MH 91 14.98% (mh91-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 91 14.98% (mh91-il) Reynolds number: 1,000,000 Max Cl/Cd: 96.65 at α=10.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh91-il-1000000.txt Download as CSV file: xf-mh91-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: MH 91 14.98%
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
------ -------- --------- --------- -------- -------- --------
-15.250 -0.9142 0.08405 0.08150 -0.0070 1.0000 0.0080
-15.000 -0.9294 0.07694 0.07425 -0.0119 1.0000 0.0080
-14.750 -0.9406 0.07106 0.06825 -0.0157 1.0000 0.0080
-14.500 -0.9456 0.06668 0.06378 -0.0184 1.0000 0.0080
-14.250 -0.9563 0.06175 0.05873 -0.0211 1.0000 0.0079
-14.000 -0.9648 0.05753 0.05439 -0.0232 1.0000 0.0079
-13.750 -0.9930 0.05070 0.04736 -0.0249 1.0000 0.0078
-13.500 -1.0076 0.04639 0.04288 -0.0256 1.0000 0.0077
-13.250 -1.0180 0.04285 0.03919 -0.0254 1.0000 0.0076
-13.000 -1.0299 0.03936 0.03550 -0.0245 1.0000 0.0076
-12.750 -1.0325 0.03699 0.03301 -0.0234 1.0000 0.0076
-12.500 -1.0385 0.03431 0.03014 -0.0216 1.0000 0.0075
-12.250 -1.0398 0.03213 0.02780 -0.0197 1.0000 0.0075
-12.000 -1.0381 0.03023 0.02575 -0.0176 1.0000 0.0075
-11.750 -1.0328 0.02872 0.02413 -0.0156 1.0000 0.0075
-11.500 -1.0272 0.02714 0.02241 -0.0134 1.0000 0.0075
-11.250 -1.0189 0.02583 0.02100 -0.0113 1.0000 0.0075
-11.000 -1.0094 0.02460 0.01968 -0.0091 1.0000 0.0075
-10.750 -0.9989 0.02346 0.01844 -0.0069 1.0000 0.0075
-10.500 -0.9872 0.02244 0.01734 -0.0048 1.0000 0.0075
-10.250 -0.9743 0.02149 0.01632 -0.0027 1.0000 0.0076
-10.000 -0.9591 0.02061 0.01537 -0.0009 1.0000 0.0076
-9.750 -0.9416 0.01975 0.01444 0.0005 1.0000 0.0077
-9.500 -0.9183 0.01897 0.01352 0.0009 0.9259 0.0077
-9.250 -0.9040 0.01843 0.01284 0.0034 0.8954 0.0078
-9.000 -0.8854 0.01797 0.01226 0.0050 0.8737 0.0079
-8.750 -0.8709 0.01700 0.01115 0.0072 0.8549 0.0080
-8.500 -0.8552 0.01609 0.01012 0.0092 0.8382 0.0082
-8.250 -0.8352 0.01552 0.00947 0.0105 0.8232 0.0084
-8.000 -0.8138 0.01503 0.00891 0.0117 0.8087 0.0087
-7.750 -0.7910 0.01462 0.00844 0.0126 0.7946 0.0090
-7.500 -0.7680 0.01418 0.00794 0.0135 0.7812 0.0092
-7.250 -0.7441 0.01383 0.00751 0.0143 0.7686 0.0096
-7.000 -0.7202 0.01347 0.00706 0.0151 0.7556 0.0099
-6.750 -0.6953 0.01315 0.00669 0.0157 0.7427 0.0101
-6.500 -0.6725 0.01260 0.00607 0.0167 0.7306 0.0107
-6.250 -0.6477 0.01227 0.00569 0.0173 0.7184 0.0112
-6.000 -0.6221 0.01198 0.00535 0.0178 0.7060 0.0118
-5.750 -0.5961 0.01172 0.00504 0.0183 0.6941 0.0126
-5.500 -0.5709 0.01138 0.00465 0.0188 0.6821 0.0138
