NACA M27 AIRFOIL (m27-il) Xfoil prediction polar at RE=500,000 Ncrit=9
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Airfoil: NACA M27 AIRFOIL (m27-il) Reynolds number: 500,000 Max Cl/Cd: 105.54 at α=8.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-m27-il-500000.txt Download as CSV file: xf-m27-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: NACA M27 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.1771 0.09782 0.09427 -0.0156 0.5877 0.0214
-7.750 -0.1736 0.09506 0.09148 -0.0202 0.5850 0.0216
-7.500 -0.1705 0.09260 0.08900 -0.0251 0.5824 0.0217
-7.250 -0.1604 0.08894 0.08534 -0.0283 0.5793 0.0218
-7.000 -0.1500 0.08510 0.08150 -0.0272 0.5757 0.0219
-6.750 -0.1385 0.08209 0.07846 -0.0278 0.5723 0.0221
-6.500 -0.1257 0.07934 0.07565 -0.0293 0.5691 0.0224
-6.250 -0.1113 0.07663 0.07291 -0.0312 0.5661 0.0227
-6.000 -0.0954 0.07386 0.07013 -0.0333 0.5630 0.0232
-5.750 -0.0782 0.07106 0.06728 -0.0355 0.5598 0.0238
-5.500 -0.0591 0.06820 0.06436 -0.0379 0.5567 0.0248
-5.250 -0.0233 0.06551 0.06145 -0.0448 0.5539 0.0258
-5.000 -0.0017 0.06213 0.05795 -0.0468 0.5509 0.0259
-4.750 0.0108 0.05871 0.05455 -0.0465 0.5479 0.0262
-4.500 0.0283 0.05615 0.05197 -0.0469 0.5445 0.0264
-4.250 0.0484 0.05386 0.04962 -0.0477 0.5415 0.0268
-4.000 0.0704 0.05167 0.04735 -0.0487 0.5385 0.0273
-3.750 0.0937 0.04957 0.04513 -0.0497 0.5354 0.0281
-3.500 0.1194 0.04734 0.04283 -0.0508 0.5326 0.0295
-3.250 0.1612 0.04530 0.04052 -0.0532 0.5295 0.0308
-3.000 0.1798 0.04195 0.03709 -0.0533 0.5265 0.0311
-2.750 0.2001 0.03998 0.03505 -0.0534 0.5235 0.0315
-2.500 0.2226 0.03833 0.03331 -0.0536 0.5205 0.0319
-2.250 0.2472 0.03673 0.03165 -0.0539 0.5178 0.0326
-2.000 0.2733 0.03511 0.02995 -0.0542 0.5148 0.0337
-1.750 0.3116 0.03379 0.02835 -0.0544 0.5118 0.0366
-1.500 0.3341 0.03093 0.02534 -0.0542 0.5091 0.0372
-1.250 0.3569 0.02954 0.02387 -0.0543 0.5060 0.0377
-1.000 0.3817 0.02843 0.02268 -0.0544 0.5031 0.0386
-0.750 0.4083 0.02725 0.02143 -0.0544 0.5004 0.0400
-0.500 0.4443 0.02639 0.02026 -0.0539 0.4975 0.0438
-0.250 0.4661 0.02401 0.01781 -0.0538 0.4948 0.0450
0.000 0.4918 0.02319 0.01693 -0.0540 0.4919 0.0461
0.250 0.5187 0.02249 0.01610 -0.0540 0.4888 0.0484
0.500 0.5490 0.02094 0.01428 -0.0534 0.4862 0.0534
0.750 0.5754 0.02016 0.01350 -0.0537 0.4834 0.0546
1.000 0.6028 0.01953 0.01282 -0.0538 0.4805 0.0568
1.250 0.6346 0.01993 0.01295 -0.0535 0.4777 0.0625
1.500 0.6593 0.01785 0.01080 -0.0536 0.4751 0.0654
1.750 0.6869 0.01739 0.01025 -0.0537 0.4721 0.0681
2.000 0.7172 0.01785 0.01057 -0.0536 0.4694 0.0744
2.250 0.7485 0.01365 0.00583 -0.0528 0.4670 0.0430
2.500 0.7760 0.01330 0.00544 -0.0528 0.4642 0.0431
