NACA M13 AIRFOIL (m13-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA M13 AIRFOIL (m13-il) Reynolds number: 100,000 Max Cl/Cd: 56.83 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-m13-il-100000-n5.txt Download as CSV file: xf-m13-il-100000-n5.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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4637 0.11811 0.11333 0.0018 1.0000 0.0308
-8.750 -0.4605 0.11528 0.11055 -0.0010 1.0000 0.0309
-8.500 -0.4571 0.11226 0.10759 -0.0038 1.0000 0.0310
-8.250 -0.4531 0.10902 0.10440 -0.0067 1.0000 0.0310
-8.000 -0.4480 0.10560 0.10102 -0.0098 1.0000 0.0311
-7.750 -0.4405 0.10094 0.09641 -0.0112 1.0000 0.0313
-7.500 -0.4312 0.09587 0.09134 -0.0074 1.0000 0.0324
-7.250 -0.4236 0.09233 0.08779 -0.0088 1.0000 0.0332
-7.000 -0.4146 0.08879 0.08427 -0.0113 1.0000 0.0342
-6.750 -0.4043 0.08517 0.08068 -0.0144 1.0000 0.0354
-6.500 -0.3915 0.08151 0.07702 -0.0185 1.0000 0.0377
-6.250 -0.3644 0.07801 0.07339 -0.0306 1.0000 0.0401
-6.000 -0.3634 0.07384 0.06936 -0.0255 1.0000 0.0428
-5.750 -0.3466 0.07048 0.06597 -0.0285 1.0000 0.0472
-5.500 -0.3151 0.06650 0.06177 -0.0376 1.0000 0.0502
-5.250 -0.3088 0.06267 0.05805 -0.0353 1.0000 0.0520
-5.000 -0.2925 0.05959 0.05494 -0.0363 1.0000 0.0557
-4.500 -0.2556 0.05305 0.04824 -0.0398 1.0000 0.0636
-4.250 -0.2112 0.04681 0.04148 -0.0461 0.9897 0.0493
-4.000 -0.1781 0.04209 0.03659 -0.0497 0.9765 0.0445
-3.750 -0.1387 0.03811 0.03222 -0.0536 0.9622 0.0473
-3.500 -0.1011 0.03411 0.02781 -0.0566 0.9480 0.0463
-3.250 -0.0642 0.03056 0.02377 -0.0589 0.9338 0.0464
-3.000 -0.0279 0.02745 0.01999 -0.0604 0.9192 0.0492
-2.750 0.0041 0.02506 0.01713 -0.0612 0.9040 0.0489
-2.500 0.0345 0.02306 0.01466 -0.0614 0.8886 0.0491
-2.250 0.0635 0.02143 0.01259 -0.0613 0.8733 0.0495
-2.000 0.0906 0.02049 0.01145 -0.0611 0.8581 0.0519
-1.750 0.1174 0.01985 0.01061 -0.0607 0.8434 0.0549
-1.500 0.1446 0.01882 0.00931 -0.0602 0.8295 0.0550
-1.250 0.1716 0.01794 0.00820 -0.0596 0.8160 0.0549
-1.000 0.1983 0.01720 0.00730 -0.0590 0.8029 0.0552
-0.750 0.2248 0.01658 0.00654 -0.0585 0.7905 0.0557
-0.500 0.2510 0.01606 0.00593 -0.0579 0.7785 0.0565
-0.250 0.2770 0.01563 0.00541 -0.0573 0.7669 0.0580
0.000 0.3035 0.01531 0.00497 -0.0567 0.7550 0.0602
0.250 0.3302 0.01508 0.00469 -0.0563 0.7433 0.0642
0.500 0.3572 0.01493 0.00440 -0.0559 0.7320 0.0731
0.750 0.3841 0.01477 0.00418 -0.0556 0.7214 0.0888
1.000 0.4110 0.01468 0.00407 -0.0553 0.7106 0.1071
