MH 200 12.97% (mh200-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 200 12.97% (mh200-il) Reynolds number: 1,000,000 Max Cl/Cd: 93.67 at α=2.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh200-il-1000000-n5.txt Download as CSV file: xf-mh200-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH 200 12.97%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.250 -0.6279 0.06076 0.05892 -0.0668 1.0000 0.0025
-12.000 -0.6762 0.04908 0.04698 -0.0747 1.0000 0.0024
-11.750 -0.6951 0.04231 0.03997 -0.0799 0.9973 0.0025
-11.250 -0.7076 0.03274 0.02983 -0.0863 0.9672 0.0025
-11.000 -0.6834 0.02888 0.02562 -0.0925 0.9493 0.0026
-10.750 -0.6622 0.02637 0.02277 -0.0956 0.9191 0.0027
-10.500 -0.6646 0.02468 0.02073 -0.0922 0.8878 0.0027
-10.000 -0.6486 0.02206 0.01764 -0.0878 0.8585 0.0028
-9.750 -0.6368 0.02076 0.01612 -0.0860 0.8485 0.0028
-9.500 -0.6210 0.01982 0.01501 -0.0846 0.8402 0.0029
-9.250 -0.6051 0.01868 0.01369 -0.0833 0.8325 0.0029
-9.000 -0.5863 0.01790 0.01277 -0.0823 0.8258 0.0029
-8.750 -0.5673 0.01701 0.01174 -0.0812 0.8193 0.0030
-8.500 -0.5478 0.01616 0.01074 -0.0802 0.8135 0.0030
-8.250 -0.5266 0.01546 0.00994 -0.0795 0.8086 0.0030
-8.000 -0.5054 0.01474 0.00909 -0.0787 0.8037 0.0031
-7.750 -0.4828 0.01422 0.00849 -0.0781 0.7993 0.0032
-7.500 -0.4591 0.01377 0.00797 -0.0777 0.7954 0.0033
-7.250 -0.4351 0.01333 0.00746 -0.0773 0.7912 0.0034
-7.000 -0.4114 0.01286 0.00691 -0.0768 0.7871 0.0034
-6.750 -0.3872 0.01245 0.00644 -0.0764 0.7835 0.0035
-6.500 -0.3640 0.01181 0.00571 -0.0759 0.7802 0.0036
-6.250 -0.3400 0.01127 0.00510 -0.0755 0.7769 0.0036
-6.000 -0.3149 0.01087 0.00464 -0.0752 0.7737 0.0037
-5.750 -0.2895 0.01050 0.00421 -0.0749 0.7706 0.0039
-5.500 -0.2635 0.01019 0.00385 -0.0748 0.7677 0.0041
-5.250 -0.2369 0.00992 0.00355 -0.0747 0.7647 0.0043
-5.000 -0.2101 0.00968 0.00327 -0.0747 0.7619 0.0047
-4.750 -0.1832 0.00947 0.00302 -0.0747 0.7590 0.0053
-4.500 -0.1563 0.00924 0.00277 -0.0746 0.7562 0.0072
-4.250 -0.1291 0.00904 0.00257 -0.0747 0.7536 0.0113
-4.000 -0.1022 0.00876 0.00235 -0.0747 0.7507 0.0261
-3.750 -0.0754 0.00848 0.00217 -0.0748 0.7475 0.0502
-3.500 -0.0496 0.00803 0.00195 -0.0748 0.7444 0.1114
-3.250 -0.0246 0.00743 0.00173 -0.0748 0.7415 0.2139
-3.000 0.0019 0.00701 0.00158 -0.0750 0.7387 0.2908
-2.750 0.0288 0.00662 0.00144 -0.0752 0.7357 0.3674
-2.500 0.0564 0.00636 0.00134 -0.0754 0.7326 0.4207
-2.250 0.0842 0.00615 0.00125 -0.0756 0.7295 0.4694
-2.000 0.1120 0.00597 0.00118 -0.0759 0.7264 0.5133
-1.750 0.1401 0.00577 0.00113 -0.0761 0.7230 0.5615
-1.500 0.1683 0.00563 0.00110 -0.0763 0.7187 0.6026
-1.250 0.1966 0.00557 0.00108 -0.0765 0.7142 0.6311
-1.000 0.2250 0.00554 0.00108 -0.0767 0.7101 0.6524
-0.750 0.2538 0.00552 0.00109 -0.0769 0.7054 0.6686
-0.500 0.2823 0.00552 0.00109 -0.0771 0.7005 0.6814
-0.250 0.3108 0.00554 0.00110 -0.0773 0.6957 0.6914
0.000 0.3395 0.00555 0.00111 -0.0776 0.6896 0.6999
0.250 0.3676 0.00558 0.00113 -0.0776 0.6826 0.7079
0.500 0.3962 0.00560 0.00115 -0.0778 0.6743 0.7159
0.750 0.4242 0.00564 0.00118 -0.0779 0.6658 0.7236
1.000 0.4524 0.00568 0.00120 -0.0781 0.6557 0.7291
1.250 0.4803 0.00573 0.00124 -0.0781 0.6440 0.7334
1.500 0.5078 0.00580 0.00127 -0.0781 0.6289 0.7376
1.750 0.5348 0.00591 0.00131 -0.0781 0.6101 0.7414
2.000 0.5606 0.00607 0.00138 -0.0777 0.5826 0.7447
2.250 0.5858 0.00628 0.00148 -0.0773 0.5522 0.7482
2.500 0.6107 0.00652 0.00161 -0.0769 0.5206 0.7523
2.750 0.6354 0.00681 0.00176 -0.0764 0.4868 0.7565
