MH 78 14.47% (mh78-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: MH 78 14.47% (mh78-il) Reynolds number: 1,000,000 Max Cl/Cd: 99.25 at α=10.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh78-il-1000000.txt Download as CSV file: xf-mh78-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: MH 78 14.47%
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
------ -------- --------- --------- -------- -------- --------
-12.750 -0.6037 0.13903 0.13747 0.0479 1.0000 0.0163
-12.500 -0.6040 0.13288 0.13134 0.0448 1.0000 0.0163
-11.500 -1.0083 0.03878 0.03541 -0.0029 1.0000 0.0111
-11.250 -1.0103 0.03731 0.03382 0.0003 1.0000 0.0111
-11.000 -1.0070 0.03607 0.03247 0.0031 1.0000 0.0110
-10.750 -0.9982 0.03474 0.03104 0.0052 1.0000 0.0110
-10.500 -0.9869 0.03348 0.02967 0.0071 1.0000 0.0110
-10.250 -0.9900 0.02930 0.02523 0.0099 1.0000 0.0107
-10.000 -0.9789 0.02729 0.02303 0.0119 1.0000 0.0107
-9.750 -0.9692 0.02595 0.02128 0.0148 0.8491 0.0106
-9.500 -0.9550 0.02459 0.01960 0.0169 0.7977 0.0106
-9.250 -0.9377 0.02329 0.01804 0.0185 0.7599 0.0106
-9.000 -0.9182 0.02219 0.01672 0.0199 0.7283 0.0106
-8.750 -0.8976 0.02114 0.01548 0.0212 0.7011 0.0106
-8.500 -0.8760 0.02018 0.01434 0.0223 0.6762 0.0106
-8.250 -0.8536 0.01933 0.01333 0.0234 0.6540 0.0106
-8.000 -0.8305 0.01855 0.01241 0.0244 0.6331 0.0107
-7.750 -0.8068 0.01785 0.01158 0.0253 0.6138 0.0107
-7.500 -0.7827 0.01721 0.01083 0.0262 0.5953 0.0108
-7.250 -0.7580 0.01664 0.01015 0.0270 0.5776 0.0108
-7.000 -0.7330 0.01612 0.00953 0.0278 0.5612 0.0109
-6.750 -0.7076 0.01567 0.00898 0.0285 0.5450 0.0109
-6.500 -0.6856 0.01464 0.00784 0.0297 0.5308 0.0112
-6.250 -0.6608 0.01407 0.00720 0.0305 0.5165 0.0115
-6.000 -0.6348 0.01370 0.00677 0.0311 0.5022 0.0119
-5.750 -0.6084 0.01335 0.00636 0.0317 0.4890 0.0121
-5.500 -0.5818 0.01303 0.00599 0.0323 0.4770 0.0124
-5.250 -0.5550 0.01274 0.00563 0.0328 0.4640 0.0128
-5.000 -0.5279 0.01248 0.00531 0.0333 0.4516 0.0132
-4.750 -0.5006 0.01225 0.00502 0.0337 0.4401 0.0135
-4.500 -0.4744 0.01184 0.00455 0.0343 0.4289 0.0142
-4.250 -0.4470 0.01159 0.00427 0.0348 0.4190 0.0148
-4.000 -0.4195 0.01141 0.00403 0.0352 0.4079 0.0155
-3.250 -0.3364 0.01078 0.00331 0.0364 0.3786 0.0199
-3.000 -0.3087 0.01061 0.00311 0.0367 0.3687 0.0237
-2.750 -0.2811 0.01038 0.00292 0.0371 0.3611 0.0320
-2.500 -0.2537 0.01017 0.00274 0.0375 0.3520 0.0472
-2.250 -0.2266 0.00989 0.00258 0.0379 0.3441 0.0742
-2.000 -0.2001 0.00956 0.00242 0.0383 0.3358 0.1201
-1.750 -0.1734 0.00927 0.00230 0.0387 0.3285 0.1705
-1.500 -0.1463 0.00903 0.00221 0.0391 0.3217 0.2146
-1.250 -0.1193 0.00882 0.00213 0.0394 0.3138 0.2649
-1.000 -0.0931 0.00847 0.00204 0.0399 0.3083 0.3375
-0.750 -0.0681 0.00805 0.00196 0.0405 0.3017 0.4398
-0.500 -0.0448 0.00754 0.00188 0.0414 0.2949 0.5680
-0.250 -0.0220 0.00703 0.00181 0.0427 0.2909 0.6904
0.000 -0.0005 0.00664 0.00188 0.0445 0.2858 0.8186
0.250 0.0255 0.00670 0.00201 0.0455 0.2796 0.8656
0.500 0.0533 0.00677 0.00208 0.0460 0.2754 0.8827
0.750 0.0815 0.00685 0.00213 0.0464 0.2707 0.8932
1.000 0.1095 0.00696 0.00220 0.0468 0.2659 0.9020
1.250 0.1376 0.00709 0.00227 0.0471 0.2609 0.9092
1.500 0.1657 0.00716 0.00234 0.0475 0.2580 0.9153
1.750 0.1936 0.00726 0.00241 0.0479 0.2542 0.9215
2.000 0.2215 0.00738 0.00247 0.0482 0.2499 0.9267
2.250 0.2490 0.00753 0.00258 0.0487 0.2451 0.9314
2.500 0.2764 0.00762 0.00267 0.0492 0.2431 0.9371
2.750 0.3028 0.00772 0.00275 0.0499 0.2405 0.9435
