MH 46 9.1% (mh46-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 46 9.1% (mh46-il) Reynolds number: 100,000 Max Cl/Cd: 46.04 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh46-il-100000.txt Download as CSV file: xf-mh46-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: MH 46 9.1%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4431 0.09136 0.08711 -0.0033 1.0000 0.1126
-8.500 -0.4434 0.08735 0.08314 -0.0047 1.0000 0.1171
-8.250 -0.4684 0.08296 0.07889 -0.0106 1.0000 0.1206
-8.000 -0.5790 0.08465 0.08025 -0.0210 1.0000 0.1078
-7.750 -0.5366 0.08216 0.07789 -0.0104 1.0000 0.1181
-7.500 -0.5621 0.07653 0.07220 -0.0213 1.0000 0.1209
-7.250 -0.5374 0.07360 0.06941 -0.0154 1.0000 0.1269
-7.000 -0.5526 0.06802 0.06367 -0.0233 1.0000 0.1359
-6.750 -0.5550 0.04953 0.04420 -0.0300 1.0000 0.0536
-6.500 -0.5447 0.04488 0.03935 -0.0297 1.0000 0.0512
-6.250 -0.5354 0.03935 0.03272 -0.0280 1.0000 0.0431
-6.000 -0.5205 0.03573 0.02868 -0.0268 1.0000 0.0432
-5.750 -0.5042 0.03235 0.02489 -0.0253 1.0000 0.0434
-5.500 -0.4860 0.02952 0.02164 -0.0237 1.0000 0.0433
-5.250 -0.4672 0.02677 0.01853 -0.0219 1.0000 0.0434
-5.000 -0.4486 0.02411 0.01561 -0.0201 1.0000 0.0446
-4.750 -0.4303 0.02223 0.01365 -0.0183 1.0000 0.0473
-4.500 -0.4124 0.02104 0.01225 -0.0162 1.0000 0.0543
-4.250 -0.3970 0.01947 0.01076 -0.0140 1.0000 0.0641
-4.000 -0.3828 0.01797 0.00935 -0.0115 1.0000 0.0845
-3.750 -0.3699 0.01655 0.00826 -0.0090 1.0000 0.1384
-3.500 -0.3577 0.01521 0.00756 -0.0066 1.0000 0.2436
-3.250 -0.3440 0.01450 0.00728 -0.0045 1.0000 0.3396
-3.000 -0.3299 0.01402 0.00718 -0.0024 1.0000 0.4323
-2.750 -0.3152 0.01361 0.00709 -0.0002 1.0000 0.5252
-2.500 -0.2994 0.01319 0.00706 0.0021 1.0000 0.6267
-2.250 -0.2621 0.01268 0.00715 0.0014 0.9956 0.8007
-2.000 -0.1307 0.01270 0.00689 -0.0175 1.0000 1.0000
-1.750 -0.0952 0.01285 0.00676 -0.0205 0.9926 1.0000
-1.500 -0.0394 0.01301 0.00665 -0.0268 0.9819 1.0000
-1.250 0.0145 0.01310 0.00651 -0.0325 0.9705 1.0000
-1.000 0.0692 0.01314 0.00638 -0.0382 0.9593 1.0000
-0.750 0.1222 0.01312 0.00624 -0.0435 0.9477 1.0000
-0.500 0.1699 0.01309 0.00609 -0.0475 0.9344 1.0000
-0.250 0.2107 0.01307 0.00599 -0.0499 0.9194 1.0000
0.000 0.2440 0.01309 0.00594 -0.0507 0.9032 1.0000
0.250 0.2711 0.01316 0.00594 -0.0500 0.8868 1.0000
0.500 0.2921 0.01330 0.00602 -0.0483 0.8683 1.0000
0.750 0.3127 0.01343 0.00609 -0.0464 0.8507 1.0000
