NACA M13 AIRFOIL (m13-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA M13 AIRFOIL (m13-il) Reynolds number: 200,000 Max Cl/Cd: 74.13 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-m13-il-200000.txt Download as CSV file: xf-m13-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: NACA M13 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.4598 0.10480 0.10143 0.0032 1.0000 0.0279
-8.000 -0.4568 0.10270 0.09938 -0.0015 1.0000 0.0286
-7.750 -0.4523 0.10003 0.09675 -0.0071 1.0000 0.0289
-7.500 -0.4405 0.09648 0.09320 -0.0127 1.0000 0.0290
-7.250 -0.4271 0.09261 0.08932 -0.0172 1.0000 0.0291
-7.000 -0.4127 0.08851 0.08523 -0.0211 1.0000 0.0292
-6.750 -0.4134 0.08200 0.07874 -0.0185 1.0000 0.0300
-6.500 -0.4036 0.07829 0.07505 -0.0182 1.0000 0.0308
-6.250 -0.3905 0.07474 0.07149 -0.0200 1.0000 0.0318
-6.000 -0.3749 0.07112 0.06786 -0.0228 1.0000 0.0331
-5.750 -0.3569 0.06739 0.06409 -0.0262 1.0000 0.0348
-5.500 -0.3338 0.06350 0.06013 -0.0307 1.0000 0.0374
-5.250 -0.3005 0.05851 0.05491 -0.0383 1.0000 0.0399
-5.000 -0.2934 0.05555 0.05206 -0.0365 1.0000 0.0418
-4.750 -0.2761 0.05278 0.04926 -0.0373 1.0000 0.0445
-4.500 -0.2400 0.05026 0.04627 -0.0417 1.0000 0.0502
-4.250 -0.2358 0.04638 0.04256 -0.0405 0.9978 0.0515
-4.000 -0.2000 0.04317 0.03929 -0.0445 0.9902 0.0563
-3.750 -0.1532 0.03896 0.03476 -0.0504 0.9824 0.0636
-3.500 -0.1042 0.03724 0.03242 -0.0547 0.9707 0.0736
-3.250 -0.0752 0.03269 0.02801 -0.0575 0.9579 0.0761
-3.000 -0.0399 0.03040 0.02549 -0.0596 0.9431 0.0824
-2.750 -0.0084 0.02781 0.02259 -0.0607 0.9272 0.0890
-2.500 0.0182 0.02624 0.02082 -0.0604 0.9094 0.0952
-2.250 0.0440 0.02436 0.01860 -0.0599 0.8922 0.1021
-2.000 0.0700 0.02345 0.01733 -0.0590 0.8760 0.1141
-1.750 0.0935 0.02167 0.01550 -0.0584 0.8607 0.1185
-1.500 0.1269 0.01863 0.01166 -0.0569 0.8479 0.0772
-1.250 0.1563 0.01655 0.00889 -0.0555 0.8351 0.0620
-1.000 0.1831 0.01580 0.00792 -0.0548 0.8218 0.0608
-0.750 0.2096 0.01484 0.00678 -0.0541 0.8093 0.0607
-0.500 0.2362 0.01419 0.00596 -0.0535 0.7972 0.0611
-0.250 0.2624 0.01335 0.00511 -0.0530 0.7850 0.0628
0.000 0.2890 0.01298 0.00473 -0.0526 0.7726 0.0661
0.250 0.3158 0.01275 0.00445 -0.0522 0.7606 0.0711
0.500 0.3424 0.01237 0.00404 -0.0517 0.7491 0.0744
0.750 0.3690 0.01204 0.00372 -0.0514 0.7380 0.0826
1.000 0.3956 0.01171 0.00340 -0.0510 0.7272 0.1067
1.250 0.4226 0.01149 0.00335 -0.0508 0.7152 0.1712
1.500 0.4552 0.00959 0.00334 -0.0517 0.7037 1.0000
1.750 0.4819 0.00973 0.00334 -0.0514 0.6924 1.0000
2.000 0.5085 0.00987 0.00337 -0.0510 0.6814 1.0000
2.250 0.5352 0.01002 0.00342 -0.0507 0.6704 1.0000
2.500 0.5621 0.01016 0.00350 -0.0505 0.6583 1.0000
2.750 0.5890 0.01032 0.00362 -0.0502 0.6466 1.0000
3.000 0.6159 0.01047 0.00374 -0.0500 0.6351 1.0000
3.250 0.6427 0.01064 0.00386 -0.0497 0.6238 1.0000
3.500 0.6695 0.01081 0.00397 -0.0495 0.6127 1.0000
3.750 0.6965 0.01096 0.00417 -0.0493 0.6007 1.0000
4.000 0.7234 0.01114 0.00438 -0.0491 0.5891 1.0000
4.250 0.7504 0.01133 0.00459 -0.0489 0.5781 1.0000
4.500 0.7773 0.01153 0.00482 -0.0487 0.5676 1.0000
4.750 0.8038 0.01165 0.00501 -0.0484 0.5522 1.0000
5.000 0.8289 0.01160 0.00493 -0.0476 0.5232 1.0000
5.250 0.8542 0.01165 0.00496 -0.0470 0.4913 1.0000
5.500 0.8784 0.01185 0.00503 -0.0462 0.4441 1.0000
5.750 0.8991 0.01263 0.00533 -0.0452 0.3169 1.0000
6.000 0.9067 0.01636 0.00737 -0.0435 0.0503 1.0000
6.250 0.9290 0.01739 0.00853 -0.0427 0.0411 1.0000
6.500 0.9472 0.01901 0.01025 -0.0415 0.0367 1.0000
6.750 0.9669 0.02030 0.01164 -0.0403 0.0350 1.0000
7.000 0.9874 0.02148 0.01289 -0.0392 0.0324 1.0000
7.250 1.0073 0.02279 0.01428 -0.0380 0.0299 1.0000
7.500 1.0271 0.02444 0.01597 -0.0368 0.0288 1.0000
7.750 1.0484 0.02635 0.01793 -0.0356 0.0282 1.0000
8.000 1.0717 0.02851 0.02022 -0.0346 0.0281 1.0000
8.250 1.0962 0.03103 0.02300 -0.0335 0.0289 1.0000
8.500 1.1174 0.03351 0.02566 -0.0326 0.0279 1.0000
8.750 1.1372 0.03655 0.02897 -0.0317 0.0273 1.0000
9.000 1.1533 0.04277 0.03600 -0.0289 0.0345 1.0000
15.000 0.7372 0.16010 0.15684 -0.0432 0.0497 1.0000
15.250 0.7446 0.16394 0.16068 -0.0415 0.0479 1.0000
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Polar data table (+)
Polar graphs
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