MH 92 15.49% (mh92-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 92 15.49% (mh92-il) Reynolds number: 1,000,000 Max Cl/Cd: 94.19 at α=10.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh92-il-1000000.txt Download as CSV file: xf-mh92-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: MH 92 15.49%
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
------ -------- --------- --------- -------- -------- --------
-16.250 -0.7153 0.12585 0.12412 0.0237 1.0000 0.0084
-16.000 -0.6999 0.12576 0.12409 0.0235 1.0000 0.0085
-15.750 -0.9240 0.08958 0.08699 -0.0031 1.0000 0.0077
-15.500 -0.9627 0.07816 0.07534 -0.0102 1.0000 0.0077
-15.250 -0.9828 0.07081 0.06783 -0.0146 1.0000 0.0076
-15.000 -1.0019 0.06420 0.06105 -0.0182 1.0000 0.0076
-14.750 -1.0217 0.05802 0.05468 -0.0211 1.0000 0.0075
-14.500 -1.0337 0.05341 0.04992 -0.0227 1.0000 0.0075
-14.250 -1.0466 0.04897 0.04531 -0.0238 1.0000 0.0075
-14.000 -1.0544 0.04545 0.04165 -0.0241 1.0000 0.0074
-13.750 -1.0630 0.04202 0.03804 -0.0239 1.0000 0.0075
-13.500 -1.0671 0.03925 0.03513 -0.0232 1.0000 0.0074
-13.250 -1.0693 0.03675 0.03249 -0.0222 1.0000 0.0074
-13.000 -1.0700 0.03448 0.03009 -0.0208 1.0000 0.0074
-12.750 -1.0679 0.03254 0.02802 -0.0193 1.0000 0.0074
-12.500 -1.0641 0.03079 0.02616 -0.0177 1.0000 0.0074
-12.250 -1.0590 0.02916 0.02442 -0.0160 1.0000 0.0074
-12.000 -1.0519 0.02776 0.02292 -0.0142 1.0000 0.0074
-11.750 -1.0437 0.02646 0.02152 -0.0123 1.0000 0.0075
-11.500 -1.0347 0.02521 0.02018 -0.0104 1.0000 0.0075
-11.250 -1.0241 0.02413 0.01902 -0.0085 1.0000 0.0076
-11.000 -1.0124 0.02316 0.01798 -0.0066 1.0000 0.0076
-10.750 -1.0007 0.02216 0.01691 -0.0047 1.0000 0.0076
-10.500 -0.9866 0.02139 0.01609 -0.0028 1.0000 0.0077
-10.250 -0.9732 0.02056 0.01520 -0.0009 1.0000 0.0077
-10.000 -0.9526 0.01992 0.01450 -0.0001 0.9643 0.0078
-9.750 -0.9487 0.01873 0.01309 0.0038 0.9028 0.0080
-9.500 -0.9397 0.01794 0.01215 0.0069 0.8758 0.0082
-9.250 -0.9236 0.01736 0.01147 0.0089 0.8557 0.0082
-9.000 -0.9060 0.01680 0.01082 0.0106 0.8384 0.0085
-8.750 -0.8861 0.01635 0.01030 0.0120 0.8226 0.0088
-8.500 -0.8655 0.01591 0.00978 0.0132 0.8077 0.0091
-8.250 -0.8447 0.01542 0.00921 0.0145 0.7935 0.0091
-8.000 -0.8225 0.01502 0.00874 0.0155 0.7803 0.0095
-7.750 -0.7999 0.01462 0.00827 0.0165 0.7677 0.0097
-7.250 -0.7536 0.01386 0.00736 0.0182 0.7423 0.0101
-7.000 -0.7321 0.01328 0.00672 0.0194 0.7307 0.0107
-6.500 -0.6829 0.01264 0.00599 0.0207 0.7068 0.0116
-6.250 -0.6578 0.01235 0.00564 0.0213 0.6955 0.0122
-6.000 -0.6331 0.01201 0.00524 0.0220 0.6835 0.0132
-5.750 -0.6077 0.01172 0.00493 0.0225 0.6723 0.0142
