NACA 22112 (naca22112-jf) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 22112 (naca22112-jf) Reynolds number: 100,000 Max Cl/Cd: 36.82 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca22112-jf-100000-n5.txt Download as CSV file: xf-naca22112-jf-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 22112
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.250 -0.4437 0.13770 0.13259 -0.0010 1.0000 0.0634
-13.000 -0.4465 0.13469 0.12958 -0.0023 1.0000 0.0656
-12.250 -0.6184 0.12124 0.11581 -0.0008 1.0000 0.0406
-12.000 -0.6135 0.11767 0.11225 -0.0012 1.0000 0.0403
-11.750 -0.5995 0.11774 0.11235 0.0011 1.0000 0.0439
-11.500 -0.6103 0.10905 0.10368 -0.0038 1.0000 0.0390
-11.000 -0.6867 0.08036 0.07476 -0.0267 1.0000 0.0342
-10.750 -0.6995 0.07554 0.06986 -0.0290 1.0000 0.0340
-10.500 -0.7148 0.07118 0.06539 -0.0302 1.0000 0.0338
-10.250 -0.7306 0.06739 0.06148 -0.0297 1.0000 0.0337
-10.000 -0.7445 0.06393 0.05786 -0.0281 1.0000 0.0336
-9.750 -0.7534 0.06035 0.05406 -0.0266 1.0000 0.0335
-9.500 -0.7585 0.05684 0.05030 -0.0248 1.0000 0.0334
-9.250 -0.7601 0.05342 0.04659 -0.0229 1.0000 0.0334
-9.000 -0.7585 0.05015 0.04298 -0.0208 1.0000 0.0334
-8.750 -0.7541 0.04703 0.03950 -0.0187 1.0000 0.0336
-8.500 -0.7502 0.04405 0.03593 -0.0159 1.0000 0.0342
-8.250 -0.7352 0.04191 0.03375 -0.0148 1.0000 0.0350
-8.000 -0.7197 0.04013 0.03186 -0.0135 1.0000 0.0359
-7.750 -0.7048 0.03815 0.02965 -0.0118 1.0000 0.0367
-7.500 -0.6891 0.03607 0.02730 -0.0100 1.0000 0.0371
-7.250 -0.6720 0.03412 0.02506 -0.0083 1.0000 0.0376
-7.000 -0.6537 0.03233 0.02301 -0.0066 1.0000 0.0382
-6.750 -0.6345 0.03074 0.02115 -0.0050 1.0000 0.0392
-6.500 -0.6151 0.02950 0.01954 -0.0032 1.0000 0.0407
-6.250 -0.5942 0.02799 0.01807 -0.0022 1.0000 0.0420
-6.000 -0.5727 0.02679 0.01683 -0.0010 1.0000 0.0431
-5.750 -0.5510 0.02563 0.01563 0.0002 1.0000 0.0441
-5.500 -0.5294 0.02458 0.01452 0.0015 1.0000 0.0454
-5.250 -0.5083 0.02374 0.01358 0.0029 1.0000 0.0475
-5.000 -0.4880 0.02278 0.01264 0.0043 1.0000 0.0494
-4.750 -0.4687 0.02190 0.01185 0.0058 1.0000 0.0512
-4.500 -0.4500 0.02114 0.01113 0.0074 1.0000 0.0529
-4.250 -0.4317 0.02051 0.01050 0.0091 1.0000 0.0552
-4.000 -0.4134 0.02001 0.00997 0.0108 1.0000 0.0580
-3.750 -0.3916 0.01924 0.00926 0.0115 0.9979 0.0612
-3.500 -0.3531 0.01859 0.00856 0.0091 0.9894 0.0659
-3.250 -0.3145 0.01793 0.00787 0.0067 0.9804 0.0730
-3.000 -0.2750 0.01736 0.00726 0.0043 0.9710 0.0830
-2.750 -0.2400 0.01634 0.00660 0.0025 0.9599 0.1285
-2.500 -0.2165 0.01420 0.00633 0.0025 0.9481 0.5070
-2.250 -0.1855 0.01363 0.00635 0.0026 0.9356 0.6428
-2.000 -0.1517 0.01341 0.00645 0.0026 0.9227 0.7296
-1.750 -0.1174 0.01338 0.00656 0.0027 0.9080 0.7921
-1.500 -0.0817 0.01353 0.00679 0.0028 0.8918 0.8449
-1.250 -0.0454 0.01365 0.00686 0.0024 0.8731 0.8760
-1.000 -0.0101 0.01367 0.00677 0.0017 0.8514 0.8922
-0.750 0.0273 0.01369 0.00667 0.0006 0.8280 0.9047
-0.500 0.0635 0.01372 0.00656 -0.0003 0.8014 0.9166
-0.250 0.0978 0.01376 0.00644 -0.0008 0.7716 0.9285
