MH 91 14.98% (mh91-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 91 14.98% (mh91-il) Reynolds number: 500,000 Max Cl/Cd: 75.29 at α=9.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh91-il-500000-n5.txt Download as CSV file: xf-mh91-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.250 -0.8643 0.11602 0.11313 0.0150 1.0000 0.0064
-16.000 -0.9279 0.09657 0.09328 0.0028 1.0000 0.0063
-15.750 -0.9577 0.08593 0.08242 -0.0039 1.0000 0.0062
-15.500 -0.9819 0.07710 0.07336 -0.0094 1.0000 0.0062
-15.250 -0.9997 0.06997 0.06604 -0.0137 1.0000 0.0062
-15.000 -1.0114 0.06428 0.06021 -0.0169 1.0000 0.0062
-14.750 -1.0218 0.05917 0.05494 -0.0195 1.0000 0.0063
-14.500 -1.0323 0.05439 0.04998 -0.0216 1.0000 0.0062
-14.250 -1.0381 0.05053 0.04599 -0.0230 1.0000 0.0062
-14.000 -1.0433 0.04701 0.04233 -0.0238 1.0000 0.0063
-13.750 -1.0458 0.04401 0.03921 -0.0242 1.0000 0.0063
-13.500 -1.0474 0.04127 0.03634 -0.0242 1.0000 0.0063
-13.250 -1.0478 0.03878 0.03372 -0.0237 1.0000 0.0063
-13.000 -1.0455 0.03672 0.03156 -0.0230 1.0000 0.0064
-12.750 -1.0431 0.03470 0.02941 -0.0220 1.0000 0.0064
-12.500 -1.0388 0.03297 0.02759 -0.0208 1.0000 0.0065
-12.250 -1.0322 0.03150 0.02603 -0.0196 1.0000 0.0066
-12.000 -1.0252 0.03008 0.02451 -0.0181 1.0000 0.0067
-11.750 -1.0178 0.02869 0.02303 -0.0165 1.0000 0.0067
-11.500 -1.0085 0.02751 0.02176 -0.0149 1.0000 0.0069
-11.250 -0.9990 0.02634 0.02050 -0.0131 1.0000 0.0069
-11.000 -0.9882 0.02529 0.01937 -0.0113 1.0000 0.0069
-10.750 -0.9765 0.02431 0.01832 -0.0095 1.0000 0.0071
-10.500 -0.9646 0.02337 0.01730 -0.0076 1.0000 0.0071
-10.250 -0.9512 0.02254 0.01640 -0.0057 1.0000 0.0073
-10.000 -0.9374 0.02176 0.01555 -0.0039 0.9845 0.0074
-9.750 -0.9150 0.02099 0.01465 -0.0034 0.9167 0.0076
-9.500 -0.9029 0.02042 0.01394 -0.0008 0.8857 0.0076
-9.250 -0.8876 0.01987 0.01324 0.0013 0.8634 0.0078
-9.000 -0.8702 0.01935 0.01260 0.0031 0.8448 0.0079
-8.500 -0.8349 0.01807 0.01114 0.0064 0.8123 0.0083
-8.250 -0.8146 0.01756 0.01054 0.0076 0.7976 0.0085
-8.000 -0.7935 0.01708 0.00998 0.0088 0.7838 0.0088
-7.750 -0.7718 0.01663 0.00945 0.0098 0.7706 0.0090
-7.500 -0.7497 0.01618 0.00892 0.0108 0.7573 0.0093
-7.250 -0.7266 0.01578 0.00843 0.0117 0.7442 0.0097
-7.000 -0.7033 0.01538 0.00795 0.0125 0.7319 0.0100
-6.750 -0.6800 0.01498 0.00747 0.0134 0.7194 0.0104
-6.500 -0.6560 0.01460 0.00704 0.0141 0.7067 0.0111
-6.250 -0.6314 0.01427 0.00665 0.0147 0.6945 0.0119