3.000 0.3292 0.00785 0.00287 0.0507 0.2373 0.9496
3.250 0.3542 0.00800 0.00298 0.0517 0.2339 0.9565
3.500 0.3829 0.00819 0.00314 0.0519 0.2294 0.9611
3.750 0.4138 0.00831 0.00325 0.0517 0.2277 0.9653
4.000 0.4410 0.00841 0.00335 0.0522 0.2255 0.9702
4.250 0.4742 0.00852 0.00343 0.0513 0.2227 0.9720
4.500 0.5085 0.00866 0.00353 0.0501 0.2196 0.9731
4.750 0.5417 0.00886 0.00367 0.0490 0.2153 0.9742
5.000 0.5753 0.00896 0.00377 0.0480 0.2133 0.9752
5.250 0.6087 0.00905 0.00386 0.0469 0.2114 0.9761
5.500 0.6415 0.00916 0.00396 0.0460 0.2090 0.9771
5.750 0.6735 0.00929 0.00407 0.0452 0.2065 0.9784
6.000 0.7040 0.00945 0.00420 0.0447 0.2036 0.9801
6.250 0.7290 0.00968 0.00440 0.0452 0.2000 0.9829
6.500 0.7628 0.00975 0.00449 0.0440 0.1986 0.9834
6.750 0.7965 0.00986 0.00460 0.0428 0.1967 0.9840
7.000 0.8301 0.00998 0.00473 0.0417 0.1945 0.9846
7.250 0.8631 0.01014 0.00487 0.0405 0.1921 0.9854
7.500 0.8954 0.01033 0.00504 0.0395 0.1894 0.9863
7.750 0.9268 0.01060 0.00529 0.0386 0.1862 0.9873
8.000 0.9587 0.01070 0.00542 0.0378 0.1848 0.9884
8.250 0.9899 0.01084 0.00558 0.0370 0.1830 0.9896
8.500 1.0206 0.01100 0.00575 0.0363 0.1810 0.9909
8.750 1.0507 0.01119 0.00594 0.0357 0.1789 0.9924
9.000 1.0807 0.01143 0.00617 0.0350 0.1764 0.9937
9.250 1.1125 0.01177 0.00649 0.0338 0.1733 0.9946
9.500 1.1447 0.01190 0.00666 0.0328 0.1720 0.9954
9.750 1.1764 0.01207 0.00686 0.0318 0.1704 0.9964
10.000 1.2078 0.01227 0.00708 0.0309 0.1686 0.9975
10.250 1.2388 0.01250 0.00732 0.0299 0.1663 0.9985
10.500 1.2694 0.01279 0.00761 0.0290 0.1640 0.9995
10.750 1.2933 0.01323 0.00804 0.0292 0.1612 1.0000
11.000 1.3139 0.01341 0.00827 0.0303 0.1601 1.0000
11.250 1.3337 0.01361 0.00852 0.0315 0.1588 1.0000
11.500 1.3527 0.01384 0.00878 0.0329 0.1572 1.0000
11.750 1.3710 0.01409 0.00905 0.0343 0.1554 1.0000
12.000 1.3883 0.01439 0.00937 0.0358 0.1536 1.0000
12.250 1.4051 0.01477 0.00975 0.0374 0.1515 1.0000
12.500 1.4215 0.01525 0.01024 0.0388 0.1492 1.0000
12.750 1.4426 0.01549 0.01053 0.0396 0.1480 1.0000
13.000 1.4637 0.01578 0.01087 0.0403 0.1465 1.0000
13.250 1.4844 0.01612 0.01124 0.0410 0.1448 1.0000
13.500 1.5042 0.01653 0.01168 0.0417 0.1430 1.0000
13.750 1.5224 0.01703 0.01220 0.0425 0.1411 1.0000
14.000 1.5368 0.01773 0.01292 0.0436 0.1387 1.0000
14.250 1.5538 0.01824 0.01348 0.0445 0.1375 1.0000
14.500 1.5692 0.01871 0.01402 0.0456 0.1362 1.0000
14.750 1.5780 0.01937 0.01475 0.0473 0.1349 1.0000
15.000 1.5853 0.02032 0.01574 0.0485 0.1334 1.0000
15.250 1.5918 0.02158 0.01705 0.0491 0.1317 1.0000
15.500 1.5962 0.02323 0.01875 0.0492 0.1300 1.0000
15.750 1.5953 0.02553 0.02110 0.0489 0.1280 1.0000
16.000 1.6021 0.02729 0.02294 0.0486 0.1268 1.0000
16.250 1.6096 0.02904 0.02477 0.0481 0.1255 1.0000
16.500 1.6136 0.03116 0.02697 0.0475 0.1240 1.0000
16.750 1.6135 0.03374 0.02962 0.0467 0.1224 1.0000
17.000 1.6073 0.03698 0.03291 0.0456 0.1207 1.0000
17.250 1.5955 0.04084 0.03683 0.0443 0.1191 1.0000
17.500 1.5801 0.04511 0.04118 0.0428 0.1173 1.0000
17.750 1.5757 0.04828 0.04444 0.0416 0.1161 1.0000
18.000 1.5667 0.05197 0.04822 0.0403 0.1147 1.0000
18.250 1.5538 0.05626 0.05259 0.0385 0.1129 1.0000
18.500 1.5367 0.06119 0.05759 0.0364 0.1111 1.0000
18.750 1.5142 0.06691 0.06337 0.0338 0.1092 1.0000
19.000 1.4972 0.07204 0.06856 0.0315 0.1074 1.0000
19.250 1.4862 0.07655 0.07318 0.0294 0.1056 1.0000
|
Polar data table (+)
Polar graphs
<< Back to MH 78 14.47% (mh78-il)