0.000 0.1304 0.01382 0.00631 -0.0011 0.7371 0.9407
0.250 0.1696 0.01390 0.00619 -0.0029 0.6976 0.9485
0.500 0.2048 0.01401 0.00607 -0.0040 0.6593 0.9583
0.750 0.2422 0.01413 0.00598 -0.0057 0.6220 0.9669
1.000 0.2795 0.01425 0.00591 -0.0075 0.5862 0.9750
1.250 0.3157 0.01440 0.00587 -0.0092 0.5507 0.9836
1.500 0.3542 0.01453 0.00581 -0.0114 0.5143 0.9908
1.750 0.3921 0.01470 0.00578 -0.0137 0.4774 0.9977
2.000 0.4195 0.01487 0.00578 -0.0139 0.4448 1.0000
2.250 0.4414 0.01506 0.00582 -0.0129 0.4152 1.0000
2.500 0.4631 0.01529 0.00588 -0.0120 0.3862 1.0000
2.750 0.4846 0.01555 0.00599 -0.0110 0.3579 1.0000
3.000 0.5061 0.01583 0.00613 -0.0100 0.3310 1.0000
3.250 0.5272 0.01615 0.00630 -0.0089 0.3076 1.0000
3.500 0.5486 0.01647 0.00653 -0.0079 0.2867 1.0000
3.750 0.5697 0.01682 0.00677 -0.0068 0.2686 1.0000
4.000 0.5907 0.01720 0.00705 -0.0057 0.2531 1.0000
4.250 0.6117 0.01759 0.00735 -0.0046 0.2403 1.0000
4.500 0.6326 0.01800 0.00770 -0.0035 0.2297 1.0000
4.750 0.6539 0.01840 0.00807 -0.0024 0.2202 1.0000
5.000 0.6745 0.01887 0.00844 -0.0012 0.2124 1.0000
5.250 0.6961 0.01928 0.00889 -0.0002 0.2044 1.0000
5.500 0.7168 0.01977 0.00931 0.0010 0.1981 1.0000
5.750 0.7384 0.02024 0.00981 0.0020 0.1922 1.0000
6.000 0.7597 0.02073 0.01032 0.0031 0.1864 1.0000
6.250 0.7804 0.02131 0.01081 0.0042 0.1816 1.0000
6.500 0.8022 0.02181 0.01142 0.0052 0.1763 1.0000
6.750 0.8237 0.02237 0.01200 0.0061 0.1717 1.0000
7.000 0.8450 0.02299 0.01258 0.0071 0.1677 1.0000
7.250 0.8667 0.02361 0.01330 0.0080 0.1634 1.0000
7.500 0.8883 0.02422 0.01401 0.0089 0.1589 1.0000
7.750 0.9098 0.02487 0.01468 0.0098 0.1550 1.0000
8.000 0.9314 0.02563 0.01539 0.0106 0.1516 1.0000
8.250 0.9524 0.02634 0.01632 0.0115 0.1475 1.0000
8.500 0.9733 0.02707 0.01718 0.0123 0.1435 1.0000
8.750 0.9943 0.02780 0.01793 0.0132 0.1401 1.0000
9.000 1.0153 0.02866 0.01878 0.0139 0.1369 1.0000
9.250 1.0344 0.02955 0.01995 0.0149 0.1330 1.0000
9.500 1.0535 0.03040 0.02097 0.0159 0.1292 1.0000
9.750 1.0731 0.03119 0.02181 0.0168 0.1260 1.0000
10.000 1.0928 0.03211 0.02271 0.0175 0.1231 1.0000
10.250 1.1079 0.03323 0.02420 0.0189 0.1193 1.0000
10.500 1.1238 0.03425 0.02540 0.0201 0.1158 1.0000
10.750 1.1407 0.03506 0.02628 0.0211 0.1126 1.0000
11.000 1.1577 0.03598 0.02720 0.0221 0.1099 1.0000
11.250 1.1665 0.03747 0.02907 0.0238 0.1064 1.0000
11.500 1.1767 0.03868 0.03051 0.0254 0.1031 1.0000
11.750 1.1888 0.03958 0.03147 0.0267 0.1003 1.0000
12.000 1.2022 0.04045 0.03230 0.0279 0.0980 1.0000
12.250 1.1980 0.04245 0.03469 0.0306 0.0952 1.0000
12.500 1.1954 0.04430 0.03679 0.0327 0.0926 1.0000
12.750 1.1962 0.04594 0.03858 0.0341 0.0902 1.0000
13.000 1.2010 0.04728 0.03996 0.0351 0.0881 1.0000
13.250 1.2021 0.04919 0.04194 0.0358 0.0862 1.0000
13.500 1.1846 0.05327 0.04638 0.0357 0.0843 1.0000
13.750 1.1658 0.05798 0.05137 0.0343 0.0827 1.0000
14.000 1.1436 0.06368 0.05732 0.0318 0.0814 1.0000
14.250 1.1086 0.07202 0.06591 0.0270 0.0806 1.0000
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