-5.500 -0.5822 0.01144 0.00460 0.0231 0.6610 0.0163
-5.250 -0.5566 0.01115 0.00430 0.0236 0.6495 0.0197
-5.000 -0.5312 0.01084 0.00400 0.0241 0.6387 0.0270
-4.750 -0.5062 0.01050 0.00371 0.0247 0.6275 0.0433
-4.500 -0.4814 0.01011 0.00343 0.0252 0.6167 0.0686
-4.250 -0.4577 0.00963 0.00313 0.0259 0.6060 0.1111
-4.000 -0.4342 0.00912 0.00285 0.0266 0.5956 0.1666
-3.750 -0.4106 0.00864 0.00260 0.0273 0.5852 0.2275
-3.500 -0.3865 0.00821 0.00239 0.0279 0.5740 0.2903
-3.250 -0.3615 0.00785 0.00223 0.0284 0.5639 0.3444
-3.000 -0.3362 0.00756 0.00208 0.0289 0.5533 0.3940
-2.750 -0.3108 0.00725 0.00195 0.0294 0.5426 0.4470
-2.500 -0.2853 0.00699 0.00184 0.0299 0.5321 0.4998
-2.250 -0.2593 0.00677 0.00175 0.0303 0.5216 0.5438
-2.000 -0.2331 0.00658 0.00168 0.0307 0.5115 0.5883
-1.750 -0.2066 0.00644 0.00162 0.0311 0.5003 0.6256
-1.500 -0.1794 0.00633 0.00158 0.0313 0.4899 0.6545
-1.250 -0.1517 0.00628 0.00155 0.0315 0.4797 0.6798
-1.000 -0.1240 0.00624 0.00154 0.0317 0.4686 0.7024
-0.750 -0.0959 0.00622 0.00153 0.0318 0.4584 0.7226
-0.500 -0.0678 0.00624 0.00154 0.0319 0.4477 0.7406
-0.250 -0.0393 0.00625 0.00155 0.0320 0.4377 0.7560
0.000 -0.0107 0.00630 0.00157 0.0320 0.4273 0.7686
0.250 0.0178 0.00634 0.00159 0.0320 0.4172 0.7797
0.500 0.0465 0.00639 0.00162 0.0319 0.4075 0.7890
0.750 0.0751 0.00647 0.00165 0.0319 0.3970 0.7983
1.000 0.1040 0.00652 0.00169 0.0319 0.3880 0.8060
1.250 0.1325 0.00661 0.00174 0.0318 0.3782 0.8140
1.500 0.1614 0.00668 0.00177 0.0317 0.3692 0.8210
1.750 0.1898 0.00676 0.00184 0.0317 0.3603 0.8278
2.000 0.2186 0.00684 0.00189 0.0316 0.3524 0.8344
2.250 0.2471 0.00694 0.00195 0.0316 0.3438 0.8405
2.500 0.2756 0.00701 0.00202 0.0316 0.3361 0.8465
2.750 0.3039 0.00714 0.00210 0.0315 0.3275 0.8530
3.000 0.3323 0.00721 0.00218 0.0315 0.3212 0.8593
3.250 0.3602 0.00733 0.00228 0.0316 0.3138 0.8656
3.500 0.3886 0.00744 0.00237 0.0315 0.3074 0.8714
3.750 0.4168 0.00753 0.00245 0.0315 0.3005 0.8762
4.000 0.4446 0.00766 0.00256 0.0315 0.2936 0.8809
4.250 0.4729 0.00775 0.00266 0.0315 0.2882 0.8856
4.500 0.5008 0.00790 0.00276 0.0314 0.2818 0.8902
4.750 0.5286 0.00800 0.00287 0.0315 0.2760 0.8946
5.000 0.5562 0.00811 0.00298 0.0315 0.2703 0.8989
5.250 0.5835 0.00827 0.00312 0.0316 0.2640 0.9036
5.500 0.6113 0.00839 0.00324 0.0316 0.2593 0.9079
5.750 0.6386 0.00850 0.00336 0.0317 0.2538 0.9123
6.000 0.6648 0.00869 0.00352 0.0320 0.2473 0.9169
6.250 0.6918 0.00880 0.00366 0.0321 0.2432 0.9220
6.500 0.7185 0.00894 0.00379 0.0323 0.2379 0.9269
6.750 0.7436 0.00913 0.00397 0.0328 0.2317 0.9318
7.000 0.7698 0.00925 0.00412 0.0331 0.2275 0.9367
