NACA M9 AIRFOIL (m9-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA M9 AIRFOIL (m9-il) Reynolds number: 1,000,000 Max Cl/Cd: 99.52 at α=10° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-m9-il-1000000.txt Download as CSV file: xf-m9-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: NACA M9 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.2528 0.10615 0.10373 0.0068 0.6664 0.0163
-9.500 -0.2463 0.10257 0.10014 0.0054 0.6607 0.0169
-9.000 -0.5351 0.03624 0.03302 -0.0510 0.6959 0.0148
-8.750 -0.5201 0.02785 0.02413 -0.0573 0.6908 0.0152
-8.500 -0.4978 0.02428 0.02030 -0.0593 0.6852 0.0157
-8.250 -0.4731 0.02218 0.01803 -0.0601 0.6788 0.0162
-8.000 -0.4478 0.02055 0.01623 -0.0605 0.6721 0.0167
-7.750 -0.4221 0.01900 0.01451 -0.0608 0.6659 0.0173
-7.500 -0.3959 0.01774 0.01307 -0.0608 0.6588 0.0178
-7.250 -0.3693 0.01671 0.01187 -0.0607 0.6517 0.0182
-7.000 -0.3435 0.01535 0.01037 -0.0606 0.6436 0.0192
-6.750 -0.3163 0.01465 0.00956 -0.0603 0.6348 0.0200
-6.500 -0.2889 0.01400 0.00882 -0.0601 0.6248 0.0209
-6.250 -0.2613 0.01346 0.00815 -0.0598 0.6147 0.0217
-6.000 -0.2343 0.01275 0.00732 -0.0594 0.6033 0.0229
-5.750 -0.2065 0.01237 0.00687 -0.0591 0.5911 0.0241
-5.500 -0.1785 0.01209 0.00650 -0.0587 0.5787 0.0254
-5.250 -0.1508 0.01174 0.00603 -0.0583 0.5659 0.0266
-4.750 -0.0951 0.01120 0.00533 -0.0576 0.5403 0.0296
-4.500 -0.0669 0.01104 0.00508 -0.0573 0.5290 0.0308
-4.250 -0.0392 0.01071 0.00466 -0.0569 0.5183 0.0328
-4.000 -0.0110 0.01056 0.00448 -0.0565 0.5091 0.0345
-3.750 0.0173 0.01045 0.00429 -0.0562 0.4999 0.0361
-3.500 0.0453 0.01021 0.00396 -0.0558 0.4910 0.0378
-3.250 0.0734 0.01005 0.00377 -0.0555 0.4821 0.0399
-3.000 0.1017 0.00995 0.00362 -0.0552 0.4739 0.0418
-2.750 0.1301 0.00989 0.00348 -0.0548 0.4663 0.0432
-2.500 0.1582 0.00964 0.00320 -0.0545 0.4597 0.0462
-2.250 0.1864 0.00956 0.00307 -0.0542 0.4531 0.0485
-2.000 0.2148 0.00948 0.00296 -0.0539 0.4476 0.0506
-1.750 0.2431 0.00931 0.00276 -0.0535 0.4417 0.0542
-1.500 0.2713 0.00925 0.00265 -0.0532 0.4352 0.0576
-1.250 0.2997 0.00918 0.00257 -0.0529 0.4305 0.0604
-1.000 0.3280 0.00904 0.00243 -0.0526 0.4258 0.0665
-0.750 0.3563 0.00901 0.00237 -0.0523 0.4211 0.0705
-0.500 0.3844 0.00893 0.00230 -0.0520 0.4167 0.0782
-0.250 0.4129 0.00890 0.00227 -0.0518 0.4126 0.0830
0.000 0.4410 0.00880 0.00219 -0.0515 0.4078 0.0918
0.250 0.4691 0.00883 0.00217 -0.0512 0.4022 0.0966
0.500 0.4972 0.00873 0.00210 -0.0509 0.3982 0.1052
0.750 0.5253 0.00870 0.00205 -0.0506 0.3942 0.1108
1.000 0.5532 0.00865 0.00200 -0.0503 0.3899 0.1198
1.500 0.6095 0.00873 0.00228 -0.0498 0.3816 0.2086
1.750 0.6389 0.00905 0.00258 -0.0497 0.3771 0.2190
2.000 0.6676 0.00940 0.00290 -0.0495 0.3719 0.2233
2.250 0.6960 0.00971 0.00320 -0.0493 0.3670 0.2269
2.500 0.7244 0.00988 0.00338 -0.0490 0.3625 0.2305
2.750 0.7525 0.01007 0.00352 -0.0488 0.3572 0.2336
