NACA M20 AIRFOIL (m20-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA M20 AIRFOIL (m20-il) Reynolds number: 200,000 Max Cl/Cd: 77.95 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-m20-il-200000-n5.txt Download as CSV file: xf-m20-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA M20 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3436 0.10732 0.10357 -0.0025 0.7453 0.0221
-8.000 -0.3388 0.10455 0.10078 -0.0056 0.7378 0.0222
-7.750 -0.3350 0.10186 0.09807 -0.0093 0.7301 0.0223
-7.500 -0.3254 0.09861 0.09477 -0.0138 0.7234 0.0224
-7.250 -0.3135 0.09489 0.09100 -0.0172 0.7165 0.0224
-7.000 -0.3002 0.09108 0.08711 -0.0204 0.7105 0.0225
-6.750 -0.2887 0.08650 0.08251 -0.0226 0.7040 0.0226
-6.500 -0.2825 0.08231 0.07831 -0.0198 0.6978 0.0232
-6.250 -0.2698 0.07922 0.07516 -0.0208 0.6915 0.0239
-6.000 -0.2544 0.07646 0.07234 -0.0226 0.6850 0.0257
-5.750 -0.2219 0.07443 0.07014 -0.0303 0.6791 0.0298
-5.500 -0.1967 0.07115 0.06673 -0.0348 0.6728 0.0301
-5.250 -0.1734 0.06767 0.06311 -0.0377 0.6674 0.0302
-5.000 -0.1493 0.06429 0.05959 -0.0403 0.6616 0.0303
-4.750 -0.1315 0.05894 0.05414 -0.0425 0.6562 0.0309
-4.250 -0.0982 0.05281 0.04788 -0.0432 0.6446 0.0328
-4.000 -0.0754 0.05030 0.04526 -0.0444 0.6390 0.0344
-3.750 -0.0497 0.04792 0.04273 -0.0459 0.6336 0.0373
-3.500 -0.0041 0.04685 0.04124 -0.0492 0.6275 0.0419
-3.250 0.0227 0.04421 0.03837 -0.0500 0.6223 0.0420
-3.000 0.0458 0.03999 0.03396 -0.0510 0.6170 0.0426
-2.750 0.0655 0.03731 0.03124 -0.0514 0.6113 0.0438
-2.500 0.0877 0.03574 0.02959 -0.0516 0.6063 0.0461
-2.250 0.1150 0.03410 0.02781 -0.0521 0.6002 0.0497
-1.750 0.1776 0.02886 0.02182 -0.0525 0.5904 0.0408
-1.500 0.2045 0.02687 0.01966 -0.0527 0.5846 0.0398
-1.250 0.2335 0.02515 0.01764 -0.0527 0.5796 0.0405
-1.000 0.2618 0.02358 0.01578 -0.0526 0.5748 0.0407
-0.750 0.2897 0.02198 0.01396 -0.0527 0.5690 0.0398
-0.500 0.3179 0.02055 0.01226 -0.0526 0.5639 0.0391
-0.250 0.3464 0.01926 0.01069 -0.0525 0.5591 0.0387
0.000 0.3751 0.01813 0.00932 -0.0524 0.5538 0.0386
0.250 0.4035 0.01723 0.00817 -0.0524 0.5490 0.0388
0.500 0.4318 0.01652 0.00726 -0.0523 0.5441 0.0393
0.750 0.4600 0.01595 0.00656 -0.0523 0.5385 0.0399
1.000 0.4878 0.01565 0.00614 -0.0523 0.5338 0.0414
1.250 0.5156 0.01530 0.00570 -0.0523 0.5292 0.0423
1.500 0.5432 0.01486 0.00525 -0.0522 0.5241 0.0425
1.750 0.5703 0.01452 0.00486 -0.0521 0.5194 0.0429
2.000 0.5973 0.01425 0.00458 -0.0520 0.5149 0.0434
2.250 0.6244 0.01406 0.00441 -0.0520 0.5098 0.0444
2.500 0.6516 0.01395 0.00429 -0.0519 0.5055 0.0459
2.750 0.6787 0.01390 0.00421 -0.0519 0.5015 0.0481
3.000 0.7061 0.01387 0.00420 -0.0519 0.4965 0.0517
3.250 0.7332 0.01385 0.00422 -0.0518 0.4918 0.0606
3.500 0.7600 0.01381 0.00429 -0.0518 0.4881 0.1179
4.000 0.8451 0.01257 0.00471 -0.0587 0.4782 1.0000
4.250 0.8709 0.01273 0.00482 -0.0584 0.4743 1.0000
4.500 0.8969 0.01291 0.00498 -0.0582 0.4703 1.0000