1.250 0.4378 0.01446 0.00411 -0.0552 0.6993 0.1919
1.750 0.4978 0.01285 0.00412 -0.0558 0.6783 1.0000
2.000 0.5242 0.01301 0.00418 -0.0555 0.6676 1.0000
2.250 0.5507 0.01318 0.00428 -0.0552 0.6566 1.0000
2.500 0.5772 0.01336 0.00442 -0.0549 0.6460 1.0000
2.750 0.6036 0.01354 0.00454 -0.0545 0.6360 1.0000
3.000 0.6301 0.01373 0.00472 -0.0542 0.6249 1.0000
3.250 0.6566 0.01393 0.00493 -0.0540 0.6139 1.0000
3.500 0.6831 0.01413 0.00517 -0.0537 0.6032 1.0000
3.750 0.7094 0.01434 0.00539 -0.0533 0.5928 1.0000
4.000 0.7358 0.01456 0.00566 -0.0530 0.5813 1.0000
4.250 0.7622 0.01478 0.00601 -0.0528 0.5695 1.0000
4.500 0.7885 0.01502 0.00633 -0.0525 0.5580 1.0000
4.750 0.8148 0.01527 0.00668 -0.0521 0.5469 1.0000
5.000 0.8410 0.01552 0.00704 -0.0518 0.5362 1.0000
5.250 0.8673 0.01580 0.00754 -0.0515 0.5243 1.0000
5.500 0.8919 0.01593 0.00777 -0.0507 0.4979 1.0000
5.750 0.9133 0.01607 0.00773 -0.0492 0.4377 1.0000
6.000 0.9322 0.01679 0.00800 -0.0477 0.3265 1.0000
6.250 0.9362 0.02041 0.00977 -0.0458 0.0613 1.0000
6.500 0.9542 0.02204 0.01136 -0.0446 0.0375 1.0000
6.750 0.9728 0.02344 0.01290 -0.0435 0.0318 1.0000
7.000 0.9913 0.02473 0.01442 -0.0422 0.0283 1.0000
7.250 1.0068 0.02625 0.01606 -0.0408 0.0247 1.0000
7.500 1.0203 0.02801 0.01793 -0.0391 0.0230 1.0000
7.750 1.0359 0.02965 0.01971 -0.0374 0.0221 1.0000
8.000 1.0531 0.03148 0.02166 -0.0358 0.0212 1.0000
8.250 1.0723 0.03337 0.02377 -0.0344 0.0198 1.0000
8.500 1.0918 0.03532 0.02591 -0.0333 0.0181 1.0000
8.750 1.1115 0.03768 0.02849 -0.0321 0.0172 1.0000
9.000 1.1303 0.04039 0.03149 -0.0309 0.0167 1.0000
9.250 1.1462 0.04336 0.03479 -0.0295 0.0164 1.0000
9.500 1.1585 0.04655 0.03836 -0.0279 0.0162 1.0000
9.750 1.1666 0.04993 0.04214 -0.0261 0.0161 1.0000
10.000 1.1701 0.05341 0.04602 -0.0241 0.0161 1.0000
10.250 1.1694 0.05678 0.04973 -0.0221 0.0158 1.0000
10.500 1.1641 0.06005 0.05330 -0.0200 0.0156 1.0000
10.750 1.1534 0.06321 0.05671 -0.0177 0.0154 1.0000
11.000 1.1406 0.06673 0.06047 -0.0164 0.0153 1.0000
11.250 1.1264 0.07071 0.06468 -0.0161 0.0152 1.0000
11.500 1.1108 0.07522 0.06942 -0.0168 0.0152 1.0000
11.750 1.0938 0.08040 0.07482 -0.0184 0.0152 1.0000
12.000 1.0734 0.08669 0.08134 -0.0213 0.0156 1.0000
12.250 1.0502 0.09424 0.08911 -0.0257 0.0160 1.0000
12.500 1.0262 0.10300 0.09806 -0.0313 0.0166 1.0000
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Polar data table (+)
Polar graphs
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