7.250 0.7959 0.00941 0.00426 0.0333 0.2219 0.9414
7.500 0.8204 0.00962 0.00445 0.0338 0.2154 0.9459
7.750 0.8461 0.00973 0.00460 0.0342 0.2117 0.9506
8.000 0.8710 0.00990 0.00477 0.0346 0.2069 0.9558
8.250 0.8955 0.01014 0.00499 0.0351 0.2010 0.9605
8.500 0.9213 0.01027 0.00516 0.0353 0.1975 0.9655
8.750 0.9465 0.01045 0.00535 0.0356 0.1930 0.9709
9.000 0.9755 0.01074 0.00562 0.0350 0.1872 0.9744
9.250 1.0053 0.01094 0.00584 0.0343 0.1835 0.9782
9.500 1.0339 0.01116 0.00608 0.0338 0.1792 0.9826
9.750 1.0670 0.01151 0.00640 0.0322 0.1733 0.9843
10.000 1.1003 0.01176 0.00668 0.0307 0.1694 0.9860
10.250 1.1337 0.01205 0.00697 0.0291 0.1649 0.9876
10.500 1.1654 0.01245 0.00735 0.0276 0.1589 0.9898
10.750 1.1972 0.01271 0.00765 0.0263 0.1552 0.9923
11.000 1.2290 0.01305 0.00799 0.0249 0.1504 0.9944
11.250 1.2606 0.01350 0.00843 0.0233 0.1446 0.9966
11.500 1.2931 0.01380 0.00876 0.0218 0.1403 0.9987
11.750 1.3155 0.01421 0.00916 0.0220 0.1354 1.0000
12.000 1.3200 0.01454 0.00950 0.0257 0.1315 1.0000
12.250 1.3333 0.01484 0.00983 0.0278 0.1279 1.0000
12.500 1.3459 0.01531 0.01028 0.0297 0.1231 1.0000
12.750 1.3560 0.01580 0.01078 0.0321 0.1186 1.0000
13.000 1.3649 0.01631 0.01131 0.0345 0.1143 1.0000
13.250 1.3702 0.01713 0.01211 0.0368 0.1089 1.0000
13.500 1.3812 0.01782 0.01283 0.0383 0.1052 1.0000
13.750 1.3887 0.01879 0.01380 0.0398 0.1006 1.0000
14.000 1.3960 0.01987 0.01492 0.0411 0.0968 1.0000
14.250 1.4053 0.02092 0.01601 0.0420 0.0935 1.0000
14.500 1.4105 0.02233 0.01743 0.0429 0.0898 1.0000
14.750 1.4159 0.02383 0.01896 0.0436 0.0865 1.0000
15.000 1.4228 0.02529 0.02047 0.0441 0.0836 1.0000
15.250 1.4255 0.02717 0.02237 0.0444 0.0807 1.0000
15.500 1.4256 0.02936 0.02460 0.0446 0.0774 1.0000
15.750 1.4306 0.03122 0.02653 0.0447 0.0757 1.0000
16.000 1.4320 0.03345 0.02881 0.0446 0.0736 1.0000
16.250 1.4289 0.03617 0.03157 0.0443 0.0713 1.0000
16.500 1.4231 0.03926 0.03473 0.0438 0.0694 1.0000
16.750 1.4226 0.04189 0.03743 0.0433 0.0677 1.0000
17.000 1.4203 0.04476 0.04038 0.0427 0.0663 1.0000
17.250 1.4146 0.04811 0.04380 0.0418 0.0647 1.0000
17.500 1.4055 0.05198 0.04774 0.0406 0.0633 1.0000
17.750 1.3933 0.05631 0.05213 0.0392 0.0617 1.0000
18.000 1.3830 0.06052 0.05643 0.0377 0.0603 1.0000
18.250 1.3771 0.06426 0.06026 0.0364 0.0593 1.0000
18.500 1.3683 0.06844 0.06451 0.0348 0.0580 1.0000
18.750 1.3570 0.07302 0.06917 0.0330 0.0568 1.0000
19.000 1.3429 0.07808 0.07430 0.0309 0.0555 1.0000
19.250 1.3253 0.08374 0.08002 0.0284 0.0539 1.0000
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Polar data table (+)
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