MH 91 14.98% (mh91-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: MH 91 14.98% (mh91-il) Reynolds number: 1,000,000 Max Cl/Cd: 91.45 at α=10.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh91-il-1000000-n5.txt Download as CSV file: xf-mh91-il-1000000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-18.250 -0.9810 0.12898 0.12646 0.0225 1.0000 0.0044
-18.000 -1.0159 0.11646 0.11376 0.0149 1.0000 0.0044
-17.750 -1.0448 0.10573 0.10285 0.0084 1.0000 0.0043
-17.500 -1.0765 0.09484 0.09179 0.0018 1.0000 0.0044
-17.250 -1.1022 0.08561 0.08239 -0.0038 1.0000 0.0043
-17.000 -1.1168 0.07872 0.07536 -0.0079 1.0000 0.0043
-16.750 -1.1342 0.07162 0.06812 -0.0121 1.0000 0.0043
-16.500 -1.1517 0.06488 0.06123 -0.0159 1.0000 0.0043
-16.250 -1.1621 0.05961 0.05584 -0.0186 1.0000 0.0043
-16.000 -1.1716 0.05478 0.05088 -0.0209 1.0000 0.0043
-15.750 -1.1812 0.05024 0.04621 -0.0227 1.0000 0.0043
-15.500 -1.1854 0.04668 0.04254 -0.0238 1.0000 0.0043
-15.250 -1.1909 0.04320 0.03894 -0.0245 1.0000 0.0043
-15.000 -1.1949 0.04012 0.03576 -0.0247 1.0000 0.0044
-14.750 -1.1973 0.03742 0.03295 -0.0245 1.0000 0.0044
-14.500 -1.1944 0.03537 0.03081 -0.0240 1.0000 0.0043
-14.250 -1.1930 0.03332 0.02866 -0.0231 1.0000 0.0044
-14.000 -1.1911 0.03141 0.02666 -0.0220 1.0000 0.0044
-13.750 -1.1866 0.02979 0.02497 -0.0207 1.0000 0.0045
-13.500 -1.1810 0.02834 0.02343 -0.0192 1.0000 0.0045
-13.250 -1.1741 0.02705 0.02206 -0.0177 1.0000 0.0045
-13.000 -1.1660 0.02588 0.02083 -0.0160 1.0000 0.0046
-12.750 -1.1579 0.02476 0.01964 -0.0142 1.0000 0.0045
-12.500 -1.1480 0.02378 0.01860 -0.0124 1.0000 0.0046
-12.250 -1.1361 0.02295 0.01771 -0.0106 1.0000 0.0047
-12.000 -1.1245 0.02213 0.01684 -0.0087 1.0000 0.0048
-11.750 -1.1127 0.02133 0.01599 -0.0067 1.0000 0.0048
-11.500 -1.0991 0.02066 0.01527 -0.0048 1.0000 0.0049
-11.250 -1.0870 0.01996 0.01451 -0.0026 0.9931 0.0049
-11.000 -1.0688 0.01943 0.01382 -0.0012 0.9073 0.0049
-10.750 -1.0570 0.01901 0.01327 0.0015 0.8774 0.0050
-10.500 -1.0414 0.01847 0.01261 0.0035 0.8555 0.0050
-10.250 -1.0231 0.01800 0.01205 0.0051 0.8370 0.0051
-10.000 -1.0041 0.01751 0.01146 0.0065 0.8205 0.0053
-9.750 -0.9842 0.01704 0.01090 0.0078 0.8054 0.0054
-9.500 -0.9636 0.01658 0.01035 0.0090 0.7908 0.0054
-9.250 -0.9420 0.01615 0.00985 0.0100 0.7770 0.0055
-9.000 -0.9196 0.01577 0.00939 0.0110 0.7636 0.0056
-8.750 -0.8970 0.01537 0.00892 0.0119 0.7510 0.0057
-8.500 -0.8737 0.01502 0.00849 0.0127 0.7381 0.0058
-8.250 -0.8505 0.01462 0.00803 0.0135 0.7257 0.0059
-8.000 -0.8276 0.01417 0.00751 0.0144 0.7139 0.0062
-7.750 -0.8035 0.01383 0.00712 0.0151 0.7016 0.0064
-7.500 -0.7789 0.01350 0.00674 0.0157 0.6892 0.0066
-7.250 -0.7539 0.01322 0.00641 0.0163 0.6778 0.0068