1.000 0.3329 0.01354 0.00614 -0.0443 0.8340 1.0000
1.250 0.3531 0.01364 0.00618 -0.0421 0.8179 1.0000
1.500 0.3735 0.01379 0.00630 -0.0401 0.7999 1.0000
1.750 0.3942 0.01390 0.00638 -0.0382 0.7823 1.0000
2.000 0.4154 0.01400 0.00643 -0.0362 0.7653 1.0000
2.250 0.4370 0.01408 0.00645 -0.0343 0.7487 1.0000
2.500 0.4591 0.01421 0.00660 -0.0327 0.7296 1.0000
2.750 0.4815 0.01430 0.00667 -0.0311 0.7111 1.0000
3.000 0.5042 0.01437 0.00669 -0.0294 0.6934 1.0000
3.250 0.5272 0.01450 0.00683 -0.0280 0.6727 1.0000
3.500 0.5505 0.01458 0.00692 -0.0265 0.6533 1.0000
3.750 0.5739 0.01471 0.00705 -0.0252 0.6318 1.0000
4.000 0.5976 0.01482 0.00712 -0.0238 0.6109 1.0000
4.250 0.6212 0.01498 0.00729 -0.0226 0.5871 1.0000
4.500 0.6448 0.01515 0.00745 -0.0213 0.5631 1.0000
4.750 0.6685 0.01534 0.00765 -0.0200 0.5382 1.0000
5.000 0.6919 0.01558 0.00786 -0.0188 0.5115 1.0000
5.250 0.7151 0.01586 0.00813 -0.0176 0.4828 1.0000
5.500 0.7380 0.01619 0.00845 -0.0165 0.4521 1.0000
5.750 0.7606 0.01656 0.00879 -0.0153 0.4200 1.0000
6.000 0.7826 0.01700 0.00922 -0.0141 0.3858 1.0000
6.250 0.8040 0.01750 0.00966 -0.0129 0.3492 1.0000
6.500 0.8246 0.01809 0.01020 -0.0117 0.3097 1.0000
6.750 0.8442 0.01880 0.01082 -0.0104 0.2683 1.0000
7.000 0.8624 0.01973 0.01158 -0.0091 0.2254 1.0000
7.250 0.8792 0.02095 0.01259 -0.0077 0.1823 1.0000
7.500 0.8945 0.02242 0.01385 -0.0063 0.1417 1.0000
7.750 0.9103 0.02416 0.01548 -0.0046 0.1119 1.0000
8.000 0.9259 0.02592 0.01711 -0.0032 0.0909 1.0000
8.250 0.9446 0.02811 0.01924 -0.0018 0.0780 1.0000
8.500 0.9633 0.02980 0.02111 -0.0004 0.0678 1.0000
8.750 0.9826 0.03228 0.02379 0.0009 0.0604 1.0000
9.000 1.0018 0.03478 0.02644 0.0020 0.0554 1.0000
9.250 1.0165 0.03808 0.03005 0.0034 0.0510 1.0000
9.500 1.0281 0.04071 0.03312 0.0052 0.0470 1.0000
9.750 1.0382 0.04404 0.03678 0.0069 0.0449 1.0000
10.000 1.0450 0.04764 0.04058 0.0083 0.0427 1.0000
10.250 1.0421 0.05323 0.04648 0.0096 0.0415 1.0000
10.500 1.0309 0.05572 0.04944 0.0122 0.0405 1.0000
10.750 1.0177 0.05919 0.05324 0.0143 0.0402 1.0000
11.000 0.9992 0.06240 0.05669 0.0162 0.0399 1.0000
11.250 0.9820 0.06664 0.06111 0.0164 0.0403 1.0000
11.500 0.9633 0.07117 0.06581 0.0154 0.0405 1.0000
11.750 0.9438 0.07652 0.07130 0.0133 0.0408 1.0000
12.000 0.9278 0.08266 0.07752 0.0109 0.0413 1.0000
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Polar data table (+)
Polar graphs
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