MH 78 14.47% (mh78-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 78 14.47% (mh78-il) Reynolds number: 500,000 Max Cl/Cd: 73.65 at α=9° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh78-il-500000.txt Download as CSV file: xf-mh78-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.5736 0.08940 0.08750 0.0205 1.0000 0.0282
-9.500 -0.5940 0.07943 0.07756 0.0129 1.0000 0.0285
-9.250 -0.6576 0.06323 0.06107 -0.0011 0.8995 0.0282
-9.000 -0.6909 0.05948 0.05689 0.0018 0.8076 0.0283
-8.750 -0.8268 0.03663 0.03209 0.0119 0.8283 0.0191
-8.500 -0.8364 0.02948 0.02390 0.0166 0.7955 0.0164
-8.250 -0.8180 0.02831 0.02243 0.0183 0.7591 0.0163
-8.000 -0.7994 0.02624 0.02009 0.0197 0.7295 0.0162
-7.750 -0.7789 0.02466 0.01825 0.0209 0.7034 0.0162
-7.500 -0.7570 0.02331 0.01665 0.0221 0.6795 0.0162
-7.250 -0.7340 0.02218 0.01529 0.0231 0.6574 0.0162
-7.000 -0.7100 0.02122 0.01412 0.0241 0.6363 0.0163
-6.750 -0.6863 0.01982 0.01258 0.0249 0.6173 0.0165
-6.500 -0.6622 0.01880 0.01148 0.0257 0.5991 0.0168
-6.250 -0.6374 0.01809 0.01069 0.0265 0.5815 0.0171
-6.000 -0.6121 0.01751 0.01001 0.0272 0.5647 0.0175
-5.750 -0.5867 0.01691 0.00932 0.0279 0.5488 0.0179
-5.500 -0.5612 0.01636 0.00869 0.0287 0.5335 0.0183
-5.250 -0.5355 0.01586 0.00809 0.0294 0.5190 0.0188
-5.000 -0.5092 0.01548 0.00758 0.0300 0.5049 0.0193
-4.750 -0.4850 0.01477 0.00686 0.0309 0.4921 0.0200
-4.500 -0.4589 0.01439 0.00644 0.0315 0.4795 0.0208
-4.250 -0.4326 0.01404 0.00601 0.0321 0.4666 0.0218
-4.000 -0.4063 0.01365 0.00557 0.0328 0.4545 0.0229
-3.750 -0.3798 0.01333 0.00521 0.0333 0.4430 0.0248
-3.500 -0.3530 0.01300 0.00485 0.0338 0.4319 0.0273
-3.250 -0.3262 0.01270 0.00452 0.0343 0.4216 0.0314
-3.000 -0.2995 0.01237 0.00418 0.0349 0.4108 0.0392
-2.750 -0.2737 0.01192 0.00383 0.0355 0.4010 0.0616
-2.500 -0.2488 0.01138 0.00355 0.0362 0.3911 0.1191
-2.250 -0.2234 0.01095 0.00338 0.0367 0.3824 0.1845
-2.000 -0.1975 0.01061 0.00323 0.0372 0.3734 0.2442
-1.750 -0.1723 0.01023 0.00310 0.0378 0.3653 0.3156
-1.500 -0.1481 0.00975 0.00297 0.0386 0.3570 0.4088
-1.250 -0.1265 0.00918 0.00284 0.0398 0.3490 0.5377
-1.000 -0.1076 0.00845 0.00275 0.0419 0.3426 0.6895
-0.750 -0.0858 0.00817 0.00291 0.0439 0.3356 0.8107
-0.500 -0.0600 0.00831 0.00311 0.0452 0.3289 0.8623
-0.250 -0.0344 0.00850 0.00330 0.0466 0.3225 0.8925
0.000 -0.0089 0.00872 0.00344 0.0478 0.3158 0.9090
0.250 0.0194 0.00893 0.00360 0.0484 0.3099 0.9188
0.500 0.0462 0.00907 0.00368 0.0492 0.3043 0.9277
0.750 0.0769 0.00929 0.00381 0.0493 0.2986 0.9341
1.000 0.1022 0.00946 0.00391 0.0502 0.2936 0.9423
1.250 0.1381 0.00961 0.00402 0.0492 0.2883 0.9459
1.500 0.1736 0.00980 0.00413 0.0481 0.2829 0.9501
1.750 0.1997 0.01004 0.00426 0.0488 0.2779 0.9573
2.000 0.2482 0.01023 0.00443 0.0451 0.2736 0.9596
2.250 0.3004 0.01047 0.00459 0.0406 0.2683 0.9624
2.500 0.3428 0.01072 0.00474 0.0380 0.2631 0.9667
2.750 0.3771 0.01089 0.00488 0.0370 0.2595 0.9716
3.000 0.4198 0.01097 0.00493 0.0342 0.2557 0.9736
3.250 0.4587 0.01108 0.00499 0.0321 0.2520 0.9759
3.500 0.4938 0.01123 0.00507 0.0307 0.2480 0.9788
3.750 0.5234 0.01145 0.00524 0.0304 0.2445 0.9825
4.000 0.5597 0.01147 0.00527 0.0288 0.2416 0.9841