-7.000 -0.7287 0.01294 0.00607 0.0168 0.6654 0.0070
-6.750 -0.7032 0.01268 0.00576 0.0173 0.6531 0.0073
-6.500 -0.6775 0.01243 0.00546 0.0178 0.6414 0.0076
-6.250 -0.6515 0.01221 0.00517 0.0182 0.6293 0.0079
-6.000 -0.6257 0.01193 0.00487 0.0186 0.6174 0.0085
-5.750 -0.5995 0.01171 0.00461 0.0190 0.6060 0.0092
-5.500 -0.5730 0.01152 0.00436 0.0194 0.5936 0.0099
-5.250 -0.5464 0.01131 0.00413 0.0197 0.5817 0.0110
-5.000 -0.5197 0.01112 0.00391 0.0200 0.5703 0.0125
-4.750 -0.4930 0.01094 0.00369 0.0203 0.5583 0.0148
-4.500 -0.4661 0.01075 0.00349 0.0206 0.5472 0.0185
-4.250 -0.4394 0.01054 0.00329 0.0208 0.5366 0.0250
-4.000 -0.4128 0.01034 0.00309 0.0211 0.5244 0.0353
-3.750 -0.3862 0.01010 0.00290 0.0214 0.5137 0.0499
-3.500 -0.3599 0.00985 0.00271 0.0217 0.5033 0.0718
-3.250 -0.3345 0.00950 0.00250 0.0221 0.4917 0.1111
-3.000 -0.3098 0.00907 0.00228 0.0226 0.4810 0.1690
-2.750 -0.2849 0.00868 0.00209 0.0231 0.4709 0.2288
-2.500 -0.2601 0.00826 0.00193 0.0236 0.4604 0.2976
-2.250 -0.2344 0.00796 0.00180 0.0239 0.4499 0.3522
-2.000 -0.2085 0.00770 0.00169 0.0243 0.4391 0.4041
-1.750 -0.1825 0.00744 0.00161 0.0246 0.4297 0.4591
-1.500 -0.1553 0.00732 0.00155 0.0248 0.4185 0.4927
-1.250 -0.1276 0.00723 0.00150 0.0249 0.4083 0.5195
-1.000 -0.0998 0.00717 0.00146 0.0250 0.3990 0.5432
-0.750 -0.0720 0.00711 0.00143 0.0251 0.3882 0.5673
-0.500 -0.0442 0.00705 0.00141 0.0252 0.3789 0.5926
-0.250 -0.0166 0.00699 0.00140 0.0253 0.3696 0.6189
0.000 0.0113 0.00695 0.00139 0.0254 0.3607 0.6439
0.250 0.0391 0.00694 0.00140 0.0255 0.3508 0.6653
0.500 0.0673 0.00692 0.00142 0.0255 0.3431 0.6856
0.750 0.0954 0.00695 0.00145 0.0256 0.3340 0.7035
1.000 0.1237 0.00696 0.00148 0.0256 0.3260 0.7200
1.250 0.1521 0.00702 0.00152 0.0256 0.3182 0.7344
1.500 0.1806 0.00705 0.00156 0.0255 0.3117 0.7479
1.750 0.2089 0.00711 0.00161 0.0255 0.3035 0.7592
2.000 0.2375 0.00717 0.00167 0.0255 0.2970 0.7701
2.250 0.2659 0.00723 0.00173 0.0254 0.2907 0.7803
2.500 0.2943 0.00731 0.00180 0.0254 0.2845 0.7895
2.750 0.3228 0.00737 0.00187 0.0253 0.2791 0.7994
3.000 0.3510 0.00746 0.00195 0.0253 0.2721 0.8093
3.250 0.3793 0.00755 0.00204 0.0253 0.2664 0.8194
3.500 0.4076 0.00763 0.00212 0.0253 0.2613 0.8274
3.750 0.4358 0.00774 0.00222 0.0252 0.2555 0.8345
4.000 0.4642 0.00784 0.00231 0.0251 0.2504 0.8403
4.250 0.4923 0.00794 0.00241 0.0251 0.2444 0.8462
4.500 0.5203 0.00807 0.00252 0.0251 0.2388 0.8521
4.750 0.5487 0.00818 0.00263 0.0250 0.2347 0.8572
5.000 0.5765 0.00828 0.00275 0.0250 0.2296 0.8625
5.250 0.6041 0.00843 0.00288 0.0250 0.2234 0.8681
5.500 0.6322 0.00856 0.00301 0.0249 0.2192 0.8733
5.750 0.6598 0.00868 0.00314 0.0249 0.2144 0.8783
6.000 0.6869 0.00884 0.00329 0.0250 0.2090 0.8841
