CH10 (smoothed) (ch10sm-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: CH10 (smoothed) (ch10sm-il) Reynolds number: 1,000,000 Max Cl/Cd: 175.24 at α=2.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ch10sm-il-1000000.txt Download as CSV file: xf-ch10sm-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: CH10 (smoothed)
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
------ -------- --------- --------- -------- -------- --------
-11.250 0.3003 0.08978 0.08699 -0.1577 0.7760 0.0121
-11.000 0.3046 0.08703 0.08422 -0.1587 0.7724 0.0122
-10.750 0.3103 0.08429 0.08145 -0.1597 0.7687 0.0122
-10.500 0.3170 0.08159 0.07874 -0.1606 0.7655 0.0122
-10.250 0.3263 0.07863 0.07579 -0.1608 0.7621 0.0124
-10.000 0.3354 0.07637 0.07351 -0.1614 0.7585 0.0126
-9.750 0.3447 0.07419 0.07130 -0.1621 0.7550 0.0128
-9.500 0.3532 0.07199 0.06908 -0.1627 0.7514 0.0131
-9.250 0.3617 0.06961 0.06671 -0.1635 0.7482 0.0134
-9.000 0.3697 0.06716 0.06426 -0.1643 0.7447 0.0138
-8.750 0.3770 0.06461 0.06170 -0.1650 0.7413 0.0144
-8.250 0.3430 0.07802 0.07498 -0.1688 0.7490 0.0139
-8.000 0.3535 0.07563 0.07260 -0.1702 0.7452 0.0146
-7.750 0.3597 0.07234 0.06930 -0.1733 0.7413 0.0153
-7.500 0.3686 0.06970 0.06663 -0.1751 0.7373 0.0153
-7.250 0.3780 0.06698 0.06393 -0.1758 0.7342 0.0156
-7.000 0.3910 0.06534 0.06230 -0.1764 0.7307 0.0158
-6.750 0.4029 0.06368 0.06062 -0.1773 0.7270 0.0162
-6.500 0.4133 0.06202 0.05895 -0.1782 0.7232 0.0166
-6.250 0.4279 0.05990 0.05682 -0.1805 0.7199 0.0173
-6.000 0.4475 0.05570 0.05263 -0.1882 0.7165 0.0188
-5.500 0.5975 0.01576 0.01155 -0.2662 0.7098 0.0187
-5.250 0.6373 0.01291 0.00810 -0.2714 0.7064 0.0194
-5.000 0.6678 0.01220 0.00726 -0.2727 0.7037 0.0199
-4.750 0.6975 0.01173 0.00670 -0.2735 0.7007 0.0204
-4.500 0.7270 0.01128 0.00614 -0.2743 0.6975 0.0210
-4.250 0.7562 0.01090 0.00562 -0.2749 0.6943 0.0216
-4.000 0.7851 0.01063 0.00522 -0.2754 0.6909 0.0224
-3.750 0.8142 0.01031 0.00482 -0.2760 0.6883 0.0231
-3.500 0.8439 0.00986 0.00430 -0.2767 0.6853 0.0243
-3.250 0.8724 0.00969 0.00410 -0.2771 0.6821 0.0252
-3.000 0.9007 0.00956 0.00390 -0.2774 0.6790 0.0264
-2.750 0.9290 0.00950 0.00375 -0.2777 0.6757 0.0275
-2.500 0.9583 0.00923 0.00347 -0.2782 0.6731 0.0297
-2.250 0.9865 0.00917 0.00341 -0.2785 0.6701 0.0320
-2.000 1.0151 0.00905 0.00325 -0.2789 0.6670 0.0352
-1.750 1.0429 0.00904 0.00322 -0.2791 0.6639 0.0386
-1.500 1.0709 0.00901 0.00314 -0.2793 0.6606 0.0429
-1.250 1.0987 0.00899 0.00313 -0.2795 0.6579 0.0471
-1.000 1.1268 0.00892 0.00308 -0.2798 0.6549 0.0525
-0.750 1.1541 0.00893 0.00308 -0.2799 0.6517 0.0574
-0.500 1.1815 0.00892 0.00305 -0.2800 0.6486 0.0645
-0.250 1.2083 0.00900 0.00309 -0.2800 0.6451 0.0706
0.000 1.2360 0.00896 0.00309 -0.2802 0.6424 0.0822
0.250 1.2635 0.00894 0.00310 -0.2804 0.6393 0.0975
0.500 1.2908 0.00891 0.00314 -0.2806 0.6361 0.1311
0.750 1.3180 0.00886 0.00324 -0.2808 0.6328 0.2161
