MH 83 13.29% (mh83-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 83 13.29% (mh83-il) Reynolds number: 500,000 Max Cl/Cd: 94.11 at α=8.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh83-il-500000.txt Download as CSV file: xf-mh83-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: MH 83 13.29%
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
------ -------- --------- --------- -------- -------- --------
-8.000 -0.2339 0.08768 0.08453 -0.0143 0.6511 0.0239
-7.750 -0.2280 0.08470 0.08153 -0.0157 0.6407 0.0243
-7.500 -0.2238 0.08155 0.07834 -0.0174 0.6308 0.0249
-7.250 -0.2463 0.07387 0.07074 -0.0244 0.6274 0.0264
-7.000 -0.2465 0.06888 0.06574 -0.0287 0.6192 0.0266
-6.750 -0.2348 0.06701 0.06383 -0.0292 0.6084 0.0269
-6.500 -0.2219 0.06482 0.06160 -0.0307 0.5982 0.0272
-6.250 -0.2092 0.06157 0.05831 -0.0342 0.5888 0.0276
-6.000 -0.2048 0.04216 0.03842 -0.0569 0.5890 0.0311
-5.750 -0.1837 0.04095 0.03718 -0.0570 0.5784 0.0314
-5.500 -0.1614 0.03959 0.03579 -0.0578 0.5682 0.0319
-5.250 -0.1436 0.02229 0.01661 -0.0651 0.5662 0.0223
-5.000 -0.1167 0.02015 0.01415 -0.0654 0.5569 0.0220
-4.750 -0.0886 0.01861 0.01226 -0.0656 0.5468 0.0221
-4.500 -0.0603 0.01720 0.01059 -0.0656 0.5370 0.0220
-4.250 -0.0318 0.01603 0.00917 -0.0655 0.5272 0.0219
-4.000 -0.0030 0.01510 0.00806 -0.0654 0.5178 0.0220
-3.750 0.0258 0.01443 0.00720 -0.0653 0.5087 0.0223
-3.500 0.0549 0.01390 0.00654 -0.0652 0.4994 0.0226
-3.250 0.0832 0.01310 0.00567 -0.0651 0.4905 0.0232
-3.000 0.1120 0.01264 0.00519 -0.0651 0.4811 0.0240
-2.750 0.1410 0.01231 0.00479 -0.0650 0.4724 0.0249
-2.500 0.1701 0.01200 0.00442 -0.0650 0.4635 0.0259
-2.250 0.1991 0.01168 0.00403 -0.0650 0.4555 0.0276
-2.000 0.2284 0.01145 0.00377 -0.0650 0.4473 0.0298
-1.750 0.2575 0.01122 0.00347 -0.0650 0.4395 0.0325
-1.500 0.2869 0.01098 0.00322 -0.0650 0.4316 0.0379
-1.250 0.3159 0.01060 0.00298 -0.0651 0.4238 0.0851
-1.000 0.3450 0.01036 0.00291 -0.0652 0.4164 0.1369
-0.750 0.3739 0.01022 0.00287 -0.0653 0.4091 0.1855
-0.500 0.4028 0.01011 0.00287 -0.0653 0.4026 0.2361
-0.250 0.4317 0.00998 0.00288 -0.0654 0.3958 0.2957
0.000 0.4601 0.00985 0.00293 -0.0655 0.3895 0.3786
0.250 0.4887 0.00962 0.00298 -0.0655 0.3834 0.4726
0.500 0.5167 0.00945 0.00304 -0.0655 0.3772 0.5750
0.750 0.5434 0.00923 0.00314 -0.0650 0.3716 0.6990
1.000 0.5637 0.00872 0.00318 -0.0628 0.3666 0.8942
1.250 0.5991 0.00878 0.00318 -0.0641 0.3610 1.0000
1.500 0.6279 0.00897 0.00325 -0.0641 0.3560 1.0000
1.750 0.6570 0.00907 0.00330 -0.0641 0.3515 1.0000
2.000 0.6858 0.00922 0.00336 -0.0641 0.3466 1.0000
2.250 0.7142 0.00944 0.00346 -0.0641 0.3417 1.0000
2.500 0.7430 0.00957 0.00356 -0.0641 0.3377 1.0000
2.750 0.7718 0.00971 0.00365 -0.0641 0.3338 1.0000
3.000 0.8002 0.00988 0.00376 -0.0641 0.3298 1.0000
3.250 0.8283 0.01013 0.00391 -0.0641 0.3258 1.0000
3.500 0.8568 0.01029 0.00405 -0.0641 0.3225 1.0000
3.750 0.8853 0.01043 0.00418 -0.0641 0.3190 1.0000
4.000 0.9136 0.01060 0.00431 -0.0641 0.3154 1.0000
4.250 0.9415 0.01083 0.00447 -0.0641 0.3120 1.0000
4.500 0.9690 0.01113 0.00470 -0.0641 0.3086 1.0000
