047 0.01158 -0.0605 0.9580 0.0332
-3.500 -0.1268 0.01924 0.01024 -0.0613 0.9517 0.0362
-3.250 -0.0922 0.01829 0.00922 -0.0627 0.9457 0.0409
-3.000 -0.0567 0.01743 0.00825 -0.0642 0.9401 0.0511
-2.750 -0.0246 0.01652 0.00750 -0.0652 0.9326 0.0894
-2.500 0.0086 0.01540 0.00707 -0.0668 0.9267 0.2317
-2.250 0.0366 0.01451 0.00688 -0.0672 0.9182 0.4097
-2.000 0.0653 0.01390 0.00673 -0.0670 0.9104 0.5577
-1.750 0.0929 0.01345 0.00661 -0.0661 0.9022 0.6844
-1.500 0.1173 0.01312 0.00651 -0.0642 0.8924 0.7902
-1.250 0.1578 0.01283 0.00625 -0.0654 0.8865 0.8988
-1.000 0.2133 0.01261 0.00588 -0.0707 0.8786 0.9899
-0.750 0.2462 0.01254 0.00562 -0.0716 0.8682 1.0000
-0.500 0.2752 0.01247 0.00537 -0.0717 0.8569 1.0000
-0.250 0.3027 0.01243 0.00518 -0.0714 0.8443 1.0000
0.000 0.3296 0.01240 0.00502 -0.0709 0.8307 1.0000
0.250 0.3566 0.01238 0.00487 -0.0705 0.8167 1.0000
0.500 0.3837 0.01236 0.00473 -0.0700 0.8021 1.0000
0.750 0.4103 0.01237 0.00463 -0.0695 0.7865 1.0000
1.000 0.4368 0.01240 0.00457 -0.0689 0.7700 1.0000
1.250 0.4634 0.01243 0.00451 -0.0684 0.7531 1.0000
1.500 0.4902 0.01248 0.00446 -0.0679 0.7359 1.0000
1.750 0.5170 0.01255 0.00442 -0.0673 0.7184 1.0000
2.000 0.5430 0.01265 0.00445 -0.0667 0.6994 1.0000
2.250 0.5691 0.01277 0.00450 -0.0661 0.6799 1.0000
2.500 0.5952 0.01291 0.00454 -0.0655 0.6605 1.0000
2.750 0.6206 0.01308 0.00464 -0.0649 0.6397 1.0000
3.000 0.6463 0.01327 0.00474 -0.0642 0.6194 1.0000
3.250 0.6715 0.01348 0.00492 -0.0636 0.5982 1.0000
3.500 0.6967 0.01372 0.00507 -0.0629 0.5771 1.0000
3.750 0.7215 0.01397 0.00527 -0.0622 0.5547 1.0000
4.000 0.7462 0.01425 0.00548 -0.0615 0.5329 1.0000
4.250 0.7707 0.01454 0.00576 -0.0608 0.5103 1.0000
4.500 0.7951 0.01486 0.00603 -0.0601 0.4884 1.0000
4.750 0.8192 0.01519 0.00633 -0.0594 0.4664 1.0000
5.000 0.8431 0.01555 0.00666 -0.0587 0.4445 1.0000
5.250 0.8667 0.01594 0.00704 -0.0579 0.4226 1.0000
5.500 0.8901 0.01634 0.00744 -0.0572 0.4003 1.0000
5.750 0.9129 0.01679 0.00784 -0.0563 0.3780 1.0000
6.000 0.9357 0.01724 0.00830 -0.0555 0.3550 1.0000
6.250 0.9580 0.01773 0.00878 -0.0547 0.3327 1.0000
6.500 0.9801 0.01825 0.00933 -0.0538 0.3111 1.0000
6.750 1.0018 0.01880 0.00990 -0.0529 0.2899 1.0000
7.000 1.0230 0.01939 0.01049 -0.0520 0.2691 1.0000
7.250 1.0438 0.02001 0.01113 -0.0510 0.2477 1.0000
7.500 1.0639 0.02068 0.01181 -0.0500 0.2269 1.0000
7.750 1.0836 0.02139 0.01258 -0.0489 0.2058 1.0000
8.000 1.1023 0.02216 0.01337 -0.0478 0.1857 1.0000
8.250 1.1206 0.02298 0.01421 -0.0466 0.1661 1.0000
8.500 1.1381 0.02385 0.01511 -0.0454 0.1473 1.0000
8.750 1.1541 0.02484 0.01610 -0.0440 0.1303 1.0000
9.000 1.1699 0.02585 0.01716 -0.0425 0.1136 1.0000
9.250 1.1843 0.02694 0.01835 -0.0410 0.0985 1.0000
9.500 1.1970 0.02815 0.01961 -0.0393 0.0859 1.0000
9.750 1.2077 0.02946 0.02096 -0.0374 0.0749 1.0000
10.000 1.2151 0.03087 0.02242 -0.0351 0.0666 1.0000
10.250 1.2228 0.03227 0.02397 -0.0328 0.0592 1.0000
10.500 1.2257 0.03396 0.02567 -0.0304 0.0536 1.0000
10.750 1.2321 0.03555 0.02747 -0.0283 0.0478 1.0000
11.000 1.2329 0.03753 0.02952 -0.0262 0.0438 1.0000
11.250 1.2356 0.03956 0.03173 -0.0244 0.0395 1.0000
11.500 1.2370 0.04166 0.03399 -0.0229 0.0355 1.0000
11.750 1.2322 0.04443 0.03679 -0.0216 0.0328 1.0000
12.000 1.2335 0.04688 0.03952 -0.0207 0.0290 1.0000
12.250 1.2310 0.04970 0.04254 -0.0203 0.0261 1.0000
12.500 1.2233 0.05324 0.04616 -0.0203 0.0241 1.0000
12.750 1.2183 0.05689 0.05001 -0.0204 0.0227 1.0000
13.000 1.2132 0.06076 0.05414 -0.0209 0.0211 1.0000
13.250 1.2060 0.06506 0.05864 -0.0219 0.0198 1.0000
13.500 1.1973 0.06976 0.06351 -0.0235 0.0187 1.0000
13.750 1.1876 0.07482 0.06872 -0.0257 0.0178 1.0000
14.000 1.1775 0.08017 0.07422 -0.0279 0.0175 1.0000
14.250 1.1658 0.08605 0.08024 -0.0308 0.0169 1.0000
14.500 1.1538 0.09217 0.08649 -0.0337 0.0165 1.0000
14.750 1.1414 0.09882 0.09331 -0.0371 0.0162 1.0000
15.000 1.1284 0.10596 0.10066 -0.0410 0.0160 1.0000
15.250 1.1147 0.11352 0.10841 -0.0453 0.0159 1.0000
15.500 1.1004 0.12151 0.11658 -0.0498 0.0158 1.0000
15.750 1.0862 0.12984 0.12506 -0.0547 0.0159 1.0000
16.000 1.0722 0.13842 0.13376 -0.0597 0.0161 1.0000
16.250 1.0576 0.14761 0.14307 -0.0651 0.0162 1.0000
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Polar data table (+)
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