NACA 8-H-12 AIRFOIL (n8h12-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 8-H-12 AIRFOIL (n8h12-il) Reynolds number: 200,000 Max Cl/Cd: 72.02 at α=8.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-n8h12-il-200000.txt Download as CSV file: xf-n8h12-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 8-H-12 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.4026 0.10000 0.09679 0.0050 0.7791 0.0517
-9.250 -0.4155 0.09498 0.09181 -0.0003 0.7742 0.0521
-9.000 -0.4290 0.08964 0.08647 -0.0053 0.7695 0.0523
-8.750 -0.4172 0.08446 0.08126 -0.0024 0.7638 0.0533
-8.500 -0.4029 0.08152 0.07829 -0.0009 0.7555 0.0544
-8.250 -0.3986 0.07815 0.07487 -0.0011 0.7495 0.0559
-8.000 -0.5067 0.07612 0.07262 -0.0143 0.7662 0.0532
-7.750 -0.4926 0.07382 0.07034 -0.0125 0.7587 0.0543
-7.500 -0.4854 0.07095 0.06740 -0.0124 0.7513 0.0554
-7.250 -0.4798 0.06770 0.06405 -0.0130 0.7449 0.0572
-7.000 -0.4754 0.06361 0.05978 -0.0149 0.7375 0.0610
-6.750 -0.4813 0.05772 0.05333 -0.0163 0.7328 0.0642
-6.500 -0.4639 0.05483 0.05057 -0.0160 0.7250 0.0658
-6.250 -0.4490 0.05239 0.04804 -0.0154 0.7182 0.0679
-6.000 -0.4341 0.04955 0.04499 -0.0151 0.7119 0.0717
-5.750 -0.4242 0.04544 0.04030 -0.0145 0.7056 0.0778
-5.500 -0.4058 0.04279 0.03764 -0.0139 0.6999 0.0798
-5.250 -0.3859 0.04060 0.03533 -0.0135 0.6925 0.0835
-5.000 -0.3695 0.03793 0.03214 -0.0122 0.6865 0.0926
-4.750 -0.3495 0.02895 0.02159 -0.0078 0.6833 0.0529
-4.500 -0.3246 0.02632 0.01879 -0.0072 0.6758 0.0510
-4.250 -0.3002 0.02414 0.01624 -0.0061 0.6699 0.0505
-4.000 -0.2740 0.02313 0.01486 -0.0053 0.6639 0.0520
-3.750 -0.2472 0.02155 0.01302 -0.0047 0.6573 0.0527
-3.500 -0.2206 0.01986 0.01114 -0.0042 0.6522 0.0537
-3.250 -0.1931 0.01883 0.01009 -0.0040 0.6454 0.0555
-3.000 -0.1661 0.01820 0.00939 -0.0036 0.6392 0.0588
-2.750 -0.1392 0.01758 0.00862 -0.0030 0.6342 0.0618
-2.500 -0.1122 0.01672 0.00777 -0.0027 0.6275 0.0646
-2.250 -0.0866 0.01608 0.00714 -0.0021 0.6223 0.0699
-2.000 -0.0609 0.01561 0.00661 -0.0014 0.6177 0.0777
-1.750 -0.0355 0.01504 0.00612 -0.0009 0.6116 0.0919
-1.500 -0.0124 0.01419 0.00556 0.0001 0.6067 0.1522
-1.250 0.0531 0.01145 0.00565 -0.0067 0.6014 0.9219
-1.000 0.1638 0.01205 0.00594 -0.0220 0.5935 0.9949
-0.750 0.2028 0.01200 0.00568 -0.0244 0.5891 1.0000
-0.500 0.2275 0.01204 0.00562 -0.0240 0.5845 1.0000
-0.250 0.2526 0.01209 0.00559 -0.0237 0.5795 1.0000
0.000 0.2772 0.01212 0.00550 -0.0231 0.5752 1.0000
0.250 0.3018 0.01219 0.00541 -0.0225 0.5718 1.0000
0.500 0.3276 0.01228 0.00551 -0.0224 0.5665 1.0000
0.750 0.3530 0.01237 0.00554 -0.0220 0.5623 1.0000
1.000 0.3781 0.01246 0.00554 -0.0215 0.5588 1.0000
1.250 0.4031 0.01261 0.00557 -0.0210 0.5559 1.0000
1.500 0.4292 0.01278 0.00579 -0.0210 0.5514 1.0000
1.750 0.4548 0.01293 0.00591 -0.0207 0.5473 1.0000
2.000 0.4802 0.01305 0.00597 -0.0202 0.5438 1.0000
2.250 0.5054 0.01321 0.00605 -0.0197 0.5411 1.0000
2.500 0.5313 0.01347 0.00635 -0.0196 0.5375 1.0000
2.750 0.5572 0.01370 0.00663 -0.0195 0.5337 1.0000
3.000 0.5828 0.01390 0.00682 -0.0192 0.5302 1.0000
3.250 0.6082 0.01406 0.00694 -0.0187 0.5273 1.0000
