NACA 1-H-15 AIRFOIL (n1h15-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
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Airfoil: NACA 1-H-15 AIRFOIL (n1h15-il) Reynolds number: 1,000,000 Max Cl/Cd: 150.21 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-n1h15-il-1000000.txt Download as CSV file: xf-n1h15-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 1-H-15 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-10.250 -0.2687 0.09497 0.09232 -0.0483 0.7034 0.0211
-10.000 -0.2677 0.09111 0.08846 -0.0503 0.7024 0.0211
-9.750 -0.2773 0.08546 0.08283 -0.0527 0.7015 0.0213
-9.500 -0.2703 0.08334 0.08070 -0.0532 0.7006 0.0215
-9.250 -0.2653 0.08089 0.07826 -0.0542 0.6997 0.0216
-9.000 -0.2646 0.07793 0.07530 -0.0557 0.6986 0.0217
-8.750 -0.2660 0.07501 0.07239 -0.0572 0.6973 0.0219
-8.500 -0.2740 0.07186 0.06925 -0.0591 0.6960 0.0221
-8.250 -0.2816 0.06908 0.06649 -0.0594 0.6951 0.0223
-8.000 -0.2880 0.06591 0.06331 -0.0599 0.6941 0.0225
-7.750 -0.2874 0.06266 0.06004 -0.0608 0.6930 0.0229
-7.500 -0.2860 0.05899 0.05632 -0.0617 0.6918 0.0234
-7.000 -0.3124 0.04082 0.03751 -0.0607 0.6896 0.0256
-6.750 -0.2975 0.03919 0.03581 -0.0601 0.6885 0.0258
-6.500 -0.2805 0.03790 0.03446 -0.0595 0.6876 0.0261
-6.250 -0.2623 0.03665 0.03314 -0.0591 0.6866 0.0263
-6.000 -0.2449 0.03496 0.03134 -0.0583 0.6857 0.0267
-5.750 -0.2273 0.03308 0.02933 -0.0575 0.6847 0.0273
-5.500 -0.2101 0.03079 0.02685 -0.0563 0.6836 0.0284
-5.250 -0.1928 0.02831 0.02381 -0.0535 0.6822 0.0301
-5.000 -0.1861 0.02340 0.01858 -0.0510 0.6811 0.0310
-4.750 -0.1620 0.02253 0.01770 -0.0508 0.6803 0.0314
-4.500 -0.1378 0.02177 0.01689 -0.0506 0.6794 0.0319
-4.250 -0.1137 0.02092 0.01596 -0.0502 0.6784 0.0328
-4.000 -0.0892 0.01996 0.01483 -0.0496 0.6774 0.0344
-3.750 -0.0687 0.01627 0.01055 -0.0474 0.6764 0.0294
-3.500 -0.0427 0.01502 0.00915 -0.0471 0.6754 0.0291
-3.250 -0.0156 0.01415 0.00816 -0.0470 0.6744 0.0290
-3.000 0.0120 0.01369 0.00762 -0.0470 0.6733 0.0295
-2.750 0.0398 0.01316 0.00702 -0.0471 0.6722 0.0297
-2.500 0.0676 0.01276 0.00655 -0.0471 0.6712 0.0299
-2.250 0.0955 0.01248 0.00621 -0.0472 0.6702 0.0302
-2.000 0.1229 0.01182 0.00552 -0.0473 0.6693 0.0304
-1.750 0.1492 0.01123 0.00491 -0.0471 0.6681 0.0307
-1.500 0.1756 0.01092 0.00459 -0.0470 0.6668 0.0310
-1.250 0.2026 0.01061 0.00430 -0.0470 0.6661 0.0314
-1.000 0.2298 0.01037 0.00409 -0.0470 0.6651 0.0319
-0.750 0.2571 0.01018 0.00391 -0.0471 0.6640 0.0325
-0.500 0.2848 0.01003 0.00379 -0.0472 0.6628 0.0335
-0.250 0.3123 0.00988 0.00364 -0.0473 0.6616 0.0342
0.000 0.3399 0.00976 0.00352 -0.0474 0.6605 0.0350
0.250 0.3677 0.00965 0.00342 -0.0476 0.6594 0.0357
0.500 0.3952 0.00952 0.00328 -0.0477 0.6584 0.0366
0.750 0.4228 0.00939 0.00316 -0.0477 0.6573 0.0384
1.000 0.4506 0.00931 0.00308 -0.0479 0.6563 0.0405
1.250 0.4785 0.00925 0.00302 -0.0481 0.6552 0.0434
1.500 0.5048 0.00907 0.00301 -0.0479 0.6540 0.0991
1.750 0.5011 0.00731 0.00308 -0.0421 0.6523 0.7503
2.000 0.6506 0.00765 0.00399 -0.0681 0.6523 0.9799
2.250 0.7124 0.00784 0.00418 -0.0756 0.6518 0.9865
2.500 0.7611 0.00790 0.00424 -0.0804 0.6510 0.9911
2.750 0.8146 0.00784 0.00419 -0.0862 0.6498 0.9961
3.000 0.8562 0.00763 0.00400 -0.0894 0.6465 0.9988