4.750 0.9228 0.01309 0.00520 -0.0580 0.4660 1.0000
5.000 0.9487 0.01327 0.00538 -0.0578 0.4619 1.0000
5.250 0.9744 0.01347 0.00554 -0.0575 0.4580 1.0000
5.500 1.0002 0.01365 0.00582 -0.0574 0.4527 1.0000
5.750 1.0259 0.01384 0.00606 -0.0572 0.4478 1.0000
6.000 1.0515 0.01406 0.00626 -0.0569 0.4434 1.0000
6.250 1.0769 0.01422 0.00652 -0.0567 0.4347 1.0000
6.500 1.1017 0.01434 0.00668 -0.0564 0.4203 1.0000
6.750 1.1260 0.01451 0.00684 -0.0560 0.4032 1.0000
7.000 1.1498 0.01475 0.00706 -0.0556 0.3839 1.0000
7.250 1.1729 0.01509 0.00736 -0.0552 0.3562 1.0000
7.500 1.1926 0.01577 0.00785 -0.0544 0.3024 1.0000
7.750 1.1952 0.01834 0.00953 -0.0523 0.1710 1.0000
8.000 1.1873 0.02164 0.01208 -0.0492 0.0397 1.0000
8.250 1.1974 0.02300 0.01341 -0.0474 0.0281 1.0000
8.500 1.2108 0.02398 0.01453 -0.0460 0.0246 1.0000
8.750 1.2201 0.02519 0.01586 -0.0443 0.0220 1.0000
9.000 1.2226 0.02670 0.01753 -0.0420 0.0205 1.0000
9.250 1.2220 0.02879 0.01980 -0.0403 0.0194 1.0000
9.500 1.2270 0.03066 0.02180 -0.0393 0.0187 1.0000
9.750 1.2312 0.03274 0.02401 -0.0386 0.0179 1.0000
10.000 1.2339 0.03505 0.02645 -0.0380 0.0169 1.0000
10.250 1.2350 0.03760 0.02912 -0.0375 0.0160 1.0000
10.500 1.2339 0.04043 0.03207 -0.0370 0.0155 1.0000
10.750 1.2317 0.04341 0.03516 -0.0366 0.0150 1.0000
11.000 1.2289 0.04648 0.03832 -0.0362 0.0147 1.0000
11.250 1.2258 0.04959 0.04151 -0.0358 0.0143 1.0000
11.500 1.2225 0.05270 0.04472 -0.0353 0.0139 1.0000
11.750 1.2195 0.05574 0.04783 -0.0347 0.0136 1.0000
12.000 1.2163 0.05867 0.05081 -0.0339 0.0132 1.0000
12.250 1.2152 0.06119 0.05333 -0.0324 0.0127 1.0000
12.500 1.2214 0.06332 0.05558 -0.0320 0.0123 1.0000
12.750 1.2275 0.06546 0.05782 -0.0316 0.0117 1.0000
13.000 1.2340 0.06743 0.05987 -0.0307 0.0113 1.0000
13.250 1.2418 0.06921 0.06171 -0.0296 0.0109 1.0000
13.500 1.2502 0.07091 0.06350 -0.0284 0.0106 1.0000
13.750 1.2587 0.07269 0.06539 -0.0273 0.0103 1.0000
14.000 1.2669 0.07457 0.06738 -0.0262 0.0101 1.0000
14.250 1.2746 0.07662 0.06955 -0.0253 0.0098 1.0000
14.500 1.2807 0.07893 0.07199 -0.0246 0.0096 1.0000
14.750 1.2847 0.08156 0.07475 -0.0242 0.0094 1.0000
15.000 1.2874 0.08438 0.07768 -0.0241 0.0092 1.0000
15.250 1.2901 0.08724 0.08062 -0.0238 0.0089 1.0000
15.500 1.2894 0.09078 0.08433 -0.0235 0.0086 1.0000
15.750 1.2829 0.09517 0.08897 -0.0247 0.0085 1.0000
16.000 1.2762 0.09976 0.09380 -0.0260 0.0083 1.0000
16.250 1.2690 0.10457 0.09884 -0.0273 0.0082 1.0000
16.500 1.2609 0.10964 0.10413 -0.0289 0.0081 1.0000
16.750 1.2515 0.11504 0.10975 -0.0309 0.0081 1.0000
17.000 1.2409 0.12083 0.11575 -0.0332 0.0080 1.0000
17.250 1.2295 0.12696 0.12208 -0.0360 0.0080 1.0000
17.500 1.2175 0.13347 0.12878 -0.0393 0.0080 1.0000
17.750 1.2051 0.14032 0.13582 -0.0430 0.0080 1.0000
18.000 1.1923 0.14756 0.14324 -0.0471 0.0080 1.0000
18.250 1.1793 0.15519 0.15104 -0.0517 0.0080 1.0000
18.500 1.1665 0.16318 0.15919 -0.0566 0.0081 1.0000
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