-5.250 -0.5446 0.01115 0.00437 0.0193 0.6698 0.0154
-5.000 -0.5186 0.01085 0.00405 0.0197 0.6582 0.0187
-4.750 -0.4929 0.01055 0.00375 0.0202 0.6464 0.0258
-4.500 -0.4674 0.01020 0.00347 0.0207 0.6346 0.0419
-4.250 -0.4424 0.00980 0.00319 0.0212 0.6236 0.0709
-4.000 -0.4183 0.00932 0.00290 0.0218 0.6117 0.1192
-3.750 -0.3944 0.00879 0.00263 0.0225 0.6004 0.1814
-3.500 -0.3703 0.00831 0.00239 0.0231 0.5896 0.2473
-3.250 -0.3456 0.00792 0.00220 0.0236 0.5776 0.3093
-3.000 -0.3201 0.00758 0.00205 0.0240 0.5661 0.3641
-2.750 -0.2943 0.00730 0.00192 0.0244 0.5552 0.4142
-2.500 -0.2685 0.00702 0.00181 0.0248 0.5434 0.4700
-2.250 -0.2425 0.00678 0.00172 0.0252 0.5320 0.5218
-2.000 -0.2161 0.00659 0.00164 0.0256 0.5207 0.5645
-1.750 -0.1896 0.00642 0.00158 0.0259 0.5091 0.6084
-1.500 -0.1624 0.00631 0.00153 0.0262 0.4976 0.6405
-1.250 -0.1349 0.00625 0.00150 0.0264 0.4861 0.6674
-1.000 -0.1071 0.00620 0.00148 0.0266 0.4746 0.6924
-0.750 -0.0790 0.00619 0.00148 0.0267 0.4633 0.7143
-0.500 -0.0509 0.00620 0.00148 0.0268 0.4517 0.7339
-0.250 -0.0227 0.00621 0.00149 0.0269 0.4407 0.7513
0.000 0.0057 0.00624 0.00151 0.0269 0.4298 0.7662
0.250 0.0340 0.00629 0.00154 0.0270 0.4183 0.7781
0.500 0.0628 0.00633 0.00156 0.0270 0.4079 0.7888
0.750 0.0913 0.00640 0.00159 0.0270 0.3974 0.7989
1.000 0.1198 0.00647 0.00163 0.0270 0.3865 0.8076
1.250 0.1485 0.00653 0.00167 0.0269 0.3773 0.8163
1.500 0.1770 0.00663 0.00172 0.0269 0.3673 0.8240
1.750 0.2056 0.00669 0.00177 0.0269 0.3581 0.8314
2.250 0.2625 0.00686 0.00190 0.0268 0.3408 0.8452
2.500 0.2909 0.00697 0.00197 0.0268 0.3327 0.8521
2.750 0.3194 0.00705 0.00203 0.0268 0.3250 0.8585
3.000 0.3472 0.00717 0.00213 0.0269 0.3168 0.8655
3.250 0.3755 0.00727 0.00222 0.0269 0.3098 0.8727
3.500 0.4032 0.00739 0.00232 0.0270 0.3022 0.8788
3.750 0.4313 0.00747 0.00241 0.0270 0.2965 0.8844
4.000 0.4593 0.00760 0.00250 0.0270 0.2895 0.8899
4.250 0.4871 0.00771 0.00261 0.0270 0.2828 0.8948
4.500 0.5148 0.00781 0.00271 0.0272 0.2770 0.8997
4.750 0.5422 0.00797 0.00283 0.0272 0.2704 0.9049
5.000 0.5702 0.00808 0.00294 0.0272 0.2653 0.9097
5.250 0.5972 0.00819 0.00306 0.0274 0.2592 0.9144
5.500 0.6238 0.00836 0.00321 0.0276 0.2527 0.9194
5.750 0.6513 0.00846 0.00332 0.0277 0.2482 0.9245
6.000 0.6778 0.00860 0.00345 0.0280 0.2425 0.9294
6.250 0.7034 0.00877 0.00362 0.0284 0.2364 0.9348
6.500 0.7296 0.00889 0.00375 0.0287 0.2318 0.9409
6.750 0.7548 0.00904 0.00390 0.0293 0.2258 0.9463
7.000 0.7797 0.00921 0.00406 0.0298 0.2202 0.9521
7.250 0.8052 0.00934 0.00420 0.0302 0.2152 0.9576