6.250 0.7144 0.00898 0.00344 0.0250 0.2043 0.8902
6.500 0.7414 0.00912 0.00360 0.0251 0.1994 0.8960
6.750 0.7677 0.00932 0.00378 0.0253 0.1931 0.9022
7.000 0.7947 0.00948 0.00394 0.0254 0.1882 0.9077
7.250 0.8213 0.00965 0.00412 0.0255 0.1829 0.9122
7.500 0.8471 0.00986 0.00432 0.0258 0.1779 0.9172
7.750 0.8737 0.01002 0.00450 0.0259 0.1741 0.9222
8.000 0.9000 0.01021 0.00469 0.0260 0.1696 0.9268
8.250 0.9250 0.01044 0.00492 0.0264 0.1646 0.9317
8.500 0.9507 0.01062 0.00513 0.0266 0.1609 0.9370
8.750 0.9762 0.01082 0.00534 0.0269 0.1569 0.9421
9.000 1.0007 0.01107 0.00559 0.0273 0.1523 0.9475
9.250 1.0255 0.01129 0.00583 0.0276 0.1485 0.9536
9.500 1.0507 0.01152 0.00608 0.0279 0.1442 0.9592
9.750 1.0765 0.01180 0.00637 0.0279 0.1397 0.9651
10.000 1.1028 0.01208 0.00666 0.0278 0.1356 0.9713
10.250 1.1321 0.01238 0.00697 0.0270 0.1306 0.9761
10.500 1.1603 0.01277 0.00734 0.0263 0.1252 0.9815
10.750 1.1908 0.01309 0.00768 0.0253 0.1210 0.9852
11.000 1.2206 0.01353 0.00810 0.0241 0.1148 0.9895
11.250 1.2500 0.01393 0.00852 0.0231 0.1100 0.9947
11.500 1.2776 0.01440 0.00897 0.0223 0.1046 1.0000
11.750 1.2937 0.01482 0.00939 0.0238 0.1004 1.0000
12.000 1.3103 0.01526 0.00984 0.0252 0.0956 1.0000
12.250 1.3250 0.01581 0.01038 0.0267 0.0909 1.0000
12.500 1.3392 0.01630 0.01088 0.0283 0.0867 1.0000
12.750 1.3460 0.01695 0.01152 0.0310 0.0824 1.0000
13.000 1.3551 0.01760 0.01220 0.0330 0.0793 1.0000
13.250 1.3640 0.01838 0.01301 0.0348 0.0758 1.0000
13.500 1.3721 0.01931 0.01395 0.0363 0.0731 1.0000
13.750 1.3814 0.02027 0.01495 0.0374 0.0706 1.0000
14.000 1.3908 0.02131 0.01603 0.0384 0.0684 1.0000
14.250 1.3981 0.02256 0.01732 0.0393 0.0660 1.0000
14.500 1.4026 0.02413 0.01890 0.0400 0.0630 1.0000
14.750 1.4106 0.02551 0.02034 0.0405 0.0612 1.0000
15.000 1.4173 0.02706 0.02195 0.0409 0.0598 1.0000
15.250 1.4199 0.02904 0.02397 0.0411 0.0574 1.0000
15.500 1.4207 0.03128 0.02624 0.0411 0.0549 1.0000
15.750 1.4240 0.03336 0.02839 0.0410 0.0534 1.0000
16.000 1.4254 0.03570 0.03080 0.0408 0.0521 1.0000
16.250 1.4239 0.03838 0.03355 0.0403 0.0507 1.0000
16.500 1.4186 0.04156 0.03678 0.0397 0.0490 1.0000
16.750 1.4148 0.04465 0.03995 0.0389 0.0477 1.0000
17.000 1.4110 0.04782 0.04321 0.0381 0.0467 1.0000
17.250 1.4034 0.05159 0.04705 0.0369 0.0452 1.0000
17.500 1.3958 0.05544 0.05098 0.0356 0.0443 1.0000
17.750 1.3828 0.06005 0.05566 0.0339 0.0429 1.0000
18.000 1.3708 0.06468 0.06038 0.0321 0.0418 1.0000
18.250 1.3601 0.06921 0.06500 0.0303 0.0407 1.0000
18.500 1.3483 0.07403 0.06990 0.0283 0.0397 1.0000
18.750 1.3341 0.07924 0.07520 0.0261 0.0386 1.0000
19.000 1.3201 0.08455 0.08060 0.0237 0.0379 1.0000
|
Polar data table (+)
Polar graphs
<< Back to MH 91 14.98% (mh91-il)