3.250 0.8891 0.00756 0.00393 -0.0908 0.6446 0.9998
3.500 0.9170 0.00753 0.00390 -0.0912 0.6429 1.0000
3.750 0.9432 0.00749 0.00384 -0.0911 0.6406 1.0000
4.000 0.9689 0.00751 0.00383 -0.0909 0.6377 1.0000
4.250 0.9963 0.00753 0.00390 -0.0913 0.6355 1.0000
4.500 1.0236 0.00753 0.00395 -0.0916 0.6322 1.0000
4.750 1.0508 0.00749 0.00392 -0.0918 0.6282 1.0000
5.000 1.0773 0.00745 0.00385 -0.0918 0.6227 1.0000
5.250 1.1066 0.00750 0.00397 -0.0927 0.6148 1.0000
5.500 1.1350 0.00758 0.00404 -0.0933 0.6056 1.0000
5.750 1.1641 0.00775 0.00420 -0.0942 0.5940 1.0000
6.000 1.1956 0.00814 0.00459 -0.0960 0.5751 1.0000
6.250 1.2301 0.01000 0.00618 -0.1008 0.5095 1.0000
6.500 1.2101 0.01415 0.00987 -0.0981 0.4209 1.0000
6.750 1.1763 0.01555 0.01120 -0.0883 0.4047 1.0000
7.000 1.1421 0.01727 0.01280 -0.0789 0.3787 1.0000
7.250 1.1119 0.01945 0.01477 -0.0711 0.3386 1.0000
7.500 1.0769 0.02227 0.01725 -0.0633 0.2762 1.0000
7.750 1.0494 0.02501 0.01961 -0.0569 0.2073 1.0000
8.000 1.0327 0.02737 0.02164 -0.0521 0.1456 1.0000
8.250 1.0242 0.02940 0.02340 -0.0484 0.0968 1.0000
8.500 1.0220 0.03113 0.02490 -0.0455 0.0584 1.0000
8.750 1.0303 0.03224 0.02595 -0.0437 0.0478 1.0000
9.000 1.0409 0.03324 0.02693 -0.0422 0.0441 1.0000
9.250 1.0519 0.03422 0.02791 -0.0408 0.0410 1.0000
9.500 1.0651 0.03507 0.02878 -0.0395 0.0397 1.0000
9.750 1.0779 0.03596 0.02967 -0.0383 0.0381 1.0000
10.000 1.0887 0.03700 0.03074 -0.0370 0.0368 1.0000
10.250 1.0986 0.03813 0.03187 -0.0356 0.0353 1.0000
10.500 1.1089 0.03924 0.03301 -0.0342 0.0342 1.0000
10.750 1.1224 0.04013 0.03393 -0.0332 0.0336 1.0000
11.000 1.1349 0.04112 0.03494 -0.0321 0.0329 1.0000
11.250 1.1466 0.04218 0.03603 -0.0311 0.0320 1.0000
11.500 1.1581 0.04325 0.03713 -0.0300 0.0313 1.0000
11.750 1.1689 0.04439 0.03828 -0.0289 0.0303 1.0000
12.000 1.1780 0.04569 0.03959 -0.0277 0.0294 1.0000
12.250 1.1819 0.04746 0.04141 -0.0261 0.0283 1.0000
12.500 1.1955 0.04843 0.04242 -0.0254 0.0279 1.0000
12.750 1.2076 0.04952 0.04355 -0.0245 0.0274 1.0000
13.000 1.2193 0.05066 0.04472 -0.0236 0.0269 1.0000
13.250 1.2303 0.05189 0.04598 -0.0228 0.0262 1.0000
13.500 1.2407 0.05317 0.04729 -0.0219 0.0256 1.0000
13.750 1.2525 0.05434 0.04847 -0.0212 0.0248 1.0000
14.000 1.2605 0.05585 0.05001 -0.0202 0.0243 1.0000
14.250 1.2604 0.05807 0.05227 -0.0187 0.0233 1.0000
14.500 1.2727 0.05925 0.05350 -0.0181 0.0230 1.0000
14.750 1.2845 0.06047 0.05476 -0.0176 0.0225 1.0000
15.000 1.2960 0.06172 0.05606 -0.0170 0.0220 1.0000
15.250 1.3064 0.06310 0.05748 -0.0164 0.0214 1.0000
15.500 1.3177 0.06442 0.05882 -0.0159 0.0208 1.0000
15.750 1.3258 0.06603 0.06047 -0.0152 0.0203 1.0000
16.000 1.3355 0.06748 0.06193 -0.0147 0.0198 1.0000
16.250 1.3340 0.07000 0.06450 -0.0136 0.0190 1.0000
16.500 1.3435 0.07153 0.06609 -0.0131 0.0188 1.0000
16.750 1.3540 0.07298 0.06760 -0.0127 0.0184 1.0000
17.000 1.3622 0.07465 0.06932 -0.0123 0.0181 1.0000
17.250 1.3699 0.07642 0.07115 -0.0119 0.0176 1.0000
17.500 1.3793 0.07801 0.07278 -0.0117 0.0171 1.0000
17.750 1.3861 0.07985 0.07467 -0.0113 0.0168 1.0000
18.000 1.3936 0.08169 0.07653 -0.0111 0.0163 1.0000
18.250 1.3975 0.08390 0.07878 -0.0107 0.0159 1.0000
18.500 1.3957 0.08671 0.08165 -0.0102 0.0154 1.0000
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