7.500 0.8310 0.00953 0.00438 0.0305 0.2096 0.9625
7.750 0.8568 0.00970 0.00456 0.0308 0.2049 0.9682
8.000 0.8850 0.00986 0.00473 0.0306 0.2001 0.9726
8.250 0.9149 0.01011 0.00496 0.0299 0.1943 0.9761
8.500 0.9452 0.01031 0.00517 0.0291 0.1898 0.9801
8.750 0.9760 0.01052 0.00538 0.0282 0.1853 0.9834
9.000 1.0095 0.01082 0.00567 0.0266 0.1794 0.9851
9.250 1.0436 0.01105 0.00591 0.0250 0.1751 0.9866
9.500 1.0772 0.01130 0.00617 0.0234 0.1703 0.9883
9.750 1.1094 0.01167 0.00651 0.0220 0.1645 0.9906
10.000 1.1413 0.01188 0.00676 0.0208 0.1606 0.9930
10.250 1.1742 0.01218 0.00706 0.0193 0.1556 0.9948
10.500 1.2069 0.01258 0.00743 0.0177 0.1500 0.9969
10.750 1.2400 0.01283 0.00772 0.0161 0.1457 0.9988
11.000 1.2649 0.01320 0.00807 0.0160 0.1404 1.0000
11.250 1.2749 0.01349 0.00838 0.0189 0.1365 1.0000
11.500 1.2904 0.01375 0.00866 0.0208 0.1328 1.0000
11.750 1.3062 0.01414 0.00903 0.0225 0.1279 1.0000
12.000 1.3236 0.01454 0.00944 0.0238 0.1230 1.0000
12.250 1.3413 0.01495 0.00986 0.0250 0.1180 1.0000
12.500 1.3564 0.01549 0.01038 0.0264 0.1121 1.0000
12.750 1.3717 0.01596 0.01086 0.0279 0.1073 1.0000
13.000 1.3785 0.01661 0.01150 0.0306 0.1024 1.0000
13.250 1.3888 0.01720 0.01212 0.0325 0.0987 1.0000
13.500 1.3973 0.01798 0.01292 0.0344 0.0949 1.0000
13.750 1.4035 0.01899 0.01394 0.0361 0.0908 1.0000
14.000 1.4140 0.01986 0.01486 0.0372 0.0877 1.0000
14.250 1.4212 0.02103 0.01604 0.0383 0.0845 1.0000
14.500 1.4253 0.02250 0.01753 0.0393 0.0808 1.0000
14.750 1.4347 0.02369 0.01878 0.0400 0.0786 1.0000
15.000 1.4406 0.02521 0.02035 0.0405 0.0763 1.0000
15.250 1.4429 0.02711 0.02228 0.0409 0.0736 1.0000
15.500 1.4455 0.02910 0.02432 0.0412 0.0710 1.0000
15.750 1.4506 0.03093 0.02622 0.0412 0.0693 1.0000
16.000 1.4520 0.03317 0.02852 0.0411 0.0674 1.0000
16.250 1.4494 0.03588 0.03128 0.0408 0.0655 1.0000
16.500 1.4436 0.03901 0.03446 0.0403 0.0635 1.0000
16.750 1.4432 0.04166 0.03720 0.0398 0.0622 1.0000
17.000 1.4413 0.04453 0.04015 0.0391 0.0609 1.0000
17.250 1.4355 0.04791 0.04360 0.0382 0.0593 1.0000
17.500 1.4270 0.05177 0.04753 0.0370 0.0581 1.0000
17.750 1.4143 0.05620 0.05203 0.0355 0.0565 1.0000
18.000 1.4011 0.06085 0.05677 0.0338 0.0552 1.0000
18.250 1.3963 0.06453 0.06053 0.0324 0.0541 1.0000
18.500 1.3862 0.06897 0.06506 0.0306 0.0530 1.0000
18.750 1.3729 0.07392 0.07010 0.0286 0.0517 1.0000
19.000 1.3579 0.07923 0.07548 0.0263 0.0506 1.0000
19.250 1.3412 0.08488 0.08121 0.0237 0.0494 1.0000
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Polar data table (+)
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