MH 120 11.57% (mh120-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 120 11.57% (mh120-il) Reynolds number: 50,000 Max Cl/Cd: 34.72 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh120-il-50000-n5.txt Download as CSV file: xf-mh120-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH 120 11.57%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.4016 0.11000 0.10287 -0.0383 1.0000 0.0602
-10.000 -0.4026 0.10587 0.09882 -0.0394 1.0000 0.0574
-9.750 -0.4276 0.09835 0.09150 -0.0475 1.0000 0.0515
-9.500 -0.4199 0.09542 0.08855 -0.0457 1.0000 0.0505
-9.250 -0.4215 0.09155 0.08475 -0.0461 1.0000 0.0497
-9.000 -0.4255 0.08763 0.08092 -0.0471 1.0000 0.0489
-8.750 -0.4319 0.08359 0.07697 -0.0484 1.0000 0.0481
-8.500 -0.4452 0.07910 0.07257 -0.0502 1.0000 0.0474
-8.250 -0.4627 0.07565 0.06921 -0.0494 1.0000 0.0469
-8.000 -0.4789 0.07219 0.06579 -0.0481 1.0000 0.0463
-7.750 -0.4944 0.06880 0.06240 -0.0465 1.0000 0.0457
-7.500 -0.5086 0.06557 0.05912 -0.0443 1.0000 0.0451
-7.250 -0.5214 0.06238 0.05583 -0.0417 1.0000 0.0446
-7.000 -0.5316 0.05928 0.05258 -0.0390 1.0000 0.0441
-6.750 -0.5389 0.05630 0.04940 -0.0361 1.0000 0.0439
-6.500 -0.5429 0.05354 0.04641 -0.0332 1.0000 0.0441
-6.250 -0.5443 0.05091 0.04352 -0.0303 1.0000 0.0447
-6.000 -0.5435 0.04839 0.04069 -0.0275 1.0000 0.0460
-5.750 -0.5399 0.04600 0.03796 -0.0248 1.0000 0.0465
-5.500 -0.5345 0.04359 0.03516 -0.0220 1.0000 0.0476
-5.250 -0.5064 0.04042 0.03140 -0.0232 0.9928 0.0477
-5.000 -0.4762 0.03765 0.02807 -0.0242 0.9855 0.0478
-4.750 -0.4458 0.03534 0.02526 -0.0250 0.9779 0.0483
-4.500 -0.4111 0.03335 0.02282 -0.0263 0.9716 0.0491
-4.250 -0.3789 0.03169 0.02074 -0.0269 0.9639 0.0502
-4.000 -0.3431 0.03029 0.01908 -0.0283 0.9574 0.0517
-3.750 -0.3133 0.02900 0.01774 -0.0290 0.9493 0.0556
-3.500 -0.2801 0.02808 0.01660 -0.0301 0.9418 0.0630
-3.250 -0.2478 0.02706 0.01543 -0.0312 0.9339 0.0681
-3.000 -0.2155 0.02627 0.01444 -0.0322 0.9255 0.0756
-2.750 -0.1797 0.02510 0.01331 -0.0340 0.9186 0.1043
-2.500 -0.1581 0.02310 0.01286 -0.0339 0.9102 0.3883
-2.250 -0.0378 0.02193 0.01359 -0.0472 0.9199 0.9311
-2.000 0.0367 0.02200 0.01308 -0.0566 0.9174 0.9780
-1.750 0.0825 0.02205 0.01274 -0.0612 0.9097 1.0000
-1.500 0.1161 0.02195 0.01233 -0.0632 0.9004 1.0000
-1.250 0.1490 0.02189 0.01198 -0.0649 0.8905 1.0000
-1.000 0.1774 0.02191 0.01177 -0.0656 0.8794 1.0000
-0.750 0.2081 0.02193 0.01158 -0.0666 0.8694 1.0000
-0.500 0.2436 0.02189 0.01133 -0.0683 0.8612 1.0000
-0.250 0.2679 0.02200 0.01128 -0.0680 0.8496 1.0000
0.000 0.2935 0.02211 0.01126 -0.0679 0.8388 1.0000
0.250 0.3239 0.02216 0.01117 -0.0685 0.8297 1.0000
0.500 0.3526 0.02223 0.01113 -0.0688 0.8201 1.0000
0.750 0.3755 0.02242 0.01124 -0.0681 0.8090 1.0000
1.000 0.4014 0.02257 0.01132 -0.0679 0.7992 1.0000
1.250 0.4334 0.02260 0.01128 -0.0686 0.7910 1.0000
1.500 0.4543 0.02288 0.01151 -0.0675 0.7799 1.0000
