CH10 (smoothed) (ch10sm-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: CH10 (smoothed) (ch10sm-il) Reynolds number: 500,000 Max Cl/Cd: 135.37 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ch10sm-il-500000.txt Download as CSV file: xf-ch10sm-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 0.3048 0.09230 0.08899 -0.1579 0.8119 0.0166
-11.000 0.3119 0.08991 0.08661 -0.1585 0.8080 0.0171
-10.750 0.2460 0.10341 0.10000 -0.1570 0.8244 0.0161
-10.500 0.2558 0.10113 0.09772 -0.1580 0.8200 0.0165
-10.250 0.2657 0.09884 0.09539 -0.1592 0.8159 0.0170
-10.000 0.2756 0.09650 0.09301 -0.1604 0.8120 0.0178
-9.750 0.2841 0.09403 0.09056 -0.1622 0.8076 0.0186
-9.500 0.2906 0.09182 0.08834 -0.1645 0.8032 0.0188
-9.250 0.2968 0.08961 0.08609 -0.1668 0.7993 0.0189
-9.000 0.3088 0.08646 0.08294 -0.1670 0.7957 0.0190
-8.750 0.3214 0.08411 0.08058 -0.1672 0.7916 0.0193
-8.500 0.3328 0.08204 0.07850 -0.1679 0.7876 0.0196
-8.250 0.3442 0.07999 0.07640 -0.1690 0.7840 0.0200
-8.000 0.3551 0.07790 0.07431 -0.1702 0.7803 0.0206
-7.750 0.3655 0.07571 0.07213 -0.1714 0.7762 0.0215
-7.500 0.3721 0.07327 0.06968 -0.1750 0.7719 0.0228
-7.250 0.3793 0.07079 0.06717 -0.1783 0.7679 0.0229
-7.000 0.3916 0.06805 0.06445 -0.1775 0.7645 0.0232
-6.750 0.4046 0.06623 0.06263 -0.1775 0.7607 0.0236
-6.500 0.4157 0.06463 0.06102 -0.1780 0.7571 0.0242
-6.250 0.4291 0.06280 0.05915 -0.1796 0.7537 0.0253
-6.000 0.4482 0.05979 0.05614 -0.1873 0.7497 0.0274
-5.750 0.4702 0.05585 0.05222 -0.1951 0.7456 0.0277
-5.500 0.4816 0.05399 0.05034 -0.1938 0.7423 0.0282
-5.250 0.4991 0.05238 0.04870 -0.1945 0.7392 0.0287
-5.000 0.5209 0.05040 0.04668 -0.1975 0.7360 0.0298
-4.750 0.5464 0.04769 0.04398 -0.2029 0.7323 0.0318
-4.500 0.5945 0.04147 0.03768 -0.2189 0.7286 0.0339
-4.250 0.6136 0.04051 0.03670 -0.2189 0.7254 0.0347
-4.000 0.6459 0.03834 0.03445 -0.2238 0.7224 0.0363
-3.750 0.7746 0.02038 0.01555 -0.2648 0.7200 0.0316
-3.500 0.8238 0.01579 0.01015 -0.2722 0.7169 0.0318
-3.250 0.8573 0.01443 0.00842 -0.2741 0.7136 0.0326
-3.000 0.8891 0.01352 0.00723 -0.2753 0.7107 0.0336
-2.750 0.9197 0.01301 0.00662 -0.2763 0.7078 0.0353
-2.500 0.9487 0.01288 0.00642 -0.2768 0.7048 0.0377
-2.250 0.9763 0.01267 0.00614 -0.2769 0.7014 0.0398
-2.000 1.0055 0.01219 0.00562 -0.2776 0.6982 0.0431
-1.750 1.0341 0.01207 0.00544 -0.2779 0.6952 0.0469
-1.500 1.0639 0.01187 0.00519 -0.2786 0.6923 0.0521
-1.250 1.0921 0.01187 0.00515 -0.2789 0.6893 0.0574
-1.000 1.1194 0.01168 0.00499 -0.2791 0.6860 0.0638
-0.750 1.1466 0.01168 0.00497 -0.2792 0.6828 0.0702
-0.500 1.1751 0.01155 0.00483 -0.2796 0.6797 0.0793
-0.250 1.2045 0.01152 0.00474 -0.2801 0.6768 0.0891
0.000 1.2323 0.01152 0.00474 -0.2804 0.6737 0.1028
0.250 1.2590 0.01144 0.00477 -0.2805 0.6704 0.1318
0.500 1.2869 0.01129 0.00487 -0.2809 0.6670 0.2420
0.750 1.3147 0.01123 0.00498 -0.2813 0.6639 0.3434
1.000 1.3435 0.01125 0.00509 -0.2818 0.6609 0.4221
1.250 1.3696 0.01129 0.00526 -0.2818 0.6578 0.4921
1.500 1.3948 0.01130 0.00542 -0.2815 0.6543 0.5603
1.750 1.4207 0.01129 0.00556 -0.2814 0.6508 0.6415