3.000 0.7802 0.01016 0.00362 -0.0486 0.3516 0.2358
3.250 0.8083 0.01027 0.00377 -0.0484 0.3465 0.2381
3.500 0.8360 0.01042 0.00390 -0.0482 0.3395 0.2413
3.750 0.8638 0.01050 0.00396 -0.0480 0.3328 0.2429
4.000 0.8915 0.01061 0.00403 -0.0478 0.3238 0.2440
4.250 0.9191 0.01077 0.00415 -0.0476 0.3137 0.2450
4.500 0.9461 0.01084 0.00415 -0.0474 0.2996 0.2460
4.750 0.9722 0.01097 0.00419 -0.0471 0.2757 0.2480
5.250 1.0232 0.01170 0.00469 -0.0465 0.2286 0.2515
5.500 1.0496 0.01188 0.00485 -0.0463 0.2211 0.2524
5.750 1.0757 0.01209 0.00502 -0.0460 0.2134 0.2526
6.000 1.1023 0.01224 0.00517 -0.0457 0.2094 0.2541
6.250 1.1288 0.01247 0.00540 -0.0455 0.2054 0.2561
6.500 1.1547 0.01271 0.00562 -0.0452 0.2010 0.2567
6.750 1.1807 0.01285 0.00577 -0.0449 0.1976 0.2564
7.000 1.2072 0.01292 0.00588 -0.0447 0.1955 0.2563
7.250 1.2333 0.01304 0.00603 -0.0444 0.1927 0.2562
7.500 1.2590 0.01320 0.00620 -0.0441 0.1899 0.2561
7.750 1.2842 0.01341 0.00641 -0.0438 0.1869 0.2560
8.000 1.3088 0.01367 0.00670 -0.0434 0.1834 0.2560
8.250 1.3346 0.01380 0.00687 -0.0431 0.1820 0.2559
8.500 1.3604 0.01390 0.00702 -0.0428 0.1799 0.2559
8.750 1.3856 0.01406 0.00721 -0.0425 0.1769 0.2559
9.000 1.4101 0.01428 0.00744 -0.0421 0.1734 0.2559
9.250 1.4333 0.01461 0.00776 -0.0416 0.1686 0.2559
9.500 1.4584 0.01474 0.00795 -0.0413 0.1667 0.2559
9.750 1.4830 0.01491 0.00817 -0.0409 0.1642 0.2559
10.000 1.5068 0.01514 0.00842 -0.0404 0.1608 0.2559
10.250 1.5295 0.01545 0.00874 -0.0399 0.1565 0.2560
10.500 1.5522 0.01574 0.00907 -0.0393 0.1532 0.2561
10.750 1.5754 0.01597 0.00933 -0.0388 0.1489 0.2562
11.000 1.5961 0.01638 0.00972 -0.0381 0.1423 0.2563
11.250 1.6172 0.01673 0.01009 -0.0373 0.1365 0.2565
11.500 1.6349 0.01728 0.01062 -0.0363 0.1269 0.2568
11.750 1.6480 0.01808 0.01133 -0.0347 0.1107 0.2569
12.000 1.6300 0.02020 0.01318 -0.0294 0.0750 0.2569
12.250 1.6201 0.02181 0.01477 -0.0255 0.0660 0.2570
12.500 1.6163 0.02356 0.01655 -0.0233 0.0599 0.2571
12.750 1.6173 0.02528 0.01831 -0.0219 0.0568 0.2572
13.000 1.6169 0.02731 0.02037 -0.0208 0.0533 0.2574
13.250 1.6202 0.02911 0.02224 -0.0200 0.0502 0.2579
13.500 1.6183 0.03143 0.02460 -0.0192 0.0465 0.2582
13.750 1.6143 0.03402 0.02722 -0.0186 0.0414 0.2589
14.000 1.6056 0.03724 0.03044 -0.0182 0.0345 0.2588
14.500 1.5661 0.04665 0.03985 -0.0187 0.0168 0.2589
14.750 1.5563 0.05057 0.04386 -0.0192 0.0155 0.2591
15.000 1.5466 0.05465 0.04802 -0.0199 0.0145 0.2593
15.250 1.5385 0.05874 0.05221 -0.0208 0.0137 0.2593
15.500 1.5327 0.06263 0.05620 -0.0218 0.0133 0.2595
15.750 1.5238 0.06704 0.06072 -0.0231 0.0128 0.2600
16.000 1.5147 0.07160 0.06537 -0.0245 0.0125 0.2601
16.250 1.5062 0.07618 0.07005 -0.0259 0.0123 0.2602
16.500 1.4936 0.08152 0.07550 -0.0279 0.0119 0.2606
16.750 1.4795 0.08724 0.08133 -0.0300 0.0115 0.2610
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