MH 70 11.08% (mh70-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 70 11.08% (mh70-il) Reynolds number: 200,000 Max Cl/Cd: 67.9 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh70-il-200000-n5.txt Download as CSV file: xf-mh70-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH 70 11.08%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.3982 0.09563 0.09208 -0.0238 1.0000 0.0117
-9.500 -0.3994 0.09087 0.08737 -0.0261 1.0000 0.0117
-9.250 -0.3956 0.08774 0.08427 -0.0275 1.0000 0.0114
-9.000 -0.3977 0.08307 0.07966 -0.0299 1.0000 0.0114
-8.750 -0.3990 0.07884 0.07548 -0.0322 1.0000 0.0111
-8.500 -0.4044 0.07381 0.07052 -0.0353 1.0000 0.0111
-8.250 -0.4128 0.06858 0.06538 -0.0388 1.0000 0.0108
-8.000 -0.4277 0.06214 0.05902 -0.0445 1.0000 0.0106
-7.750 -0.4342 0.04435 0.04067 -0.0621 0.9470 0.0100
-7.500 -0.4296 0.03671 0.03237 -0.0658 0.9249 0.0099
-7.250 -0.4192 0.03197 0.02703 -0.0662 0.9083 0.0100
-7.000 -0.4024 0.02916 0.02376 -0.0659 0.8953 0.0104
-6.750 -0.3844 0.02670 0.02080 -0.0651 0.8833 0.0110
-6.500 -0.3647 0.02434 0.01782 -0.0641 0.8725 0.0117
-6.250 -0.3432 0.02283 0.01608 -0.0634 0.8633 0.0122
-6.000 -0.3203 0.02152 0.01453 -0.0626 0.8535 0.0125
-5.750 -0.2967 0.02024 0.01301 -0.0619 0.8449 0.0128
-5.500 -0.2727 0.01911 0.01167 -0.0611 0.8363 0.0132
-5.250 -0.2481 0.01809 0.01049 -0.0604 0.8279 0.0136
-5.000 -0.2235 0.01717 0.00941 -0.0596 0.8199 0.0143
-4.750 -0.1985 0.01637 0.00847 -0.0590 0.8118 0.0150
-4.500 -0.1736 0.01568 0.00772 -0.0584 0.8040 0.0159
-4.250 -0.1480 0.01510 0.00704 -0.0579 0.7960 0.0175
-4.000 -0.1221 0.01462 0.00648 -0.0574 0.7884 0.0203
-3.750 -0.0960 0.01413 0.00592 -0.0570 0.7806 0.0248
-3.500 -0.0698 0.01364 0.00536 -0.0565 0.7729 0.0317
-3.250 -0.0437 0.01313 0.00489 -0.0561 0.7653 0.0483
-3.000 -0.0180 0.01255 0.00449 -0.0557 0.7575 0.0925
-2.750 0.0076 0.01202 0.00423 -0.0555 0.7500 0.1662
-2.500 0.0337 0.01163 0.00404 -0.0552 0.7419 0.2325
-2.250 0.0597 0.01129 0.00387 -0.0548 0.7343 0.2986
-2.000 0.0855 0.01094 0.00375 -0.0544 0.7259 0.3733
-1.750 0.1113 0.01065 0.00364 -0.0540 0.7180 0.4427
-1.500 0.1368 0.01038 0.00353 -0.0534 0.7095 0.5092
-1.250 0.1620 0.01011 0.00346 -0.0526 0.7009 0.5796
-1.000 0.1864 0.00985 0.00341 -0.0516 0.6923 0.6568
-0.750 0.2103 0.00962 0.00339 -0.0502 0.6832 0.7370
-0.250 0.2646 0.00939 0.00335 -0.0485 0.6644 0.8808
0.000 0.3021 0.00937 0.00328 -0.0500 0.6543 0.9299
0.250 0.3423 0.00938 0.00317 -0.0523 0.6436 0.9631
0.500 0.3830 0.00939 0.00309 -0.0549 0.6313 0.9867
0.750 0.4197 0.00943 0.00302 -0.0567 0.6192 1.0000
1.000 0.4442 0.00951 0.00299 -0.0560 0.6074 1.0000
1.250 0.4688 0.00960 0.00298 -0.0553 0.5952 1.0000
1.500 0.4936 0.00970 0.00298 -0.0546 0.5823 1.0000
1.750 0.5186 0.00981 0.00301 -0.0540 0.5686 1.0000
2.000 0.5438 0.00994 0.00305 -0.0534 0.5545 1.0000
2.250 0.5690 0.01007 0.00310 -0.0528 0.5402 1.0000
2.500 0.5943 0.01022 0.00316 -0.0523 0.5254 1.0000
2.750 0.6196 0.01038 0.00324 -0.0517 0.5104 1.0000
3.000 0.6449 0.01056 0.00334 -0.0512 0.4947 1.0000
3.250 0.6702 0.01075 0.00346 -0.0507 0.4789 1.0000
3.500 0.6954 0.01096 0.00358 -0.0502 0.4628 1.0000