4.750 0.9973 0.01127 0.00487 -0.0641 0.3061 1.0000
5.000 1.0254 0.01144 0.00503 -0.0641 0.3030 1.0000
5.250 1.0533 0.01163 0.00520 -0.0641 0.2999 1.0000
5.500 1.0808 0.01186 0.00540 -0.0640 0.2969 1.0000
5.750 1.1077 0.01222 0.00569 -0.0639 0.2937 1.0000
6.000 1.1353 0.01241 0.00591 -0.0639 0.2915 1.0000
6.250 1.1629 0.01259 0.00613 -0.0639 0.2890 1.0000
6.500 1.1903 0.01279 0.00633 -0.0639 0.2862 1.0000
6.750 1.2174 0.01302 0.00655 -0.0638 0.2835 1.0000
7.000 1.2441 0.01331 0.00682 -0.0637 0.2809 1.0000
7.250 1.2701 0.01375 0.00720 -0.0636 0.2778 1.0000
7.500 1.2972 0.01393 0.00745 -0.0635 0.2759 1.0000
7.750 1.3240 0.01414 0.00771 -0.0635 0.2735 1.0000
8.000 1.3505 0.01437 0.00798 -0.0634 0.2709 1.0000
8.250 1.3768 0.01463 0.00825 -0.0633 0.2685 1.0000
8.500 1.4026 0.01495 0.00856 -0.0632 0.2662 1.0000
8.750 1.4277 0.01541 0.00898 -0.0630 0.2633 1.0000
9.000 1.4533 0.01569 0.00933 -0.0628 0.2611 1.0000
9.250 1.4789 0.01594 0.00965 -0.0627 0.2588 1.0000
9.500 1.5042 0.01622 0.00999 -0.0625 0.2565 1.0000
9.750 1.5291 0.01651 0.01032 -0.0622 0.2541 1.0000
10.000 1.5535 0.01685 0.01067 -0.0620 0.2515 1.0000
10.250 1.5770 0.01734 0.01114 -0.0617 0.2487 1.0000
10.500 1.6008 0.01773 0.01160 -0.0614 0.2465 1.0000
10.750 1.6244 0.01803 0.01199 -0.0610 0.2442 1.0000
11.000 1.6475 0.01835 0.01239 -0.0607 0.2416 1.0000
11.250 1.6701 0.01870 0.01279 -0.0602 0.2391 1.0000
11.500 1.6917 0.01912 0.01322 -0.0597 0.2365 1.0000
11.750 1.7122 0.01976 0.01383 -0.0591 0.2333 1.0000
12.000 1.7326 0.02011 0.01432 -0.0585 0.2312 1.0000
12.250 1.7520 0.02052 0.01483 -0.0577 0.2286 1.0000
12.500 1.7702 0.02096 0.01535 -0.0568 0.2258 1.0000
12.750 1.7858 0.02147 0.01590 -0.0556 0.2232 1.0000
13.000 1.7970 0.02215 0.01659 -0.0539 0.2205 1.0000
13.250 1.8074 0.02291 0.01742 -0.0523 0.2180 1.0000
13.500 1.8174 0.02366 0.01830 -0.0509 0.2156 1.0000
13.750 1.8273 0.02454 0.01928 -0.0497 0.2129 1.0000
14.000 1.8360 0.02558 0.02038 -0.0487 0.2098 1.0000
14.250 1.8423 0.02690 0.02171 -0.0477 0.2064 1.0000
14.500 1.8495 0.02826 0.02318 -0.0470 0.2034 1.0000
14.750 1.8569 0.02971 0.02475 -0.0465 0.2000 1.0000
15.000 1.8613 0.03147 0.02657 -0.0461 0.1961 1.0000
15.250 1.8622 0.03363 0.02873 -0.0457 0.1924 1.0000
15.500 1.8666 0.03562 0.03086 -0.0456 0.1892 1.0000
15.750 1.8680 0.03796 0.03331 -0.0457 0.1848 1.0000
16.000 1.8643 0.04087 0.03625 -0.0459 0.1809 1.0000
16.250 1.8606 0.04389 0.03935 -0.0462 0.1770 1.0000
16.500 1.8582 0.04693 0.04251 -0.0467 0.1729 1.0000
16.750 1.8499 0.05064 0.04628 -0.0474 0.1690 1.0000
17.000 1.8392 0.05480 0.05049 -0.0483 0.1653 1.0000
17.250 1.8328 0.05866 0.05448 -0.0493 0.1613 1.0000
17.500 1.8208 0.06332 0.05922 -0.0507 0.1572 1.0000
17.750 1.8052 0.06858 0.06451 -0.0523 0.1531 1.0000
18.000 1.7940 0.07345 0.06952 -0.0540 0.1488 1.0000
18.250 1.7777 0.07910 0.07523 -0.0560 0.1447 1.0000
18.500 1.7594 0.08521 0.08139 -0.0584 0.1406 1.0000
18.750 1.7453 0.09085 0.08715 -0.0606 0.1363 1.0000
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Polar data table (+)
Polar graphs
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