3.500 0.6335 0.01431 0.00713 -0.0183 0.5249 1.0000
3.750 0.6594 0.01466 0.00761 -0.0183 0.5211 1.0000
4.000 0.6850 0.01494 0.00796 -0.0182 0.5173 1.0000
4.250 0.7105 0.01517 0.00821 -0.0178 0.5140 1.0000
4.500 0.7359 0.01540 0.00843 -0.0174 0.5115 1.0000
4.750 0.7613 0.01570 0.00872 -0.0170 0.5089 1.0000
5.000 0.7865 0.01612 0.00931 -0.0171 0.5044 1.0000
5.250 0.8117 0.01643 0.00970 -0.0169 0.5006 1.0000
5.500 0.8371 0.01656 0.00985 -0.0164 0.4970 1.0000
5.750 0.8626 0.01671 0.00994 -0.0157 0.4936 1.0000
6.000 0.8870 0.01709 0.01054 -0.0157 0.4876 1.0000
6.250 0.9123 0.01720 0.01069 -0.0152 0.4829 1.0000
6.500 0.9382 0.01709 0.01050 -0.0144 0.4781 1.0000
6.750 0.9625 0.01704 0.01062 -0.0139 0.4686 1.0000
7.000 0.9879 0.01674 0.01028 -0.0131 0.4596 1.0000
7.250 1.0132 0.01642 0.00996 -0.0124 0.4498 1.0000
7.500 1.0376 0.01626 0.00992 -0.0118 0.4383 1.0000
7.750 1.0621 0.01606 0.00977 -0.0111 0.4262 1.0000
8.000 1.0866 0.01593 0.00968 -0.0105 0.4140 1.0000
8.250 1.1105 0.01588 0.00971 -0.0099 0.4001 1.0000
8.500 1.1338 0.01593 0.00991 -0.0094 0.3822 1.0000
8.750 1.1560 0.01605 0.01009 -0.0088 0.3580 1.0000
9.000 1.1745 0.01654 0.01051 -0.0080 0.3047 1.0000
9.250 1.1723 0.01883 0.01214 -0.0061 0.2066 1.0000
9.500 1.1592 0.02170 0.01456 -0.0034 0.1426 1.0000
9.750 1.1411 0.02430 0.01696 -0.0002 0.1125 1.0000
10.000 1.1235 0.02715 0.01966 0.0024 0.0922 1.0000
10.250 1.1106 0.03015 0.02256 0.0040 0.0786 1.0000
10.500 1.1030 0.03295 0.02534 0.0050 0.0695 1.0000
10.750 1.0962 0.03580 0.02820 0.0059 0.0635 1.0000
11.000 1.0927 0.03843 0.03085 0.0066 0.0591 1.0000
11.250 1.0850 0.04143 0.03381 0.0074 0.0559 1.0000
11.500 1.0878 0.04352 0.03599 0.0081 0.0532 1.0000
11.750 1.0899 0.04568 0.03819 0.0087 0.0505 1.0000
12.000 1.0910 0.04788 0.04036 0.0094 0.0481 1.0000
12.250 1.0951 0.04965 0.04211 0.0106 0.0460 1.0000
12.500 1.1032 0.05131 0.04386 0.0113 0.0443 1.0000
12.750 1.1130 0.05272 0.04532 0.0123 0.0430 1.0000
13.000 1.1234 0.05409 0.04672 0.0132 0.0416 1.0000
13.250 1.1351 0.05534 0.04798 0.0143 0.0403 1.0000
13.500 1.1536 0.05593 0.04851 0.0163 0.0388 1.0000
13.750 1.1715 0.05699 0.04966 0.0179 0.0378 1.0000
14.000 1.1792 0.05893 0.05176 0.0184 0.0370 1.0000
14.250 1.1878 0.06092 0.05391 0.0189 0.0362 1.0000
14.500 1.1966 0.06298 0.05614 0.0195 0.0356 1.0000
14.750 1.2040 0.06529 0.05860 0.0200 0.0351 1.0000
15.000 1.2087 0.06792 0.06142 0.0203 0.0346 1.0000
15.250 1.2111 0.07085 0.06453 0.0203 0.0342 1.0000
15.500 1.2103 0.07419 0.06806 0.0201 0.0340 1.0000
15.750 1.2071 0.07780 0.07186 0.0196 0.0337 1.0000
16.000 1.2022 0.08168 0.07591 0.0188 0.0334 1.0000
16.250 1.1988 0.08531 0.07967 0.0180 0.0329 1.0000
16.500 1.1869 0.09031 0.08489 0.0164 0.0330 1.0000
16.750 1.1819 0.09426 0.08892 0.0151 0.0323 1.0000
17.000 1.1629 0.10058 0.09550 0.0124 0.0326 1.0000
17.250 1.1102 0.11314 0.10853 0.0058 0.0337 1.0000
17.500 1.0779 0.12303 0.11867 0.0002 0.0341 1.0000
17.750 1.0256 0.13836 0.13428 -0.0088 0.0355 1.0000
18.000 0.9784 0.15455 0.15063 -0.0184 0.0370 1.0000
18.250 0.9558 0.16561 0.16172 -0.0241 0.0380 1.0000
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