3.750 0.7205 0.01119 0.00373 -0.0497 0.4467 1.0000
4.000 0.7456 0.01143 0.00391 -0.0492 0.4303 1.0000
4.250 0.7705 0.01168 0.00410 -0.0487 0.4140 1.0000
4.500 0.7953 0.01195 0.00430 -0.0482 0.3975 1.0000
4.750 0.8200 0.01224 0.00453 -0.0477 0.3811 1.0000
5.000 0.8446 0.01253 0.00477 -0.0472 0.3648 1.0000
5.250 0.8690 0.01284 0.00503 -0.0467 0.3488 1.0000
5.500 0.8933 0.01317 0.00531 -0.0462 0.3330 1.0000
5.750 0.9173 0.01351 0.00563 -0.0456 0.3175 1.0000
6.000 0.9411 0.01388 0.00595 -0.0451 0.3026 1.0000
6.250 0.9647 0.01426 0.00629 -0.0445 0.2884 1.0000
6.500 0.9880 0.01466 0.00667 -0.0439 0.2746 1.0000
6.750 1.0112 0.01505 0.00705 -0.0433 0.2613 1.0000
7.000 1.0342 0.01547 0.00746 -0.0427 0.2483 1.0000
7.250 1.0569 0.01589 0.00789 -0.0421 0.2363 1.0000
7.500 1.0791 0.01635 0.00834 -0.0414 0.2249 1.0000
7.750 1.1007 0.01684 0.00882 -0.0406 0.2141 1.0000
8.000 1.1223 0.01732 0.00932 -0.0398 0.2032 1.0000
8.250 1.1436 0.01781 0.00984 -0.0390 0.1930 1.0000
8.500 1.1639 0.01835 0.01039 -0.0381 0.1837 1.0000
8.750 1.1837 0.01891 0.01097 -0.0372 0.1742 1.0000
9.000 1.2036 0.01945 0.01156 -0.0363 0.1654 1.0000
9.250 1.2215 0.02008 0.01220 -0.0351 0.1572 1.0000
9.500 1.2399 0.02067 0.01284 -0.0340 0.1489 1.0000
9.750 1.2566 0.02133 0.01355 -0.0327 0.1415 1.0000
10.000 1.2722 0.02201 0.01427 -0.0313 0.1338 1.0000
10.250 1.2857 0.02270 0.01502 -0.0296 0.1273 1.0000
10.500 1.2975 0.02348 0.01583 -0.0277 0.1205 1.0000
10.750 1.3091 0.02430 0.01672 -0.0259 0.1146 1.0000
11.000 1.3199 0.02521 0.01770 -0.0243 0.1084 1.0000
11.250 1.3297 0.02623 0.01877 -0.0227 0.1029 1.0000
11.500 1.3397 0.02729 0.01991 -0.0213 0.0971 1.0000
11.750 1.3471 0.02857 0.02123 -0.0198 0.0921 1.0000
12.000 1.3568 0.02977 0.02254 -0.0186 0.0866 1.0000
12.250 1.3619 0.03133 0.02414 -0.0174 0.0820 1.0000
12.500 1.3704 0.03274 0.02567 -0.0165 0.0774 1.0000
12.750 1.3756 0.03445 0.02745 -0.0155 0.0729 1.0000
13.000 1.3792 0.03637 0.02944 -0.0148 0.0693 1.0000
13.250 1.3848 0.03820 0.03140 -0.0141 0.0653 1.0000
13.500 1.3862 0.04048 0.03374 -0.0136 0.0618 1.0000
13.750 1.3877 0.04283 0.03620 -0.0133 0.0588 1.0000
14.000 1.3901 0.04520 0.03869 -0.0131 0.0556 1.0000
14.250 1.3887 0.04805 0.04163 -0.0132 0.0528 1.0000
14.500 1.3856 0.05120 0.04487 -0.0134 0.0505 1.0000
14.750 1.3855 0.05410 0.04793 -0.0137 0.0479 1.0000
15.000 1.3820 0.05753 0.05147 -0.0144 0.0455 1.0000
15.250 1.3757 0.06149 0.05552 -0.0154 0.0438 1.0000
15.500 1.3697 0.06556 0.05971 -0.0166 0.0421 1.0000
15.750 1.3656 0.06954 0.06384 -0.0178 0.0403 1.0000
16.000 1.3593 0.07399 0.06843 -0.0195 0.0386 1.0000
16.250 1.3508 0.07890 0.07346 -0.0214 0.0372 1.0000
16.500 1.3398 0.08436 0.07901 -0.0238 0.0361 1.0000
16.750 1.3304 0.08969 0.08446 -0.0261 0.0351 1.0000
17.000 1.3224 0.09497 0.08990 -0.0284 0.0338 1.0000
17.250 1.3130 0.10056 0.09564 -0.0311 0.0327 1.0000
17.500 1.3025 0.10649 0.10170 -0.0340 0.0317 1.0000
17.750 1.2914 0.11265 0.10797 -0.0371 0.0308 1.0000
18.000 1.2796 0.11904 0.11445 -0.0405 0.0300 1.0000
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Polar data table (+)
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