2.750 0.8031 0.01309 0.00519 -0.0527 0.4616 0.0437
3.000 0.8288 0.01284 0.00489 -0.0524 0.4589 0.0449
3.250 0.8551 0.01279 0.00484 -0.0523 0.4561 0.0468
3.500 0.8821 0.01272 0.00482 -0.0524 0.4534 0.0495
3.750 0.9090 0.01268 0.00481 -0.0524 0.4505 0.0540
4.250 0.9627 0.01267 0.00491 -0.0525 0.4453 0.1029
4.500 0.9895 0.01277 0.00502 -0.0526 0.4426 0.1305
4.750 1.0160 0.01282 0.00521 -0.0527 0.4400 0.1839
5.000 1.0675 0.01182 0.00582 -0.0580 0.4368 0.9786
5.250 1.2022 0.01224 0.00618 -0.0818 0.4320 1.0000
5.500 1.2275 0.01238 0.00628 -0.0817 0.4295 1.0000
5.750 1.2526 0.01260 0.00643 -0.0816 0.4268 1.0000
6.000 1.2775 0.01275 0.00661 -0.0814 0.4244 1.0000
6.250 1.3023 0.01287 0.00678 -0.0812 0.4217 1.0000
6.500 1.3268 0.01300 0.00693 -0.0810 0.4185 1.0000
6.750 1.3509 0.01311 0.00702 -0.0808 0.4144 1.0000
7.000 1.3746 0.01333 0.00720 -0.0804 0.4102 1.0000
7.250 1.3983 0.01344 0.00739 -0.0801 0.4067 1.0000
7.500 1.4216 0.01356 0.00754 -0.0798 0.4020 1.0000
7.750 1.4443 0.01376 0.00771 -0.0793 0.3974 1.0000
8.000 1.4667 0.01396 0.00795 -0.0789 0.3932 1.0000
8.250 1.4891 0.01411 0.00817 -0.0784 0.3886 1.0000
8.500 1.5103 0.01433 0.00838 -0.0777 0.3833 1.0000
8.750 1.5309 0.01458 0.00867 -0.0770 0.3777 1.0000
9.000 1.5506 0.01481 0.00893 -0.0761 0.3696 1.0000
9.250 1.5689 0.01513 0.00926 -0.0750 0.3623 1.0000
9.500 1.5849 0.01552 0.00965 -0.0736 0.3526 1.0000
9.750 1.5983 0.01599 0.01014 -0.0719 0.3397 1.0000
10.000 1.6026 0.01680 0.01088 -0.0688 0.3222 1.0000
10.250 1.5953 0.01788 0.01190 -0.0639 0.3048 1.0000
10.500 1.5757 0.01929 0.01329 -0.0576 0.2930 1.0000
10.750 1.5597 0.02138 0.01532 -0.0532 0.2749 1.0000
11.000 1.5414 0.02423 0.01808 -0.0496 0.2526 1.0000
11.250 1.5199 0.02782 0.02157 -0.0466 0.2288 1.0000
11.500 1.4934 0.03219 0.02583 -0.0440 0.2038 1.0000
11.750 1.4643 0.03703 0.03058 -0.0417 0.1792 1.0000
12.000 1.4363 0.04199 0.03547 -0.0398 0.1568 1.0000
12.250 1.4086 0.04726 0.04067 -0.0382 0.1340 1.0000
12.500 1.3813 0.05277 0.04611 -0.0371 0.1107 1.0000
12.750 1.3543 0.05848 0.05175 -0.0362 0.0852 1.0000
13.000 1.3283 0.06427 0.05747 -0.0355 0.0606 1.0000
13.250 1.3031 0.07018 0.06331 -0.0351 0.0349 1.0000
13.500 1.2907 0.07466 0.06778 -0.0349 0.0253 1.0000
13.750 1.2866 0.07819 0.07135 -0.0348 0.0225 1.0000
14.000 1.2850 0.08146 0.07470 -0.0348 0.0214 1.0000
14.250 1.2836 0.08472 0.07804 -0.0348 0.0206 1.0000
14.500 1.2803 0.08826 0.08167 -0.0349 0.0198 1.0000
14.750 1.2771 0.09179 0.08528 -0.0350 0.0191 1.0000
15.000 1.2716 0.09574 0.08930 -0.0352 0.0184 1.0000
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Polar data table (+)
Polar graphs
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