4.250 0.5956 0.01153 0.00532 0.0273 0.2384 0.9856
4.500 0.6301 0.01163 0.00538 0.0259 0.2353 0.9875
4.750 0.6630 0.01180 0.00549 0.0248 0.2320 0.9895
5.000 0.6947 0.01201 0.00567 0.0240 0.2287 0.9916
5.250 0.7259 0.01209 0.00578 0.0233 0.2264 0.9936
5.500 0.7600 0.01216 0.00586 0.0220 0.2236 0.9949
5.750 0.7933 0.01227 0.00596 0.0208 0.2209 0.9965
6.000 0.8256 0.01242 0.00608 0.0198 0.2182 0.9981
6.250 0.8568 0.01276 0.00635 0.0189 0.2148 0.9994
6.500 0.8848 0.01287 0.00651 0.0188 0.2129 1.0000
6.750 0.9090 0.01299 0.00667 0.0194 0.2107 1.0000
7.000 0.9328 0.01316 0.00685 0.0200 0.2084 1.0000
7.250 0.9563 0.01334 0.00705 0.0207 0.2063 1.0000
7.500 0.9794 0.01356 0.00726 0.0215 0.2041 1.0000
7.750 1.0018 0.01388 0.00755 0.0223 0.2018 1.0000
8.000 1.0238 0.01424 0.00792 0.0231 0.1995 1.0000
8.250 1.0465 0.01442 0.00815 0.0239 0.1978 1.0000
8.500 1.0688 0.01462 0.00840 0.0247 0.1957 1.0000
8.750 1.0907 0.01485 0.00867 0.0257 0.1937 1.0000
9.000 1.1121 0.01510 0.00893 0.0266 0.1918 1.0000
9.250 1.1328 0.01539 0.00922 0.0277 0.1899 1.0000
9.500 1.1524 0.01580 0.00961 0.0288 0.1878 1.0000
9.750 1.1716 0.01623 0.01006 0.0301 0.1858 1.0000
10.000 1.1914 0.01647 0.01038 0.0313 0.1842 1.0000
10.250 1.2106 0.01675 0.01072 0.0325 0.1824 1.0000
10.500 1.2292 0.01705 0.01106 0.0339 0.1807 1.0000
10.750 1.2474 0.01735 0.01140 0.0353 0.1789 1.0000
11.000 1.2653 0.01767 0.01174 0.0366 0.1772 1.0000
11.250 1.2826 0.01810 0.01215 0.0380 0.1752 1.0000
11.500 1.2993 0.01871 0.01275 0.0394 0.1731 1.0000
11.750 1.3176 0.01905 0.01319 0.0406 0.1718 1.0000
12.000 1.3360 0.01941 0.01363 0.0416 0.1700 1.0000
12.250 1.3545 0.01981 0.01409 0.0426 0.1682 1.0000
12.500 1.3728 0.02024 0.01456 0.0435 0.1664 1.0000
12.750 1.3903 0.02070 0.01504 0.0444 0.1646 1.0000
13.000 1.4063 0.02130 0.01564 0.0454 0.1627 1.0000
13.250 1.4207 0.02207 0.01643 0.0465 0.1607 1.0000
13.500 1.4308 0.02267 0.01715 0.0481 0.1593 1.0000
13.750 1.4380 0.02346 0.01803 0.0496 0.1578 1.0000
14.000 1.4460 0.02441 0.01906 0.0505 0.1561 1.0000
14.250 1.4545 0.02551 0.02022 0.0509 0.1544 1.0000
14.500 1.4627 0.02676 0.02152 0.0512 0.1528 1.0000
14.750 1.4703 0.02816 0.02292 0.0513 0.1510 1.0000
15.000 1.4784 0.02960 0.02436 0.0516 0.1492 1.0000
15.250 1.4819 0.03154 0.02645 0.0510 0.1479 1.0000
15.500 1.4850 0.03361 0.02864 0.0504 0.1463 1.0000
15.750 1.4879 0.03576 0.03089 0.0497 0.1447 1.0000
16.000 1.4899 0.03805 0.03325 0.0489 0.1430 1.0000
16.250 1.4911 0.04045 0.03569 0.0480 0.1413 1.0000
16.500 1.4934 0.04267 0.03792 0.0474 0.1396 1.0000
16.750 1.4946 0.04498 0.04027 0.0469 0.1378 1.0000
17.000 1.4841 0.04892 0.04437 0.0450 0.1362 1.0000
17.250 1.4760 0.05258 0.04815 0.0433 0.1345 1.0000
17.500 1.4687 0.05628 0.05194 0.0415 0.1327 1.0000
17.750 1.4628 0.05991 0.05563 0.0398 0.1309 1.0000
18.000 1.4626 0.06276 0.05848 0.0385 0.1290 1.0000
18.250 1.4603 0.06591 0.06166 0.0372 0.1271 1.0000
18.500 1.4384 0.07207 0.06800 0.0338 0.1253 1.0000
18.750 1.4212 0.07769 0.07374 0.0308 0.1231 1.0000
19.000 1.4090 0.08265 0.07877 0.0281 0.1210 1.0000
19.250 1.4097 0.08569 0.08180 0.0266 0.1189 1.0000
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