1.000 1.3449 0.00890 0.00336 -0.2810 0.6292 0.2867
1.250 1.3720 0.00886 0.00347 -0.2812 0.6265 0.3520
1.500 1.3989 0.00886 0.00358 -0.2813 0.6233 0.4108
1.750 1.4251 0.00890 0.00370 -0.2812 0.6199 0.4685
2.000 1.4507 0.00897 0.00384 -0.2811 0.6165 0.5254
2.250 1.4766 0.00904 0.00399 -0.2810 0.6131 0.5873
2.500 1.5028 0.00901 0.00414 -0.2810 0.6100 0.6679
2.750 1.5263 0.00871 0.00430 -0.2804 0.6066 1.0000
3.000 1.5509 0.00886 0.00440 -0.2800 0.6030 1.0000
3.250 1.5748 0.00906 0.00454 -0.2795 0.5991 1.0000
3.500 1.5993 0.00915 0.00466 -0.2791 0.5959 1.0000
3.750 1.6231 0.00927 0.00478 -0.2786 0.5922 1.0000
4.000 1.6460 0.00944 0.00492 -0.2779 0.5883 1.0000
4.250 1.6676 0.00966 0.00510 -0.2769 0.5841 1.0000
4.500 1.6907 0.00980 0.00526 -0.2763 0.5805 1.0000
4.750 1.7133 0.00995 0.00543 -0.2756 0.5765 1.0000
5.000 1.7345 0.01016 0.00562 -0.2746 0.5723 1.0000
5.250 1.7544 0.01043 0.00587 -0.2733 0.5679 1.0000
5.500 1.7768 0.01059 0.00606 -0.2726 0.5641 1.0000
5.750 1.7976 0.01081 0.00629 -0.2716 0.5596 1.0000
6.000 1.8160 0.01112 0.00658 -0.2701 0.5549 1.0000
6.250 1.8361 0.01138 0.00686 -0.2690 0.5505 1.0000
6.500 1.8565 0.01163 0.00714 -0.2680 0.5459 1.0000
6.750 1.8744 0.01198 0.00748 -0.2666 0.5411 1.0000
7.000 1.8922 0.01235 0.00786 -0.2651 0.5365 1.0000
7.250 1.9122 0.01264 0.00819 -0.2641 0.5318 1.0000
7.500 1.9296 0.01303 0.00860 -0.2626 0.5267 1.0000
7.750 1.9450 0.01354 0.00910 -0.2608 0.5217 1.0000
8.000 1.9643 0.01388 0.00949 -0.2598 0.5168 1.0000
8.250 1.9803 0.01438 0.01001 -0.2581 0.5112 1.0000
8.500 1.9945 0.01497 0.01061 -0.2562 0.5058 1.0000
8.750 2.0112 0.01547 0.01115 -0.2548 0.4990 1.0000
9.000 2.0205 0.01633 0.01199 -0.2522 0.4888 1.0000
9.500 2.0377 0.01825 0.01389 -0.2470 0.4655 1.0000
9.750 2.0459 0.01929 0.01493 -0.2444 0.4545 1.0000
10.000 2.0499 0.02061 0.01622 -0.2413 0.4412 1.0000
10.250 2.0524 0.02209 0.01766 -0.2381 0.4268 1.0000
10.500 2.0542 0.02367 0.01921 -0.2348 0.4123 1.0000
10.750 2.0542 0.02542 0.02093 -0.2315 0.3970 1.0000
11.000 2.0519 0.02743 0.02288 -0.2280 0.3800 1.0000
11.250 2.0469 0.02972 0.02511 -0.2242 0.3613 1.0000
11.500 2.0390 0.03230 0.02761 -0.2203 0.3422 1.0000
11.750 2.0305 0.03502 0.03026 -0.2165 0.3235 1.0000
12.000 2.0210 0.03794 0.03310 -0.2128 0.3025 1.0000
12.250 2.0105 0.04102 0.03610 -0.2091 0.2830 1.0000
12.500 1.9991 0.04426 0.03927 -0.2055 0.2640 1.0000
12.750 1.9895 0.04743 0.04238 -0.2022 0.2450 1.0000
13.000 1.9780 0.05085 0.04572 -0.1989 0.2256 1.0000
13.250 1.9649 0.05448 0.04926 -0.1957 0.2065 1.0000
13.500 1.9516 0.05824 0.05293 -0.1926 0.1849 1.0000
13.750 1.9354 0.06239 0.05697 -0.1894 0.1631 1.0000
14.000 1.9167 0.06687 0.06133 -0.1862 0.1395 1.0000
14.250 1.8970 0.07159 0.06593 -0.1832 0.1151 1.0000
14.500 1.8768 0.07650 0.07072 -0.1804 0.0915 1.0000
14.750 1.8586 0.08125 0.07538 -0.1780 0.0711 1.0000
15.000 1.8438 0.08572 0.07978 -0.1759 0.0552 1.0000
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