-6.000 -0.6067 0.01396 0.00627 0.0154 0.6824 0.0129
-5.750 -0.5818 0.01364 0.00591 0.0159 0.6695 0.0144
-5.500 -0.5566 0.01335 0.00556 0.0165 0.6576 0.0161
-5.250 -0.5312 0.01307 0.00523 0.0170 0.6455 0.0185
-5.000 -0.5058 0.01278 0.00491 0.0175 0.6333 0.0224
-4.750 -0.4802 0.01249 0.00461 0.0180 0.6214 0.0289
-4.500 -0.4547 0.01220 0.00433 0.0185 0.6096 0.0394
-4.250 -0.4297 0.01185 0.00404 0.0190 0.5974 0.0591
-4.000 -0.4054 0.01142 0.00374 0.0196 0.5860 0.0942
-3.750 -0.3820 0.01091 0.00344 0.0203 0.5746 0.1484
-3.500 -0.3585 0.01039 0.00316 0.0209 0.5632 0.2113
-3.250 -0.3350 0.00989 0.00293 0.0216 0.5521 0.2811
-3.000 -0.3109 0.00949 0.00273 0.0222 0.5407 0.3438
-2.750 -0.2862 0.00915 0.00257 0.0227 0.5294 0.3987
-2.500 -0.2615 0.00884 0.00244 0.0233 0.5186 0.4544
-2.250 -0.2368 0.00856 0.00233 0.0239 0.5068 0.5092
-2.000 -0.2106 0.00840 0.00224 0.0243 0.4958 0.5449
-1.750 -0.1838 0.00829 0.00217 0.0246 0.4851 0.5727
-1.500 -0.1569 0.00820 0.00210 0.0249 0.4735 0.5988
-1.250 -0.1299 0.00812 0.00206 0.0252 0.4624 0.6255
-1.000 -0.1030 0.00805 0.00203 0.0256 0.4520 0.6528
-0.750 -0.0758 0.00801 0.00202 0.0259 0.4407 0.6786
-0.500 -0.0483 0.00800 0.00202 0.0261 0.4301 0.6997
0.000 0.0073 0.00804 0.00204 0.0264 0.4092 0.7345
0.250 0.0352 0.00809 0.00206 0.0266 0.3989 0.7495
0.500 0.0632 0.00813 0.00210 0.0267 0.3889 0.7623
0.750 0.0912 0.00819 0.00214 0.0268 0.3797 0.7740
1.000 0.1193 0.00828 0.00217 0.0268 0.3696 0.7853
1.250 0.1474 0.00834 0.00223 0.0269 0.3609 0.7952
1.750 0.2034 0.00851 0.00235 0.0271 0.3433 0.8138
2.250 0.2591 0.00871 0.00251 0.0273 0.3278 0.8323
2.500 0.2867 0.00883 0.00259 0.0274 0.3197 0.8412
2.750 0.3144 0.00893 0.00269 0.0276 0.3125 0.8490
3.000 0.3422 0.00905 0.00278 0.0276 0.3052 0.8563
3.250 0.3698 0.00916 0.00289 0.0278 0.2992 0.8619
3.500 0.3975 0.00927 0.00300 0.0278 0.2927 0.8682
4.000 0.4524 0.00953 0.00322 0.0280 0.2797 0.8793
4.250 0.4796 0.00966 0.00335 0.0282 0.2737 0.8850
4.500 0.5067 0.00983 0.00348 0.0283 0.2682 0.8910
4.750 0.5340 0.00994 0.00361 0.0284 0.2628 0.8959
5.000 0.5607 0.01010 0.00377 0.0287 0.2565 0.9014
5.250 0.5872 0.01026 0.00392 0.0289 0.2512 0.9077
5.500 0.6139 0.01040 0.00407 0.0291 0.2463 0.9131
5.750 0.6399 0.01057 0.00425 0.0294 0.2407 0.9192
6.000 0.6657 0.01075 0.00442 0.0298 0.2355 0.9258
6.250 0.6923 0.01090 0.00459 0.0300 0.2304 0.9305
6.500 0.7184 0.01109 0.00479 0.0302 0.2253 0.9357
6.750 0.7437 0.01129 0.00498 0.0306 0.2203 0.9417