2.000 1.4439 0.01093 0.00564 -0.2806 0.6478 1.0000
2.250 1.4728 0.01111 0.00572 -0.2811 0.6446 1.0000
2.500 1.4963 0.01124 0.00587 -0.2805 0.6412 1.0000
2.750 1.5211 0.01138 0.00599 -0.2801 0.6376 1.0000
3.000 1.5466 0.01152 0.00609 -0.2799 0.6342 1.0000
3.250 1.5736 0.01168 0.00618 -0.2801 0.6309 1.0000
3.500 1.5988 0.01186 0.00636 -0.2799 0.6276 1.0000
3.750 1.6215 0.01202 0.00654 -0.2791 0.6237 1.0000
4.000 1.6453 0.01218 0.00668 -0.2786 0.6200 1.0000
4.250 1.6705 0.01234 0.00681 -0.2784 0.6165 1.0000
4.500 1.6960 0.01255 0.00699 -0.2783 0.6129 1.0000
4.750 1.7162 0.01273 0.00722 -0.2771 0.6088 1.0000
5.000 1.7380 0.01291 0.00741 -0.2762 0.6048 1.0000
5.250 1.7618 0.01310 0.00758 -0.2758 0.6010 1.0000
5.500 1.7847 0.01332 0.00781 -0.2751 0.5971 1.0000
5.750 1.8013 0.01354 0.00808 -0.2732 0.5926 1.0000
6.000 1.8202 0.01376 0.00831 -0.2718 0.5884 1.0000
6.250 1.8437 0.01399 0.00851 -0.2713 0.5844 1.0000
6.500 1.8594 0.01428 0.00886 -0.2693 0.5799 1.0000
6.750 1.8747 0.01457 0.00921 -0.2673 0.5751 1.0000
7.000 1.8935 0.01486 0.00949 -0.2659 0.5707 1.0000
7.250 1.9113 0.01519 0.00985 -0.2644 0.5661 1.0000
7.500 1.9241 0.01559 0.01033 -0.2620 0.5610 1.0000
7.750 1.9403 0.01597 0.01072 -0.2603 0.5562 1.0000
8.000 1.9584 0.01636 0.01111 -0.2589 0.5516 1.0000
8.250 1.9696 0.01688 0.01174 -0.2564 0.5462 1.0000
8.500 1.9841 0.01737 0.01225 -0.2544 0.5411 1.0000
8.750 2.0000 0.01786 0.01276 -0.2528 0.5361 1.0000
9.000 2.0100 0.01853 0.01353 -0.2502 0.5303 1.0000
9.250 2.0235 0.01912 0.01414 -0.2482 0.5247 1.0000
9.500 2.0337 0.01988 0.01496 -0.2458 0.5184 1.0000
9.750 2.0391 0.02084 0.01594 -0.2427 0.5095 1.0000
10.000 2.0420 0.02201 0.01716 -0.2393 0.4991 1.0000
10.250 2.0449 0.02326 0.01842 -0.2360 0.4885 1.0000
10.500 2.0470 0.02462 0.01979 -0.2327 0.4779 1.0000
10.750 2.0493 0.02608 0.02130 -0.2296 0.4667 1.0000
11.000 2.0503 0.02771 0.02295 -0.2264 0.4552 1.0000
11.250 2.0491 0.02956 0.02480 -0.2230 0.4426 1.0000
11.500 2.0466 0.03159 0.02682 -0.2197 0.4296 1.0000
11.750 2.0436 0.03377 0.02899 -0.2164 0.4160 1.0000
12.000 2.0399 0.03610 0.03132 -0.2132 0.4015 1.0000
12.250 2.0331 0.03875 0.03395 -0.2098 0.3859 1.0000
12.500 2.0246 0.04165 0.03682 -0.2064 0.3696 1.0000
12.750 2.0156 0.04470 0.03983 -0.2031 0.3519 1.0000
13.000 2.0043 0.04804 0.04313 -0.1997 0.3332 1.0000
13.250 1.9924 0.05152 0.04656 -0.1965 0.3154 1.0000
13.500 1.9800 0.05515 0.05014 -0.1934 0.2979 1.0000
13.750 1.9666 0.05896 0.05391 -0.1903 0.2806 1.0000
14.000 1.9538 0.06279 0.05769 -0.1875 0.2629 1.0000
14.250 1.9402 0.06678 0.06162 -0.1848 0.2440 1.0000
14.500 1.9247 0.07106 0.06584 -0.1822 0.2245 1.0000
14.750 1.9077 0.07561 0.07031 -0.1796 0.2043 1.0000
15.000 1.8896 0.08033 0.07494 -0.1772 0.1816 1.0000
15.250 1.8688 0.08547 0.07995 -0.1748 0.1567 1.0000
15.500 1.8461 0.09096 0.08530 -0.1726 0.1296 1.0000
15.750 1.8218 0.09673 0.09090 -0.1706 0.1020 1.0000
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Polar data table (+)
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