3.000 0.6595 0.00709 0.00192 -0.0759 0.4526 0.7601
3.250 0.6837 0.00738 0.00209 -0.0753 0.4189 0.7634
3.500 0.7078 0.00768 0.00226 -0.0748 0.3869 0.7664
3.750 0.7317 0.00800 0.00245 -0.0742 0.3554 0.7693
4.000 0.7559 0.00830 0.00264 -0.0737 0.3267 0.7718
4.250 0.7794 0.00861 0.00284 -0.0731 0.2978 0.7743
4.500 0.8033 0.00889 0.00305 -0.0726 0.2730 0.7768
4.750 0.8264 0.00923 0.00328 -0.0719 0.2452 0.7796
5.000 0.8496 0.00956 0.00351 -0.0713 0.2215 0.7823
5.250 0.8734 0.00985 0.00373 -0.0707 0.2025 0.7850
5.500 0.8959 0.01020 0.00399 -0.0700 0.1801 0.7875
5.750 0.9188 0.01051 0.00424 -0.0693 0.1615 0.7901
6.000 0.9416 0.01082 0.00450 -0.0685 0.1455 0.7928
6.250 0.9631 0.01121 0.00480 -0.0676 0.1257 0.7958
6.500 0.9851 0.01155 0.00509 -0.0668 0.1103 0.7989
6.750 1.0071 0.01189 0.00539 -0.0660 0.0980 0.8016
7.000 1.0283 0.01224 0.00571 -0.0650 0.0858 0.8044
7.250 1.0487 0.01263 0.00606 -0.0639 0.0732 0.8076
7.500 1.0687 0.01302 0.00642 -0.0627 0.0624 0.8112
7.750 1.0887 0.01340 0.00678 -0.0615 0.0539 0.8146
8.000 1.1066 0.01377 0.00715 -0.0600 0.0459 0.8180
8.250 1.1228 0.01420 0.00756 -0.0581 0.0376 0.8220
8.500 1.1388 0.01467 0.00801 -0.0563 0.0306 0.8266
8.750 1.1548 0.01515 0.00847 -0.0544 0.0247 0.8309
9.000 1.1712 0.01561 0.00895 -0.0528 0.0203 0.8356
9.250 1.1869 0.01611 0.00946 -0.0510 0.0168 0.8408
9.500 1.2039 0.01655 0.00993 -0.0495 0.0151 0.8460
9.750 1.2193 0.01706 0.01050 -0.0478 0.0130 0.8524
10.250 1.2500 0.01811 0.01164 -0.0445 0.0098 0.8677
10.500 1.2641 0.01870 0.01228 -0.0427 0.0084 0.8768
11.000 1.2905 0.01990 0.01363 -0.0390 0.0061 0.9038
11.250 1.2999 0.02050 0.01434 -0.0365 0.0053 0.9390
11.500 1.3156 0.02123 0.01516 -0.0356 0.0042 1.0000
11.750 1.3289 0.02206 0.01603 -0.0342 0.0036 1.0000
12.000 1.3412 0.02298 0.01700 -0.0327 0.0028 1.0000
12.250 1.3516 0.02405 0.01811 -0.0312 0.0019 1.0000
12.500 1.3641 0.02499 0.01910 -0.0299 0.0019 1.0000
12.750 1.3749 0.02606 0.02023 -0.0286 0.0015 1.0000
13.000 1.3857 0.02717 0.02140 -0.0273 0.0014 1.0000
13.250 1.3936 0.02852 0.02282 -0.0259 0.0010 1.0000
13.500 1.4028 0.02981 0.02418 -0.0246 0.0009 1.0000
13.750 1.4117 0.03114 0.02559 -0.0235 0.0009 1.0000
14.000 1.4193 0.03261 0.02713 -0.0224 0.0008 1.0000
14.250 1.4260 0.03420 0.02882 -0.0213 0.0007 1.0000
14.500 1.4292 0.03616 0.03086 -0.0201 0.0005 1.0000
14.750 1.4378 0.03764 0.03242 -0.0193 0.0006 1.0000
15.000 1.4389 0.03990 0.03479 -0.0183 0.0005 1.0000
15.250 1.4428 0.04196 0.03694 -0.0176 0.0005 1.0000
15.500 1.4441 0.04435 0.03943 -0.0170 0.0005 1.0000
15.750 1.4410 0.04732 0.04254 -0.0165 0.0004 1.0000
16.000 1.4438 0.04975 0.04506 -0.0163 0.0004 1.0000
16.250 1.4380 0.05333 0.04878 -0.0162 0.0004 1.0000
16.500 1.4363 0.05654 0.05209 -0.0165 0.0004 1.0000
16.750 1.4330 0.06012 0.05579 -0.0170 0.0004 1.0000
17.000 1.4274 0.06420 0.06000 -0.0179 0.0004 1.0000
17.250 1.4219 0.06844 0.06436 -0.0191 0.0004 1.0000
17.500 1.4126 0.07345 0.06951 -0.0208 0.0004 1.0000
17.750 1.4033 0.07871 0.07492 -0.0229 0.0004 1.0000
18.000 1.3912 0.08469 0.08103 -0.0255 0.0004 1.0000
18.250 1.3774 0.09118 0.08767 -0.0286 0.0004 1.0000
18.500 1.3612 0.09839 0.09503 -0.0322 0.0004 1.0000
18.750 1.3429 0.10627 0.10306 -0.0364 0.0004 1.0000
19.000 1.3214 0.11502 0.11198 -0.0412 0.0004 1.0000
19.250 1.3008 0.12382 0.12092 -0.0462 0.0004 1.0000
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Polar data table (+)
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