7.000 0.7711 0.01146 0.00518 0.0305 0.2152 0.9459
7.250 0.7978 0.01168 0.00540 0.0306 0.2098 0.9508
7.500 0.8233 0.01190 0.00562 0.0308 0.2046 0.9567
7.750 0.8526 0.01212 0.00586 0.0302 0.1985 0.9604
8.000 0.8812 0.01241 0.00613 0.0297 0.1930 0.9647
8.250 0.9090 0.01263 0.00638 0.0295 0.1888 0.9699
8.500 0.9400 0.01290 0.00667 0.0284 0.1834 0.9731
8.750 0.9705 0.01325 0.00700 0.0274 0.1781 0.9765
9.000 1.0006 0.01351 0.00730 0.0265 0.1740 0.9805
9.250 1.0311 0.01382 0.00763 0.0255 0.1687 0.9840
9.500 1.0627 0.01422 0.00803 0.0241 0.1636 0.9868
9.750 1.0940 0.01453 0.00838 0.0229 0.1591 0.9899
10.250 1.1537 0.01534 0.00922 0.0207 0.1492 0.9978
10.500 1.1774 0.01569 0.00960 0.0208 0.1450 1.0000
10.750 1.1907 0.01606 0.00998 0.0229 0.1406 1.0000
11.000 1.2046 0.01649 0.01042 0.0248 0.1366 1.0000
11.250 1.2212 0.01687 0.01084 0.0262 0.1327 1.0000
11.500 1.2363 0.01734 0.01133 0.0277 0.1283 1.0000
11.750 1.2485 0.01790 0.01190 0.0296 0.1242 1.0000
12.000 1.2598 0.01840 0.01245 0.0316 0.1203 1.0000
12.250 1.2690 0.01908 0.01315 0.0336 0.1161 1.0000
12.500 1.2774 0.01992 0.01400 0.0353 0.1124 1.0000
12.750 1.2884 0.02072 0.01486 0.0365 0.1086 1.0000
13.000 1.2968 0.02176 0.01593 0.0377 0.1044 1.0000
13.250 1.3041 0.02297 0.01716 0.0387 0.1006 1.0000
13.500 1.3128 0.02416 0.01841 0.0395 0.0970 1.0000
13.750 1.3182 0.02568 0.01996 0.0401 0.0932 1.0000
14.000 1.3231 0.02734 0.02166 0.0406 0.0897 1.0000
14.250 1.3284 0.02905 0.02343 0.0409 0.0863 1.0000
14.500 1.3303 0.03113 0.02555 0.0411 0.0830 1.0000
14.750 1.3313 0.03339 0.02786 0.0410 0.0805 1.0000
15.000 1.3343 0.03554 0.03009 0.0409 0.0783 1.0000
15.250 1.3344 0.03805 0.03267 0.0405 0.0759 1.0000
15.500 1.3313 0.04095 0.03564 0.0400 0.0737 1.0000
15.750 1.3251 0.04429 0.03903 0.0392 0.0717 1.0000
16.000 1.3240 0.04713 0.04197 0.0385 0.0702 1.0000
16.250 1.3199 0.05040 0.04533 0.0376 0.0684 1.0000
16.500 1.3128 0.05417 0.04916 0.0363 0.0661 1.0000
16.750 1.3049 0.05813 0.05321 0.0349 0.0649 1.0000
17.000 1.2931 0.06273 0.05787 0.0331 0.0632 1.0000
17.250 1.2877 0.06656 0.06181 0.0316 0.0620 1.0000
17.500 1.2805 0.07074 0.06607 0.0299 0.0600 1.0000
17.750 1.2716 0.07524 0.07066 0.0280 0.0587 1.0000
18.000 1.2624 0.07984 0.07535 0.0260 0.0577 1.0000
18.250 1.2500 0.08502 0.08059 0.0236 0.0562 1.0000
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Polar data table (+)
Polar graphs
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