1.750 0.4776 0.02311 0.01171 -0.0667 0.7695 1.0000
2.000 0.5088 0.02316 0.01175 -0.0672 0.7616 1.0000
2.250 0.5304 0.02344 0.01202 -0.0661 0.7507 1.0000
2.500 0.5517 0.02375 0.01234 -0.0650 0.7400 1.0000
2.750 0.5774 0.02394 0.01254 -0.0645 0.7304 1.0000
3.000 0.6056 0.02405 0.01271 -0.0644 0.7211 1.0000
3.250 0.6253 0.02441 0.01310 -0.0629 0.7097 1.0000
3.500 0.6472 0.02470 0.01345 -0.0618 0.6986 1.0000
3.750 0.6723 0.02488 0.01369 -0.0611 0.6881 1.0000
4.000 0.7015 0.02492 0.01383 -0.0609 0.6780 1.0000
4.250 0.7215 0.02523 0.01422 -0.0593 0.6654 1.0000
4.500 0.7422 0.02550 0.01458 -0.0579 0.6526 1.0000
4.750 0.7634 0.02576 0.01493 -0.0564 0.6399 1.0000
5.000 0.7851 0.02599 0.01527 -0.0551 0.6268 1.0000
5.250 0.8068 0.02621 0.01567 -0.0537 0.6136 1.0000
5.500 0.8285 0.02643 0.01601 -0.0522 0.5999 1.0000
5.750 0.8498 0.02662 0.01634 -0.0507 0.5854 1.0000
6.000 0.8709 0.02680 0.01665 -0.0490 0.5700 1.0000
6.250 0.8922 0.02694 0.01692 -0.0474 0.5540 1.0000
6.500 0.9148 0.02700 0.01710 -0.0458 0.5372 1.0000
6.750 0.9284 0.02739 0.01773 -0.0432 0.5181 1.0000
7.000 0.9461 0.02759 0.01806 -0.0409 0.4984 1.0000
7.250 0.9621 0.02785 0.01845 -0.0384 0.4774 1.0000
7.500 0.9770 0.02814 0.01885 -0.0358 0.4548 1.0000
7.750 0.9888 0.02858 0.01942 -0.0329 0.4309 1.0000
8.000 1.0010 0.02903 0.01995 -0.0299 0.4057 1.0000
8.250 1.0112 0.02957 0.02054 -0.0268 0.3794 1.0000
8.500 1.0200 0.03025 0.02130 -0.0236 0.3530 1.0000
8.750 1.0260 0.03105 0.02209 -0.0201 0.3269 1.0000
9.000 1.0291 0.03203 0.02307 -0.0164 0.3011 1.0000
9.250 1.0308 0.03318 0.02421 -0.0129 0.2754 1.0000
9.500 1.0302 0.03454 0.02552 -0.0094 0.2494 1.0000
9.750 1.0261 0.03617 0.02707 -0.0060 0.2220 1.0000
10.000 1.0177 0.03821 0.02897 -0.0030 0.1913 1.0000
10.250 1.0093 0.04057 0.03114 -0.0007 0.1613 1.0000
10.500 1.0000 0.04336 0.03375 0.0010 0.1266 1.0000
10.750 0.9917 0.04642 0.03660 0.0023 0.0982 1.0000
11.000 0.9846 0.04968 0.03976 0.0034 0.0783 1.0000
11.250 0.9766 0.05323 0.04323 0.0043 0.0637 1.0000
11.500 0.9704 0.05671 0.04667 0.0050 0.0549 1.0000
11.750 0.9672 0.05996 0.04998 0.0055 0.0497 1.0000
12.000 0.9621 0.06358 0.05364 0.0058 0.0429 1.0000
12.250 0.9603 0.06683 0.05707 0.0060 0.0395 1.0000
12.500 0.9598 0.06994 0.06027 0.0061 0.0381 1.0000
12.750 0.9579 0.07342 0.06385 0.0064 0.0354 1.0000
13.000 0.9605 0.07648 0.06717 0.0069 0.0337 1.0000
13.250 0.9628 0.07967 0.07059 0.0072 0.0325 1.0000
13.500 0.9634 0.08326 0.07442 0.0073 0.0314 1.0000
13.750 0.9623 0.08710 0.07849 0.0069 0.0307 1.0000
14.000 0.9580 0.09161 0.08323 0.0060 0.0301 1.0000
14.250 0.9511 0.09666 0.08849 0.0045 0.0296 1.0000
14.500 0.9419 0.10228 0.09435 0.0025 0.0294 1.0000
14.750 0.9294 0.10883 0.10112 -0.0003 0.0293 1.0000
15.000 0.9151 0.11609 0.10859 -0.0039 0.0295 1.0000
15.250 0.8960 0.12510 0.11781 -0.0087 0.0299 1.0000
15.500 0.8755 0.13525 0.12810 -0.0143 0.0306 1.0000
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